The document discusses maneuverability testing of the MiG-21 fighter jet. It describes how US evaluations found the MiG-21 could maintain controllability and turn performance at much lower speeds and higher angles of attack than indicated in Soviet manuals. Even highly maneuverable jets like the F-15 struggled in dogfights against the MiG-21 at low speeds. The document analyzes aerodynamic characteristics that gave the MiG-21 excellent low-speed maneuverability, such as a delta wing design and stability at high angles of attack.
The document compares 4th generation fighters the F-15 and Su-27. It notes that the Su-27 was intended to surpass the F-15 in overall capability with improvements like 10% larger dimensions and engines for greater thrust. The Su-27 also has a more optimized cross-section and internal fuel capacity for comparable range to rivals using external tanks. Both fighters improved maneuverability over previous generations with innovations like larger wings, more powerful engines, and advanced flight control systems.
The document discusses criticisms of the U.S. Air Force's procurement of the F-22 fighter jet. It argues that the Air Force has ignored lessons from history by prioritizing technology like stealth and speed over situational awareness and dogfighting ability. While stealth technology provides some advantages, it does not make aircraft invisible and radars must still be operated to engage enemies. The document also questions whether the F-22 can fulfill its mission of gaining the first sighting of an enemy when its rearward visibility is limited. Overall, the document asserts that the Air Force's focus on the F-22's technological capabilities does not guarantee success against a thinking enemy in realistic air combat situations.
The document provides background information on the Mikoyan MiG-29 fighter jet. It discusses:
1) The MiG-29 was designed in the Soviet Union in the 1970s to meet the need for a new fighter capable of countering modern Western fighters like the F-16, while also defending Soviet airspace and attacking ground targets.
2) When it first appeared, the MiG-29's capabilities were not well understood in the West and it was often dismissed as an inferior copy of Western fighters. It is now recognized as an highly aerodynamically advanced design with excellent dogfighting abilities, though its avionics are limited for beyond visual range combat.
3) Upgrades
Oral presentation of my final report while attending the National Test Pilot School (NTPS) in Mojave, CA, as a student flight test engineer. Published without corrections.
The F-35 is designed to work with most legacy weapons.
And the F-35 with the internal fusion engine will allow a whole new approach to the development and use of weapons. Here the focus is upon the legacy weapons.
Legacy 4th generation fighters must load all of their weapons externally which directly impacts aerodynamic performance (agility) and radar cross-section (RCS).
In fact, any strides made to reduce airframe RCS are lost.
5th generation have the option of loading stores internally.
Legacy 4th gen fighters must carry external fuel tanks in order to overcome the drag penalty of the external ordinance.
The F-35 does not need external fuel tanks for two reasons:
1) the airframe was specifically designed to carry significant amounts of internal fuel and,
2) there is no aerodynamic drag from internal ordinance.
A 4th gen fighter is unable to safely penetrate denied airspace. This is airspace for which the threats are able to dominate entirely against the 4th generation.
5th gen fighters are able to penetrate denied airspace.
The internal ordinance of an F-35 is approximately that of an F-16 loaded “wall to wall.”
Because the weapons are internal, the F-35 has a much longer combat range fully loaded or significantly longer loiter time in the area of interest.
In the permissive environment, the F-35 holds another advantage over the F-16: payload.
The F-35 has 11 hard points and can carry about three times the stores load.
External weapons on an F-35 impact aerodynamic performance such that our range is about the same as an F-16.
The picture in slide 4shows an F-35A model with a full compliment of internal stores.
This loadout, which is all internal, is about 5000lbs.
Internal carriage means ZERO impact on radar cross section and ZERO aerodynamic drag.
An F-16, fully loaded, with external stores carries just over 5000lbs and because the load is external the radar cross sections is severely impacted as well as having a significant hit to aerodynamic performance.
The weapons within the blue cone can be carried internally.
The weapons with orange color font will be certified for carry in the SDD phase of the program.
