This document presents the Hydrofret concept, a new type of seaplane designed for freight transport. It aims to reduce congestion at airports by moving freight operations to seaports. The concept involves a large catamaran-hull aircraft that uses ram wing and ground effect technologies to take off and land on water at low speeds. It discusses the challenges of seaplanes and how Hydrofret addresses them through its design. The document provides background on the concept's creators and details on the tandem wing and ram wing configurations intended to enable efficient takeoff and landing.
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
EAGES Proceedings - S. AUBIN & J. MONCHAUXStephan Aubin
1) The document discusses easy experimental methods for studying ground effects, including using a moving belt wind tunnel system to simulate the movement of the ground.
2) It presents a case study on the Mercedes CLK-GTR race car where a 1:10 scale model was tested in wind tunnel to understand flow under the car and ground clearances.
3) Key findings included that downforce increases with lower ground clearance up to a point where the boundary layer blocks the underbody flow, and that side skirts and rear wings help increase downforce by preventing crossflows and increasing underbody velocity.
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
EAGES Proceedings - S. AUBIN & J. MONCHAUXStephan Aubin
1) The document discusses easy experimental methods for studying ground effects, including using a moving belt wind tunnel system to simulate the movement of the ground.
2) It presents a case study on the Mercedes CLK-GTR race car where a 1:10 scale model was tested in wind tunnel to understand flow under the car and ground clearances.
3) Key findings included that downforce increases with lower ground clearance up to a point where the boundary layer blocks the underbody flow, and that side skirts and rear wings help increase downforce by preventing crossflows and increasing underbody velocity.
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
EAGES Proceedings - K. V. Rozhdestvenskii 1Stephan Aubin
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
Development of a Integrated Air Cushioned Vehicle (Hovercraft)IJMER
1) The document describes the development of an integrated air cushion vehicle (hovercraft) prototype. It details the design of major components like the hull, skirt, air box, engine assembly, and integrated lift and thrust system using one propeller.
2) Calculations are shown for determining the required air volume, pressures, and component sizes based on the hovercraft's weight and dimensions. A suitable impeller is selected to provide the needed airflow and pressure.
3) Fabrication of the prototype from materials like plywood, polystyrene, and aluminum is described. Testing showed the hovercraft could lift and propel itself carrying 75kg at 70mm above the surface at near 20km/hr.
This document summarizes a study about hovercraft design. It discusses the key components of a hovercraft including the lift fan, thrust propellers, momentum curtain, skirt, air box, and rudders. It provides details on hovercraft operation, including how lift and thrust are generated. Calculations are shown for determining the necessary lift forces, power requirements, and thrust forces. The results demonstrated the hovercraft's ability to hover with over 300 pounds of payload. In conclusion, hovercraft require careful design to overcome challenges while allowing for low friction movement over various surfaces.
The document discusses aircraft performance certification and optimizing an aircraft's payload and range ability given physical and environmental limitations. It covers manufacturer's weight empty, operating empty weight, maximum zero fuel weight, maximum takeoff weight, and how payload and fuel affect an aircraft's range. Changing design aspects like maximum takeoff weight, zero fuel weight, and fuel capacity can impact the payload-range envelope.
The document discusses factors that affect aircraft takeoff and landing performance at airfields, including:
- Runway length required for takeoff versus available length based on aircraft weight and design
- Impact of obstacles that must be cleared during takeoff
- Effects of high temperature and altitude on airfield performance due to lower air density
- Impact of wet runways, wind conditions, and maximum certified landing weight on performance.
Hovercraft presentation-The Future is Now!Riaz Zalil
Hovercrafts provide an amphibious mode of transportation that can move equally on land and water surfaces. They work by using lifted air to create a cushion that allows the craft to hover above the ground or water. Key elements include a lifting fan to pressurize air under the craft, flexible skirts around the edges to contain the air, and propulsion fans at the rear. While early conceptual designs date back to the 18th century, hovercrafts were first realized in the 1950s. They have since found uses in passenger transportation, military operations, and recreational activities due to their ability to traverse varied terrain with minimal environmental impact.
The document discusses hovercrafts, including their history, design, operation, and applications. Some key points:
- Hovercrafts were first conceptualized in the 1870s but were pioneered in the 1950s by Christopher Cockerell, who patented the design.
- They work by blowing air under the hull with lift fans to create an air cushion that allows movement over land and water. Flexible skirts around the edges contain the air.
- In addition to passenger ferry services, hovercrafts see military uses like mine countermeasures and transport. Future applications may include hover trains and cars.
Final 2012 navair_accomplishments_28_mar13_musicl_resCharles Abell
This document summarizes the accomplishments of the Strategic Leadership Support Team (AIR-7.1) in 2022. It lists over 100 achievements across naval aviation programs including testing new aircraft like the F-35, KC-130J, X-47B, and MQ-4C Triton. It also details engine repairs, component repairs, weapons testing and deliveries, training initiatives, and partnerships with organizations to support naval aviation.
AIRCRAFT WEIGHT AND BALANCE BASIC FOR LOAD CONTROLjasmine jacob
The document discusses aircraft weight and balance requirements. It covers key topics such as:
1) Compliance with weight and balance limits is critical for flight safety, as exceeding maximum weight limits can compromise structural integrity and affect aircraft performance. Operating with the center of gravity outside approved limits can also cause control difficulties.
2) Proper load planning, distribution, and securing of cargo and baggage is required. Various aircraft compartments and structural loading limitations must be followed.
3) Dangerous goods and special items require special documentation and handling procedures. Records of weight and balance calculations must be retained for regulatory compliance.
The document presents a design project for a canard wing for the Hawk MK 132 aircraft. It provides background on Hindustan Aeronautics Limited and the Hawk MK 132 aircraft. The objective is to design and develop a small close coupled canard wing for the aircraft to provide pilots experience flying canard configuration aircraft during training. The methodology involves calculations for center of gravity travel, canard sizing, and stability and control analyses. Tables of calculated lift, drag, and pitching moment coefficients for the canard wing at various angles of attack are also presented.
The document describes a personal jet aircraft called the Recurve designed by students. The Recurve is intended to make private aircraft ownership more affordable and can carry a pilot and two passengers. It has a range of over 1,000 miles, can cruise at over 190 mph at 20,000 feet, and can takeoff and land on runways under 2,000 feet. The students selected a canard configuration for its suitability to amateur pilots while providing space for passengers.
The document discusses progress and challenges in foundational hypersonics research. It notes that hypersonic flight requires integration across multiple disciplines including aerodynamics, materials science, and combustion. Recent accomplishments include unprecedented insights from large-scale simulations and optical diagnostics, as well as international partnerships providing opportunities for scientific flight research through programs like HIFiRE. Ongoing challenges include fully understanding nonequilibrium phenomena at small scales and limited access to hypersonic flight environments for testing.
The document summarizes the design of a fighter aircraft by Dudekula Jamal. It includes collecting reference data from 15 existing aircraft, estimating parameters like weight, selecting engines, designing the wing and tail, estimating lift and drag, and presenting performance characteristics. Diagrams and side views of the proposed design are also provided. The document concludes that the preliminary design addresses key considerations but that experience is important for successful aircraft design.
This document summarizes a seminar presentation on hovercrafts. It includes:
- An introduction to hovercrafts, describing them as vehicles that can fly, float, and drive over surfaces like grass, mud, sand, water and ice.
- A brief history of hovercraft development, noting early designs in the 1700s and the inventor who successfully built the first hovercraft in the 1960s.
- Descriptions of the basic components of hovercrafts, including lifting fans, thrust propellers, flexible skirts, engines, and rudders.
- An explanation of how hovercrafts work based on lift and propulsion principles using air pressure under the flexible skirt.
This presentation provides an overview of key aspects of airport runways and taxiways, including:
- Runway designations are based on magnetic headings using two numbers separated by a slash.
- Runway markings help pilots identify the runway and provide visual guidance, including centerlines, edge lines, and displaced thresholds.
- The length and surface of runways must support the largest aircraft using the airport.
- Taxiways connect runways to aircraft parking areas and have markings to guide aircraft movement.
- Runway and taxiway lights aid in low-visibility conditions and identify surfaces for aircraft.
This document provides an overview of weight and balance concepts for aircraft. It defines key terms like empty weight, useful load, center of gravity, moment, and arm. It explains how weight and balance affects aircraft performance and safety. Maintaining the proper center of gravity is important for longitudinal stability and control. Being over or under weight limits can reduce performance and endurance or cause structural issues. The document also describes how to calculate weight and balance using information in the aircraft's Pilot Operating Handbook.
This document discusses the V-n diagram, which plots the velocity of an aircraft against the load factor it experiences. It outlines how load factors are calculated based on the lift and weight of the aircraft. Limit, proof and ultimate load factors are explained which specify the maximum loads aircraft structures must be designed to withstand. Typical load factors for different aircraft types are shown, with fighters experiencing the highest positive load factors due to high-performance maneuvering. The V-n diagram defines the flight envelope and structural limits for an aircraft.
The document discusses the concepts of stability, maneuverability, and controllability as they relate to aircraft design. It states that stability causes an aircraft to return to steady flight after a disturbance, maneuverability allows the pilot to move the aircraft easily about its axes, and controllability is the ability to respond to pilot inputs. However, increasing one of these characteristics typically decreases another, so aircraft designs involve compromises. The document then examines longitudinal, lateral, and directional stability in more detail.
Applications of Circulation Control, Yesterday and TodayCSCJournals
Circulation control, an aerodynamic method of changing the properties of an airfoil, such as lift, camber and angle of attack, has been used in several unique ways since its inception, as an enhancement to fixed wing aircraft, in the 1960’s. Early in the research venture, this technology was used on the main wing of an aircraft in conjunction with a Coandă surface, such as a rounded trailing edge or a deployable flap. Research during this time proved to be the foundation of the circulation control technology and showed that small amounts of exit jet velocity could have a large impact on the aerodynamics of an airfoil. In the 1970’s the inspirations that drove circulation control research changed from design work to optimization of the parameters which were found to have the most effect on circulation control. These studies included slot placement, favorable momentum coefficient, and pressurization benefits and determents. This research period also allowed for expansion of the uses of circulation control to submarine/hydrodynamic and rotary wing applications. Newest research has brought on several propeller driven applications and the recent push for efficient renewable research has allowed circulation control research technologies to evolve into use in wind turbine and water turbine applications. The idea being that with circulation control the turbine can adapt easier to the changing wind velocity and direction and ultimately capture more power than an un-augmented turbine. As with most new and novel technologies there is a process and time delay associated with their development and ultimate application. For some technologies the market, or the supporting hardware, are lacking and sometimes the technology has strong advocacies for yet to be fulfilled expectations. In most of these cases a strong idea will re-surface repeatedly until the art has matured, or the better solution is found. This paper will focus on the previously developed circulation control research, from its beginnings, as used on fixed wing aircraft, following the progression, as this technology evolved through the past five decades, to its now more widely considered potential.
Changes in transport over recent decades have resulted in reduced travel times and costs, facilitating increased global travel and shifts in global manufacturing. Advances like larger container ships and ports have supported growth in imports to countries like the UK from China, indicating Asia's rising economic influence. Faster and cheaper transport has weakened the friction of distance, connecting distant places.