Block 2 weapons carriage and release will be conducted this year.
By the end of block 2, AIM-120 and JDAM will be certified.
On day 1, when stealth is of primary importance, the F-35s will probably be loaded internally.
When stealth is less important, there are 11 hard points on the airplane, which allow about 18,000lbs of ordinance to be carried.
Fighter Performance in Practice: F-4 Phantom vs MiG-21mishanbgd
Book Reviews -
If you want to know who really has the better performance F-4 or MiG-21, who is more maneuverable or faster, you can find it only in this book based on official aircraft manuals.
Who is faster or more agile operationaly and who is on paper can be seen only in this book.
I'm working like performance test engineer for Airbus, after work for Lockheed Martin.
I congratulate you for your book. It's good and specially there are not another book like this in the market.
What I read is very good, with precision, you have focused in a good point of view of analysis. I would like to be so good as you to compare 2 aircraft !!! )
It's really a good job.
I hope 2012. will be the year when you will offer a new and excellent publication about aircraft !! )
Whiskey Golf
Air Force Association - F-22 Versus F-35 ComparisonTommy Toy
The document summarizes the complementary capabilities of the F-22A and F-35A fifth generation fighter aircraft. It describes their different but complementary missions, including air superiority for the F-22A and strike capability for the F-35A. Their stealth, sensors, and weapons allow them to penetrate hostile airspace and eliminate threat sanctuaries that non-stealthy aircraft cannot access in a timely manner for time-sensitive targets. Together they provide expanded and flexible options for responding to emerging threats compared to older legacy fighters.
Blended Wing Body (BWB) - Future Of AviationAsim Ghatak
What is Blended Wing Body, History, Advantages And Disadvantages, Design and Structure, How airplanes Fly, Conventional airplanes vs. BWB, Future Scope And Challenges.
The document compares 4th generation fighters the F-15 and Su-27. It notes that the Su-27 was intended to surpass the F-15 in overall capability with improvements like 10% larger dimensions and engines for greater thrust. The Su-27 also has a more optimized cross-section and internal fuel capacity for comparable range to rivals using external tanks. Both fighters improved maneuverability over previous generations with innovations like larger wings, more powerful engines, and advanced flight control systems.
The document discusses criticisms of the U.S. Air Force's procurement of the F-22 fighter jet. It argues that the Air Force has ignored lessons from history by prioritizing technology like stealth and speed over situational awareness and dogfighting ability. While stealth technology provides some advantages, it does not make aircraft invisible and radars must still be operated to engage enemies. The document also questions whether the F-22 can fulfill its mission of gaining the first sighting of an enemy when its rearward visibility is limited. Overall, the document asserts that the Air Force's focus on the F-22's technological capabilities does not guarantee success against a thinking enemy in realistic air combat situations.
The document provides background information on the Mikoyan MiG-29 fighter jet. It discusses:
1) The MiG-29 was designed in the Soviet Union in the 1970s to meet the need for a new fighter capable of countering modern Western fighters like the F-16, while also defending Soviet airspace and attacking ground targets.
2) When it first appeared, the MiG-29's capabilities were not well understood in the West and it was often dismissed as an inferior copy of Western fighters. It is now recognized as an highly aerodynamically advanced design with excellent dogfighting abilities, though its avionics are limited for beyond visual range combat.
3) Upgrades
Oral presentation of my final report while attending the National Test Pilot School (NTPS) in Mojave, CA, as a student flight test engineer. Published without corrections.
The F-35 is designed to work with most legacy weapons.
And the F-35 with the internal fusion engine will allow a whole new approach to the development and use of weapons. Here the focus is upon the legacy weapons.
Legacy 4th generation fighters must load all of their weapons externally which directly impacts aerodynamic performance (agility) and radar cross-section (RCS).
In fact, any strides made to reduce airframe RCS are lost.
5th generation have the option of loading stores internally.
Legacy 4th gen fighters must carry external fuel tanks in order to overcome the drag penalty of the external ordinance.