The document describes a new vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) architecture being developed by VTOL Technologies that is well-suited for urban, mountainous, and maritime environments. The flying wing design with four thrust-vectoring propulsion units offers high payload capacity, endurance, and safety advantages over fixed-wing and rotorcraft UAVs. It can operate in tight spaces and recover from ships, withstanding gusts better than other designs. The unique VTOL system could enable applications like security for the 2012 London Olympics.
EAGES Proceedings - K. V. Rozhdestvenskii 1Stephan Aubin
In 2001 Euroavia Toulouse organized a symposium on ground effect. We invited most of the Russian and German actors, and some experts from Holland, UK or France for a week of science around the subject of ekranoplans / flying boats. This was dedicated to students. A book was issued... and now that all copies have been sold for a while I am sharing this on LinkedIn for everyone.
Enjoy.
Stéphan AUBIN
Development of a Integrated Air Cushioned Vehicle (Hovercraft)IJMER
1) The document describes the development of an integrated air cushion vehicle (hovercraft) prototype. It details the design of major components like the hull, skirt, air box, engine assembly, and integrated lift and thrust system using one propeller.
2) Calculations are shown for determining the required air volume, pressures, and component sizes based on the hovercraft's weight and dimensions. A suitable impeller is selected to provide the needed airflow and pressure.
3) Fabrication of the prototype from materials like plywood, polystyrene, and aluminum is described. Testing showed the hovercraft could lift and propel itself carrying 75kg at 70mm above the surface at near 20km/hr.
This document summarizes a study about hovercraft design. It discusses the key components of a hovercraft including the lift fan, thrust propellers, momentum curtain, skirt, air box, and rudders. It provides details on hovercraft operation, including how lift and thrust are generated. Calculations are shown for determining the necessary lift forces, power requirements, and thrust forces. The results demonstrated the hovercraft's ability to hover with over 300 pounds of payload. In conclusion, hovercraft require careful design to overcome challenges while allowing for low friction movement over various surfaces.
The document discusses aircraft performance certification and optimizing an aircraft's payload and range ability given physical and environmental limitations. It covers manufacturer's weight empty, operating empty weight, maximum zero fuel weight, maximum takeoff weight, and how payload and fuel affect an aircraft's range. Changing design aspects like maximum takeoff weight, zero fuel weight, and fuel capacity can impact the payload-range envelope.
The document discusses factors that affect aircraft takeoff and landing performance at airfields, including:
- Runway length required for takeoff versus available length based on aircraft weight and design
- Impact of obstacles that must be cleared during takeoff
- Effects of high temperature and altitude on airfield performance due to lower air density
- Impact of wet runways, wind conditions, and maximum certified landing weight on performance.
Hovercraft presentation-The Future is Now!Riaz Zalil
Hovercrafts provide an amphibious mode of transportation that can move equally on land and water surfaces. They work by using lifted air to create a cushion that allows the craft to hover above the ground or water. Key elements include a lifting fan to pressurize air under the craft, flexible skirts around the edges to contain the air, and propulsion fans at the rear. While early conceptual designs date back to the 18th century, hovercrafts were first realized in the 1950s. They have since found uses in passenger transportation, military operations, and recreational activities due to their ability to traverse varied terrain with minimal environmental impact.
The document discusses hovercrafts, including their history, design, operation, and applications. Some key points:
- Hovercrafts were first conceptualized in the 1870s but were pioneered in the 1950s by Christopher Cockerell, who patented the design.
- They work by blowing air under the hull with lift fans to create an air cushion that allows movement over land and water. Flexible skirts around the edges contain the air.
- In addition to passenger ferry services, hovercrafts see military uses like mine countermeasures and transport. Future applications may include hover trains and cars.
Final 2012 navair_accomplishments_28_mar13_musicl_resCharles Abell
This document summarizes the accomplishments of the Strategic Leadership Support Team (AIR-7.1) in 2022. It lists over 100 achievements across naval aviation programs including testing new aircraft like the F-35, KC-130J, X-47B, and MQ-4C Triton. It also details engine repairs, component repairs, weapons testing and deliveries, training initiatives, and partnerships with organizations to support naval aviation.
AIRCRAFT WEIGHT AND BALANCE BASIC FOR LOAD CONTROLjasmine jacob
The document discusses aircraft weight and balance requirements. It covers key topics such as:
1) Compliance with weight and balance limits is critical for flight safety, as exceeding maximum weight limits can compromise structural integrity and affect aircraft performance. Operating with the center of gravity outside approved limits can also cause control difficulties.
2) Proper load planning, distribution, and securing of cargo and baggage is required. Various aircraft compartments and structural loading limitations must be followed.
3) Dangerous goods and special items require special documentation and handling procedures. Records of weight and balance calculations must be retained for regulatory compliance.
The document presents a design project for a canard wing for the Hawk MK 132 aircraft. It provides background on Hindustan Aeronautics Limited and the Hawk MK 132 aircraft. The objective is to design and develop a small close coupled canard wing for the aircraft to provide pilots experience flying canard configuration aircraft during training. The methodology involves calculations for center of gravity travel, canard sizing, and stability and control analyses. Tables of calculated lift, drag, and pitching moment coefficients for the canard wing at various angles of attack are also presented.
The document describes a personal jet aircraft called the Recurve designed by students. The Recurve is intended to make private aircraft ownership more affordable and can carry a pilot and two passengers. It has a range of over 1,000 miles, can cruise at over 190 mph at 20,000 feet, and can takeoff and land on runways under 2,000 feet. The students selected a canard configuration for its suitability to amateur pilots while providing space for passengers.
The document discusses progress and challenges in foundational hypersonics research. It notes that hypersonic flight requires integration across multiple disciplines including aerodynamics, materials science, and combustion. Recent accomplishments include unprecedented insights from large-scale simulations and optical diagnostics, as well as international partnerships providing opportunities for scientific flight research through programs like HIFiRE. Ongoing challenges include fully understanding nonequilibrium phenomena at small scales and limited access to hypersonic flight environments for testing.
The document summarizes the design of a fighter aircraft by Dudekula Jamal. It includes collecting reference data from 15 existing aircraft, estimating parameters like weight, selecting engines, designing the wing and tail, estimating lift and drag, and presenting performance characteristics. Diagrams and side views of the proposed design are also provided. The document concludes that the preliminary design addresses key considerations but that experience is important for successful aircraft design.
This document summarizes a seminar presentation on hovercrafts. It includes:
- An introduction to hovercrafts, describing them as vehicles that can fly, float, and drive over surfaces like grass, mud, sand, water and ice.
- A brief history of hovercraft development, noting early designs in the 1700s and the inventor who successfully built the first hovercraft in the 1960s.
- Descriptions of the basic components of hovercrafts, including lifting fans, thrust propellers, flexible skirts, engines, and rudders.
- An explanation of how hovercrafts work based on lift and propulsion principles using air pressure under the flexible skirt.
This presentation provides an overview of key aspects of airport runways and taxiways, including:
- Runway designations are based on magnetic headings using two numbers separated by a slash.
- Runway markings help pilots identify the runway and provide visual guidance, including centerlines, edge lines, and displaced thresholds.
- The length and surface of runways must support the largest aircraft using the airport.
- Taxiways connect runways to aircraft parking areas and have markings to guide aircraft movement.
- Runway and taxiway lights aid in low-visibility conditions and identify surfaces for aircraft.
This document provides an overview of weight and balance concepts for aircraft. It defines key terms like empty weight, useful load, center of gravity, moment, and arm. It explains how weight and balance affects aircraft performance and safety. Maintaining the proper center of gravity is important for longitudinal stability and control. Being over or under weight limits can reduce performance and endurance or cause structural issues. The document also describes how to calculate weight and balance using information in the aircraft's Pilot Operating Handbook.
This document discusses the V-n diagram, which plots the velocity of an aircraft against the load factor it experiences. It outlines how load factors are calculated based on the lift and weight of the aircraft. Limit, proof and ultimate load factors are explained which specify the maximum loads aircraft structures must be designed to withstand. Typical load factors for different aircraft types are shown, with fighters experiencing the highest positive load factors due to high-performance maneuvering. The V-n diagram defines the flight envelope and structural limits for an aircraft.
The document discusses the concepts of stability, maneuverability, and controllability as they relate to aircraft design. It states that stability causes an aircraft to return to steady flight after a disturbance, maneuverability allows the pilot to move the aircraft easily about its axes, and controllability is the ability to respond to pilot inputs. However, increasing one of these characteristics typically decreases another, so aircraft designs involve compromises. The document then examines longitudinal, lateral, and directional stability in more detail.
Applications of Circulation Control, Yesterday and TodayCSCJournals
Circulation control, an aerodynamic method of changing the properties of an airfoil, such as lift, camber and angle of attack, has been used in several unique ways since its inception, as an enhancement to fixed wing aircraft, in the 1960’s. Early in the research venture, this technology was used on the main wing of an aircraft in conjunction with a Coandă surface, such as a rounded trailing edge or a deployable flap. Research during this time proved to be the foundation of the circulation control technology and showed that small amounts of exit jet velocity could have a large impact on the aerodynamics of an airfoil. In the 1970’s the inspirations that drove circulation control research changed from design work to optimization of the parameters which were found to have the most effect on circulation control. These studies included slot placement, favorable momentum coefficient, and pressurization benefits and determents. This research period also allowed for expansion of the uses of circulation control to submarine/hydrodynamic and rotary wing applications. Newest research has brought on several propeller driven applications and the recent push for efficient renewable research has allowed circulation control research technologies to evolve into use in wind turbine and water turbine applications. The idea being that with circulation control the turbine can adapt easier to the changing wind velocity and direction and ultimately capture more power than an un-augmented turbine. As with most new and novel technologies there is a process and time delay associated with their development and ultimate application. For some technologies the market, or the supporting hardware, are lacking and sometimes the technology has strong advocacies for yet to be fulfilled expectations. In most of these cases a strong idea will re-surface repeatedly until the art has matured, or the better solution is found. This paper will focus on the previously developed circulation control research, from its beginnings, as used on fixed wing aircraft, following the progression, as this technology evolved through the past five decades, to its now more widely considered potential.
Changes in transport over recent decades have resulted in reduced travel times and costs, facilitating increased global travel and shifts in global manufacturing. Advances like larger container ships and ports have supported growth in imports to countries like the UK from China, indicating Asia's rising economic influence. Faster and cheaper transport has weakened the friction of distance, connecting distant places.
The document describes a new vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) architecture being developed by VTOL Technologies that is well-suited for urban, mountainous, and maritime environments. The flying wing design with four thrust-vectoring propulsion units offers high payload capacity, endurance, and safety advantages over fixed-wing and rotorcraft UAVs. It can operate in tight spaces and recover from ships, withstanding gusts better than other designs. The unique VTOL system could enable applications like security for the 2012 London Olympics.
Aeronautical New Projects in different parts of the worldEduardoFalco16
Airbus is renewing its fleet of ships that transport aircraft parts between Europe and the US. The new fleet will consist of 3 modern, low-emission vessels equipped with wind-assisted propulsion technologies to reduce CO2 emissions. This supports Airbus' goal of reducing industrial emissions by 63% by 2030. Airbus selected Louis Dreyfus Armateurs to build, operate and maintain the new fleet.
This document provides a final report on the design of an executive water jet aircraft called the Jaeger. Key points:
- The design was conducted by 10 students over 11 weeks to explore the feasibility of an amphibious business jet.
- The Jaeger concept was selected through a tradeoff study and features a high wing, twin engine T-tail configuration with retractable floats.
- Performance estimates indicate it can carry 16 passengers up to 6,000 nm at a cruise speed of 0.85 Mach.