The F-35 does not need external fuel tanks for two reasons:
1) the airframe was specifically designed to carry significant amounts of internal fuel and,
2) there is no aerodynamic drag from internal ordinance.
A 4th gen fighter is unable to safely penetrate denied airspace. This is airspace for which the threats are able to dominate entirely against the 4th generation.
5th gen fighters are able to penetrate denied airspace.
The internal ordinance of an F-35 is approximately that of an F-16 loaded “wall to wall.”
Because the weapons are internal, the F-35 has a much longer combat range fully loaded or significantly longer loiter time in the area of interest.
In the permissive environment, the F-35 holds another advantage over the F-16: payload.
The F-35 has 11 hard points and can carry about three times the stores load.
External weapons on an F-35 impact aerodynamic performance such that our range is about the same as an F-16.
The picture in slide 4shows an F-35A model with a full compliment of internal stores.
This loadout, which is all internal, is about 5000lbs.
Internal carriage means ZERO impact on radar cross section and ZERO aerodynamic drag.
An F-16, fully loaded, with external stores carries just over 5000lbs and because the load is external the radar cross sections is severely impacted as well as having a significant hit to aerodynamic performance.
The weapons within the blue cone can be carried internally.
The weapons with orange color font will be certified for carry in the SDD phase of the program.
Block 2 weapons carriage and release will be conducted this year.
By the end of block 2, AIM-120 and JDAM will be certified.
On day 1, when stealth is of primary importance, the F-35s will probably be loaded internally.
When stealth is less important, there are 11 hard points on the airplane, which allow about 18,000lbs of ordinance to be carried.
Fighter Performance in Practice: F-4 Phantom vs MiG-21mishanbgd
Book Reviews -
If you want to know who really has the better performance F-4 or MiG-21, who is more maneuverable or faster, you can find it only in this book based on official aircraft manuals.
Who is faster or more agile operationaly and who is on paper can be seen only in this book.
I'm working like performance test engineer for Airbus, after work for Lockheed Martin.
I congratulate you for your book. It's good and specially there are not another book like this in the market.
What I read is very good, with precision, you have focused in a good point of view of analysis. I would like to be so good as you to compare 2 aircraft !!! )
It's really a good job.
I hope 2012. will be the year when you will offer a new and excellent publication about aircraft !! )
Whiskey Golf
Air Force Association - F-22 Versus F-35 ComparisonTommy Toy
The document summarizes the complementary capabilities of the F-22A and F-35A fifth generation fighter aircraft. It describes their different but complementary missions, including air superiority for the F-22A and strike capability for the F-35A. Their stealth, sensors, and weapons allow them to penetrate hostile airspace and eliminate threat sanctuaries that non-stealthy aircraft cannot access in a timely manner for time-sensitive targets. Together they provide expanded and flexible options for responding to emerging threats compared to older legacy fighters.
Blended Wing Body (BWB) - Future Of AviationAsim Ghatak
What is Blended Wing Body, History, Advantages And Disadvantages, Design and Structure, How airplanes Fly, Conventional airplanes vs. BWB, Future Scope And Challenges.
Leonardo AW101 NAWSARH - The superior solutionsLeonardo
The AW101 helicopter is a multi-role maritime and utility platform that can fulfill various operational requirements such as tactical transport, search and rescue, special forces operations, and maritime operations. It has a proven heritage of over 388,000 flight hours conducting missions worldwide. The AW101 provides class-leading performance with benefits such as a large and flexible cabin, long range and endurance, low vibration and noise levels, and inherent safety features like triple redundancy and a transmission that can run dry for 30 minutes. It is described as the most versatile multi-role platform capable of adapting to challenges.
This document contains the text from a Federal Aviation Administration workshop on risk management for flight instructors. It discusses topics like defining risk, hazard, and risk assessment. It provides examples of accidents and the probable causes being related to pilot decision making. It emphasizes the importance of teaching pilots to identify risks, evaluate hazards, and make informed decisions using risk management processes and checklists. The document also contains several scenarios to help stimulate decision making skills in trainees.