- Critical subsystems like operations on water, hydrodynamic drag, and stability were analyzed to assess feasibility of the concept.
Port Automation – Navigating the Underwriting RisksGen Re
With the global economy still unpredictable, industries across the world are striving to protect their profit margins. This is certainly the case for cargo carriers where fluctuating trade volumes and low freight rates continue to fuel the drive for efficiencies.
THE DISRUPTIVE POTENTIAL OF SUBSONIC AIR-LAUNCHFinmeccanica
Telespazio VEGA Deutschland present POTENTIAL OF SUBSONIC AIR-LAUNCH .
Presented at The 12th Reinventing Space Conference, organised this year by the British Interplanetary Society, will take place in London, UK between Tuesday 18 - Friday 21 November 2014
Urban air mobility (UAM) uses electric vertical take-off and landing (eVTOL) aircraft to provide air transportation services within urban areas. It has the potential to reduce traffic congestion and transportation costs. Realizing UAM faces challenges including battery limitations, noise issues, safety and certification concerns, and the need for supporting infrastructure and regulations. Recent technological advances and industry partnerships aim to develop solutions to overcome these challenges and enable UAM services to launch in the coming years.
This article discusses the design features of modern Airbus Industry A320neo aircraft, and is the study of the mechanism, directions on the patterns of the impact of new technologies on the emergence and development of a class of long haul passenger aircraft. Ruzmatov P. A. "Design Features of Modern A320PEO Aircraft" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-6 | Issue-3 , April 2022, URL: https://www.ijtsrd.com/papers/ijtsrd49881.pdf Paper URL: https://www.ijtsrd.com/engineering/aeronautical-engineering/49881/design-features-of-modern-a320peo-aircraft/ruzmatov-p-a
Airships as low cost alternatives to communication satelliteSasidhar Reddy
i want to share my views on airship as low cost alternatives to communication satellite we have only pdf of this topic because i searched a lot i didn't find any ppt so i make it and presented well in my college so i am sharing this ppt to present easily and for infromation
This document discusses the use of computational modeling to study hydrofoil design improvements for reducing water takeoff distances of amphibious aircraft. It provides background on challenges in amphibious aircraft design and limited prior research on using hydrofoils. The author develops a preliminary computational framework to assess hydrofoil performance and effectiveness for amphibious aircraft applications, focusing on optimizing hydrofoil position, span, and incidence angle to minimize water takeoff distance while maintaining aircraft stability. A case study applies this framework to a 10-seater amphibious aircraft concept, finding that a hydrofoil can reduce hull resistance and water takeoff distance.
The document discusses future possibilities for commercial air travel powered by hydrogen. It suggests that hydrogen could replace kerosene as the fuel for commercial airliners by the mid to long term future. Short-range commuter flights may be served by high-speed electric trains, while mid-range flights between 2000-5000km could use modified hydrogen-powered airliners operating from existing airports. Long-range intercontinental travel over 5000km may be enabled by scramjet-powered planes fueled by liquid hydrogen, allowing flights between continents in a small number of hours. The document outlines concepts for a hydrogen fuel cell platform stationed at high altitude to fuel and service scramjet planes, and details regarding the proposed structure and operations of
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,\, SIMULATIO~J Or' R/IPID SHIP um,0l1Drnr, BY HF.LICOPTF:R
I '
t '
Bruce F. :Powers
Center for !lava] Analyses
University of r o =hester*
Arlington, Virginia
Martin Goldberq
Industrial Engineering Department
Illinois Institute of Tc chnoloqy
Chicago, Illinois
Introduction and Summary
A ship with helico:)ters aboard arrives
in the vicinity of a shore line. 'l'he com.'llander
intends to ooerate the helicooters so as to
unload the ship as raoidly as· possible. The
ship's c a rgo is to be delivered to a soecific
point ashore by the helico~ters. The arrival
rate of the cargo at that point will neasure
the effectiveness of the \L'1loading ooeration.
The co:-:-...~ander must decide at what distance
to station the ship from the unloadinq ooint
ashore, how rnany of his helicopters to use
for the unloading, and the grouoinq of the
participa ting helicopters. He knows, or
has reliable estimates of, the ti~ e scent by
helicopters while loadinq or refueling on the
ship, unloadinq at the ooint ashore, and
flying b e tween . the ship. and ooint as h ore.
This paper describes a simulation model
"''hich can assist the comr.iander with his
decisions.
Discussion
This problem is faced by the amphibious
forces of the U.S. Navy and exercises are
conducted by the Na\~ to train forces and
to test different policies f or helicopter
unloadin g s. The develop::'.ent of a model of
the unloading proce ss would permit testing
alternate unloading policies without the
expense of sending a shio to sea. It wo~ld
permit examination of the imolicat ions of
changes in the design of the ship, the design
of helicopters, or the capacity of the
unloading point.
Anothe~ problem is also faced by the
Navy. If victims of a disaster such as a
flood or earthquake require evacuation, the
Navy would pr o bably as si gn a shio with
helicopters to the task. For medical reasons
or because of the threat of loss of life, the
helico?ter e v acuation may have to be conducted
as rapidly as possible. The aoolicability.of
a model of ship unloading could readily be
transferred to the evacuation problem.
The m~de l could also be useful for
examination of harbor ooeration oolicies
where sufficient berthing space for waiting
ships is unavailable. Under such conditions,
the use of helicopters for unloadinq shies
while in the roadstead might be an attractive
alternative to having the ships wait for
berthing space. The model can aid dcvelooment
of costing information to permit choice among
these alternative harbor management policies.
De scriotion of the System
The shio arrives in the unloadinq area
and takes stati o n as shown in Figure 1.
D
HELICOl'TEAS
Up,;lOAOll<G
POINT
SHORE Llf\: E
Figure 1. Sketch of Sy5tem
Helicopters are stored on the ship with
rotors folde d to conserve soace. When needed
to ferry cargo, helicooters are brought uo to
th.
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1. Hydrofret Concept
Prepared for the EAGES 2001 International Ground Effect Symposium
Toulouse, France
June 2001
Georges Gazuit & Yves Goupil
G. Gazuit
10 rue de la Gaiet´e
03100 Montlu¸con France
Y. Goupil
86 rue de la federation
75015 Paris France
233
3. Hydrofret Concept
Georges Gazuit & Yves Goupil
ABSTRACT
Yves Goupil and Georges Gazuit are currently studying a new concept they baptized Hydrofret,
to move the freight transport bases from the classic airports to the harbours, in order to minimize
the number of airplanes flying over inhabited regions, as well as limit the saturation problem we
are currently witnessing.
Their seaplane is not restricted to the classic limitations of air-based aircrafts and could provide
a global solution to a high number of potential problems that will occur in the next 20 years.
At least, it is worth have a thought about it.
ABOUT THE AUTHORS
Georges Gazuit
Born in 1926 in Montlu¸con
Ing´enieur des Arts et M´etiers - Cluny 1943
Ing´enieur m´ecanicien honoraire (LV) d’A´eronavale
Industrial career : Radial Tyres machines builder. International leader between 1965 and 1985.
Aviation fan :
– Design and construction of a 5m-span biplane (40 HP) in 1948
– Design and construction of a metal made 4-seater (150 HP)shown at Le Bourget in 1969 and
1970. Plane certified and sold to a Canadian company
– participates with the Amiral Goupil to the study of a new concept : Hydrofret using ground
effect for take-off and a new tandem wing configuration also regarded as a potential solution
for marine UAV
Owner of more than 30 patents in different domains
Yves Goupil
Born in Normandy (1931)
The Amiral Goupil made his whole career in the French Marine (1951-1991). He studied at the
Ecole Navale and was formed as a fighter pilot (carriers) in the US-Navy. All-weather pilot.
He worked at the CEV Bretigny and was also Chief-Pilot of the CEV-Cazaux, mainly on the
weaponry trials and landing and catapult-launching trials on carriers : Etendard, Crusader and
Marine Jaguar prototype . . .
Chef du Cabinet Militaire du Ministre de la D´efense, Major G´eneral de la MARINE.
Associated with Georges Gazuit within the Hydrofret project.
235
5. Georges Gazuit & Yves Goupil Hydrofret Concept 237
FIRST PART - YVES GOUPIL
Why The Sea Plane ?
The air transport is somewhat victim of its success. At the actual growth rate, the traffic will
increase 100 % within 10 years. This will induce large problems of congestion of Airports and
associated airspaces, as we see it already today. Technical solutions are studied to increase the
efficiency of the Air Traffic Control ; but the most acute problem exist on airports. To cope with
that, two major actions are proposed :
1. Airports extension or constructions of new ones .
2. Larger capacity aircrafts (super-jumbos)
– Action 1 is hampered by
– the reduction of land spaces available at reasonable distance from the main cities, and
corresponding high costs
– the growing environmental constraints linked to noise effect on populations.
– Action 2 has some drawbacks : passengers are reluctant to the reduction of the number of
scheduled flights offered per day.
– The existing airport infrastructures will need extensive update to accept super-jumbos :
runways, taxiways, parkings, passenger access gangways.
Of course, Actions 1 and 2 are essential, but insufficient to achieve a 100 % growth of the
traffic within 10 years. Air transports professionals estimate a maximum improvement of 40 %
with implementation of these actions. So it appears absolutely necessary to look for additional and
new solutions to prevent unacceptable congestion of the air traffic in a near future. One solution
would be to divert part of the traffic out of airports prone to saturation. The only traffic which
can be so diverted (without effect on passengers) is the air freight, less dependant on the proximity
of main cities. This solution is already used on some closed military airfields, but that remains
marginal. If we want to be completely independent from congested airports, the only abundant
receptacles are the water surfaces : lakes, large rivers, sea bays leading to the main maritime ports.
That implies to come back to the SEAPLANE : so is the HYDROFRET project.
The Seaplane presents some specific advantages :
– reduced operating infrastructure : no runways, taxiways, parkings. The loading-unloading
equipments of commercial maritime ports can be used.
– much less weight limited than aircrafts(impaired by landing gear complexity, overall size
inside the OACI square of 80m × 80m).Furthermore, the bigger the seaplane is, the more
seaworthy it is.
– under 250 tons max weight, amphibious capacity is possible, giving the highest versatility in
air transport.
– lower environmental impact (flight over water during take-off and landing)
The seaplane presents also some specific challenges of which the most serious are : sea water
corrosion and interaction between hull an water surface at high speed (150 knots).
6. 238 EAGES Proceedings
– corrosion problems are well known : good solutions exist but request specific surveillance.
– very limited experience is available concerning the behaviour of a hull at 150 knots on the
water. We are very conscious of this problem.
HYDROFRET has been specially designed to have the lowest take-off and water landing speeds
as possible. That is a must. This is achieved (we hope so ! ! !) by a specific aerodynamic formula :
– Catamaran hull
– Tandem wings
– Large surface lifting fuselage
– Use of Ram wing, air cushion and surface effect lifts.