F 35 a lightning ii, usa - joint strike fighter aircrafthindujudaic
The document summarizes the F-35A Lightning II, the conventional take-off and landing variant of the F-35 Joint Strike Fighter aircraft. It is a single-seat, single-engine stealth fighter being developed by Lockheed Martin for the US Air Force and allies. It is designed for multi-role missions including air defense, ground attack, and reconnaissance, and will replace F-16s and A-10s. Key features include its AESA radar, DAS missile warning system, internal gun, and ability to carry up to 8,100kg of weapons internally and 6,800kg externally.
This document outlines the course details and topics for a 18-week rotorcraft systems, maintenance, and role equipment class at the Malaysian Institute of Aviation Technology. The course will cover 10 topics related to helicopter structure and maintenance, and will evaluate students based on assignments, quizzes, and a final exam. Students who miss more than 10% of classes will be barred from the final exam. The document then provides details on helicopter structural design, including tubular, stressed skin, and bonded construction methods, as well as the stresses and loads placed on helicopter structures.
The document provides information on the F-35 Lightning II strike fighter program, including its vision, mission statement, and key attributes and capabilities. It describes the three variants - Conventional Take-Off and Landing (CTOL), Carrier Variant (CV), and Short Take-Off and Vertical Landing (STOVL) - and notes their commonality. It outlines requirements from the US and international partners and discusses how the F-35 enables true joint and coalition operations.
The document provides an overview of aircraft structures and their key components. It discusses the fuselage, wings, empennage, landing gear, and powerplants. For each component, it describes the basic design and functions. It also covers important aircraft structural concepts like stressed skin construction, monocoque vs semi-monocoque design, and choices of lightweight metal materials. Overall the document serves as a high-level introduction to aircraft structures and the major structural components of airplanes.
This document discusses the importance of air dominance for the US military and argues that procuring 381 F-22 Raptors and 1,763 F-35 Lightning IIs is the required course of action. It notes that threats to air dominance are increasing as competitors develop new fighters and air defense systems. Maintaining aging US fighter fleets has high costs and risks. The F-22 and F-35 are presented as complementary systems needed to ensure air superiority and support ground forces against evolving threats now and in the future.
This document provides training material on helicopter structures for the Malaysian Institute of Aviation Technology. It discusses the firewall and landing gear systems. The firewall functions to contain fires and protect the airframe and pipelines. Modern firewalls are made of titanium or composite honeycomb materials. Skid type landing gear is simpler but restricts aircraft movement compared to wheel type gear used on larger helicopters. The document describes constructing, installing, and maintaining firewalls and skid landing gear.
Lockheed Martin F35 Lightning II(Aerodynamics Presentation)SYEDMOEEDHUSSAIN1
Note: For best experience of animation, Proceed in Slide Show Mode Of MS Power Point
Lockheed Martin F35 Lightning II's
1. Brief History
2. Dimensions
3. Concept of Shockwave
4. Drag Coefficient
5. Reynold’s Number
6. Features
7. Capabilities
This document discusses various concepts related to aircraft structural design and airworthiness requirements. It describes how aircraft structure is divided into primary, secondary, and tertiary categories based on their importance. Primary structure, if failed, could cause loss of control or structural collapse. Examples provided stress the importance of withstanding forces like tension, compression, shear, bending, and torsion to ensure structural integrity and safety. Station identification systems are also covered to precisely locate structural components through methods like station numbering and zoning.
The document discusses the evolution of US fighter aircraft generations and the capabilities of 5th generation fighters. It highlights that the F-22 and F-35 each have complementary and optimized roles, with the F-22 focused on air superiority due to its speed, maneuverability and larger internal weapons capacity, and the F-35 focused on global precision attack thanks to its sensors and increased weapons payload. Maintaining a mix of both fighters is presented as critical to addressing 21st century air threats.