Figure 1 : Hydrofret in harbor
Figure 2 : Hydrofret
7. Georges Gazuit & Yves Goupil Hydrofret Concept 239
APPENDIX
AIR FREIGHT TRANSPORT EXPANSION
Air freight today
The air freight has increased from 80 billions tons per km in 1990 to 150 billions tons per km
in 2000 (i.e. 6.5 % annual rate).This rate is about two percentage points higher than the rate for
passenger traffic for the same period. Air freight today represent 40 % in value of all the goods
moving worldwide but only less than 2 % in tonnage. The actual worlds fleet of freighters (rough
figures), consists of 1600 units of which two thirds are narrow-body aircrafts. Freight capacity
ranging from 10 tons payload (BAe 146 F), to 110 tons (B 747-400). About 25 % of these aircrafts
were directly built as freighter and 75 % initially used as passenger aircrafts for an average 15-20
years period and then converted to freighters. 60 % of the air freight is still travelling in the cargo-
luggage bay of the passenger aircrafts but this percentage is rapidly decreasing in favor of pure
freighters.
Air Freight in the future
The growth rate in air cargo traffic for the next 20 years is estimated at 6 % per year (minimum)
compared to 4.5 % for passengers. Tonnage would approach 500 billions tons per km by 2020.
Freighter productivity will increase and the corresponding fleet will double while the traffic levels
more than triple.
This evolution has many reasons :
– multiplication of worldwide exchanges.
– increased consumption of off season products
– e-commerce which justifies rapid transport and delivery.
– high value of manufactured products in ever increased quantity, requiring the shortest dura-
tion transport.
The 2020 freighter fleet will consist of 3750 aircrafts with 3100 new ones to be delivered over
the period. 60 % will be wide-body aircrafts (average payload : 50-60 tons, max payload : 200-250
tons).
Among the improvements to be considered for the new freighters which could affect their design
are :
– ease of loading-unloading operations ( roll-on roll-off possibility, large cargo doors)
– large volume of the cargo bay : the average density of air freight is around 1.5 which means
that very often, the limit volume of the cargo is reached well before all the tonnage capacity
of the freighter is used.
– possibility to use common intermodal containers.
CONCLUSION
A lot of interesting work ahead for young designers ! ! ! ! (the figures given here are taken from
Aviation Week)
8. 240 EAGES Proceedings
SECOND PART - GEORGES GAZUIT
Hydrofret
Innovation generally presents two different aspects :
– Fundamental innovation which is not directly linked to a specific need.
– Cyclic innovation which rehabilitate an old concept to a new requirement.
The seaplane HYDROFRET, belongs to this second aspect, as well as the tram or the electric car.
The seaplane used water but did not like it. There are many reasons to that :
– Corrosion
– High hydrodynamic drag (water density=800 times air density)
– Suction effect on the hull during take-off, which requires the use off a step
– High level off vibrations in relation with speed on the water
– Possible impacts with floating or submerged foreign objects.
Today, when the ideas of profitability, efficiency and safety are essential, the seaplane is still
considered penalized unless you reduce these drawbacks in raising the seaplane out of water at the
lowest possible speed.
Out of water speed
There is one way to reduce this speed when the aerodynamic lift is still insufficient : create an
additional vertical thrust. Several systems may be envisaged :
1. Direct lift engines.
2. Vectored thrust engines(Harrier)
3. Conversion of kinetic energy into vertical thrust such as :
– Air-cushion(Hovercraft) : air pressure generated by a power source is sent inside a volume
closed by a flexible skirt
– Ram wing effect : a simplified air -cushion with two lateral surfaces and a mobile flap to
close the volume at the rear.
– Ground effect (Ekranoplan)
1 and 2 are impaired by a poor efficiency leading to high fuel consumption while 3 has given way
to different solutions with pro and con results.
The air-cushion has a very good efficiency, but is unstable in pitch and roll, and requests a
distinct power source and a cumbersome skirt.
9. Georges Gazuit & Yves Goupil Hydrofret Concept 241
The Ram wing no longer needs a skirt but usually remains unstable and has a weaker effect
than air-cushion. Furthermore, the air escaping by the open front face acts as an additional drag.
Ground effect is given free, providing you have a sufficient speed.
In the case of Hydrofret, this speed would be above the speed at which we expect to raise the
seaplane out of the water.
Figure 3 : The 3 phases of take-off
Hydrofret options
Ram Wing
We have opted for a Ram wing during the initial phase of take-off (0 to 70-80 knots), then for
ground effect.
Reasons for that are :
– simplicity of Ram wing operation
– Possibility to have the two lateral surfaces as floats of a catamaran design.
– Advantages of the catamaran :
– large internal volume (150 % of a conventional hull) lifting effect of the fuselage (10-15 %
of total lift)
– reduced cross-stress
– Use of forward engines as power source for Ram wing effect (see the graphs of take-off).
In the first phase, the Ram wing effect is prevailing ; in the second, the ground effect is taking
over and the mobile rear flap is gradually retracted.
However, theoretically, the catamaran presents a larger wetted surface and corresponding drag
than the classical design. But this negative effect is reduced by the noticeable lift of the fuselage
(15 %) which allows an equivalent reduction of the wing surface. So the Lift to Drag ratio of the
design is better than we had at first anticipated. This has been confirmed by wind tunnel tests on
a 1/66 model.
10. 242 EAGES Proceedings
Figure 4 : Phase 1
Tandem wing
This is the second option of Hydrofret. Above 500 tons max weight, the span of a mono-wing
aircraft exceeds the 80 meters required by ICAO (International Civil Aviation Organisation). Our
concept would be even larger with a Flying Wing design.
The only two solutions are :
– folding outer wing panels
– Tandem wing.
Figure 5 : Phase 2
But the Tandem Wing has a bad reputation ! !
The past experiences (Pou du ciel, Delanne, Nenadovitch) were so disappointing that the
concept was considered aerodynamically unacceptable. The culprit was the interaction between
the wings.
The possible solution was obvious : find a relative position of the rear wing where there is no
longer significant interaction from the front wing. This position can be defined by the values of D/
11. Georges Gazuit & Yves Goupil Hydrofret Concept 243
L and H / L, where D=longitudinal distance between the leading edges of the wings, H=vertical
distance, L=mean chord length of profile.
We have studied the problem under different aspects :
– Theoretical
– Mr LAPORTE from the Ecole Polytechnique, has written a thesis on deflexion of an air
flow behind a profile and interaction on a second profile downstream.
– NACA and French Publications (SUPAERO), on the subject.
– Practical
– Wind tunnel test on the 1 / 66 model at MALAVARD facility (ORLEANS), by Mr DE-
VINANT (Ecole Sup´erieure de l’Energie et des Mat´eriaux).
– Flights of a small radio-controlled model.
Figure 6 : Theoretical study
Figure 7 : Wind Tunnel Results
12. 244 EAGES Proceedings
The corresponding results appear on the graphs : with D/L ≥ 4 and H/L ≥ 1, the aerody-
namic efficiency of the rear wing is 98-99 % at low incidence, and 95-96 % at high incidence (the
corresponding deflexions being 0.5◦
and 2◦
on the rear wing). Moreover, the lift vs. drag curve
is becoming flat at max incidence : there is no definite stall but a purpoising effect between two
incidences.
To sum up the tandem wings concept should allow :
– 30 % reduction of span
– 3.6 % reduction off wing structural weight(thanks to a decrease in flexion stress), i.e. 2 % on
the total structure.
– better application of Whitcomb law
– deletion of the stabilizer (pitch control by differential flap action on both wings)
– better lift on take-off (no more negative lift induced by a stabilizer).
These improvements are favorable for the design of a very large aircraft.
DISCUSSION
Jean Margail (JM), Airbus
Your project is very interesting in terms of innovation, but you speak about the market and I
would like to know your estimate of the selling price of such a craft ? My point of view is that your
competitors will be older crafts, for example the companies that are more likely to be interested,
like UPS or FedEx, by your craft usually buy Boeings 747 for 15 millions of US Dollars and spend
10 millions for the modifications.
Yves Goupil (YG), Hydrofret
I agree with you that the fly away price would be much in the advantage of Airbus or Boeing
products. But I will give you an example. The artificial Island of Osaka costed, with only one
runway, costed 12 billions of US Dollars ! So what ? To land on the water with a ground based
aircraft on a artificial area costed 12 billions Dollars ? So if you speak about economy, just looking
at the airplane price, then you are completely right. The problem is that if you look at air transport
as a full system, and you add the price of the new airports, for infrastructures, for environmental
regulations and the price you will pay for the delays . . ., you will have a cheaper aircraft but taking
into account all the rest, I am not sure wether it will be in the advantage of the seaplane or not.
Everybody is paying is paying in the air transport system, all the actors : the builders, the airports,
the customers and the companies but nobody is able to evaluate the global cost of this system.
Some parts are cheaper with a ground based aircraft, some are cheaper with our design, I would
say that our design would be better in terms of operating cost for example.
JM
Classical aircrafts are compelled to follow several regulations, I am certain that your craft will
suffer such regulations, too. There will also be an extra cost for maintenance.
YG
My experience of cargo based freighter is that sea water corrosion is well treated. But then the
craft has to be designed to be well and easily maintained. You don’t need taxiways, you don’t
13. Georges Gazuit & Yves Goupil Hydrofret Concept 245
need runways, you can load and unload the craft using classical marine containers and classical
maritime devices.
JM
I agree, your design is very good. Well, what I am talking about is the reality of the market.
Companies like UPS and FedEx are really fighting for cutting down the purchase price.
YG
Do you know the total cost generated by delays for US companies last year ? 5 billions US Dollars !
You can do a lot with such an amount of money !
JM
What was the main reason for these delays ?
YG
Congestion ! Congestion and weather. During the summer, there are lots of thunderstorms. In
Europe, the average delay is now well over 15 minutes, with 35% delayed by more than 15 minutes.
This must be counted ! In the USA, lots of aircrafts are waiting for 30 minutes for landing. This is
also an operating cost.
More, I am thinking about a place that will sure play a big role in commercial aviation : South-
East Asia. The geographical characteristic is archipelagos of mountain islands. The runways are
really expensive there. The people are already living on the sea-side. I think that for these people,
the best solution is to buy seaplanes. Think about the cost of a landing fee on the artificial airport
in Osaka. It is 40% than elsewhere. . .
JM
But I am sure that authorities will invent some taxes to fly over water. It’s business !
YG
But the artificial runway already has to be reinforced ! Otherwise, in 40 years it will be completely
sunk ! Imagine that 3 companies already left Kensai ! They were thinking about building a second
runway, but it is not sure they’ll do it.
Hanno Fischer (HF), Fischer Flugmechanik
This is a very interesting project and I would like to know the L/D during take-off.
YG
We expect it to be between 7 and 8, and about 16 in flight.
HF
Because this determines the necessary power you install on the craft.
YG
We have on the biggest Hydrofret that weighs 1000 tonnes 8 engines and the total thrust is about
280 tonnes.
HF
What is interesting with your concept compared to a pure ground effect craft is that you can use
the extra power used for take-off to increase the cruise speed of your craft, and this we cannot do
for the moment on our ground effect crafts. So I think the combination has a good chance !
YG
I insist on the fact that it is not a ground effect machine. It is a normal seaplane that has an
aerodynamic configuration allowing the lowest take-off and landing speed.
14. 246 EAGES Proceedings
But our experience of ground effect is that if the waves are more than 20m, which can happen,
then, where is the ground effect ?
HF
This is question of dimension and speed. If you are big enough and fast enough, you don’t feel it.
With a bad road, if you drive fast enough, you don’t feel all the holes !
Mario Mihalina (MM), Euroavia Zagreb
Why didn’t you start with a smaller project ? All the other projects started with smaller crafts . . .
YG
But it is not a project, it is a concept ! The reason why we made such a big design is to show that
such a big seaplane is easier to design than a comparable airplane in terms of payload or weight.