The document provides an overview of various naval aircraft, missiles, and weapons systems used by the US Navy. It describes the main categories of aircraft as fixed-wing, rotary-wing, and lighter-than-air. It then discusses different types of naval aircraft like attack planes, fighter planes, patrol aircraft, electronic warfare aircraft, and reconnaissance aircraft. The document also summarizes naval missiles from guided missiles to ballistic missiles and cruise missiles. It concludes with a brief overview of naval torpedoes and underwater warfare systems.
The document defines preventive maintenance and outlines who is authorized to perform it according to FAA regulations. It specifies that holders of pilot certificates can perform preventive maintenance on aircraft they own or operate, including private pilots. The document lists the specific preventive maintenance tasks allowed by FAA regulations and provides guidance on maintenance records, required performance standards, and additional FAA resources.
This document discusses Lockheed Martin's focus on affordability for the F-35 Lightning II fighter jet program. It summarizes the three main variants of the F-35—the F-35A conventional takeoff and landing variant, the F-35B short takeoff and vertical landing variant, and the F-35C carrier-based catapult takeoff variant. It also outlines Lockheed Martin's goals of achieving economies of scale through design commonality across variants, implementing new lean manufacturing processes to reduce costs over time, and engaging international partners in the production process.
BVR combat was, for a long time, dream of both Western and Asian air forces. Today, it seems that the dream has been finally fulfilled; but is that really so?
Blended Wing Body (BWB) - Future Of AviationAsim Ghatak
What Is Blended Wing Body, History of BWB, How Airplanes Fly, Aircraft Control Surfaces, Design and Structure of BWB, Advantages and Disadvantages, Conventional aircraft vs. BWB, Future Scope and Challenges
MiG-21 US/UM Flight Manual with W&B Manualmishanbgd
This email contains a long string of repetitive characters with no meaningful information. It appears to be spam or some type of automated message without any discernible purpose or message to summarize.
This is an email address for Marina Biblija. The email address is marina.biblija@gmail.com and it appears to belong to an individual named Marina Biblija.
Leonardo AW101 NAWSARH - The superior solutionsLeonardo
The AW101 helicopter is a multi-role maritime and utility platform that can fulfill various operational requirements such as tactical transport, search and rescue, special forces operations, and maritime operations. It has a proven heritage of over 388,000 flight hours conducting missions worldwide. The AW101 provides class-leading performance with benefits such as a large and flexible cabin, long range and endurance, low vibration and noise levels, and inherent safety features like triple redundancy and a transmission that can run dry for 30 minutes. It is described as the most versatile multi-role platform capable of adapting to challenges.
This document contains the text from a Federal Aviation Administration workshop on risk management for flight instructors. It discusses topics like defining risk, hazard, and risk assessment. It provides examples of accidents and the probable causes being related to pilot decision making. It emphasizes the importance of teaching pilots to identify risks, evaluate hazards, and make informed decisions using risk management processes and checklists. The document also contains several scenarios to help stimulate decision making skills in trainees.
F 35 a lightning ii, usa - joint strike fighter aircrafthindujudaic
The document summarizes the F-35A Lightning II, the conventional take-off and landing variant of the F-35 Joint Strike Fighter aircraft. It is a single-seat, single-engine stealth fighter being developed by Lockheed Martin for the US Air Force and allies. It is designed for multi-role missions including air defense, ground attack, and reconnaissance, and will replace F-16s and A-10s. Key features include its AESA radar, DAS missile warning system, internal gun, and ability to carry up to 8,100kg of weapons internally and 6,800kg externally.
This document outlines the course details and topics for a 18-week rotorcraft systems, maintenance, and role equipment class at the Malaysian Institute of Aviation Technology. The course will cover 10 topics related to helicopter structure and maintenance, and will evaluate students based on assignments, quizzes, and a final exam. Students who miss more than 10% of classes will be barred from the final exam. The document then provides details on helicopter structural design, including tubular, stressed skin, and bonded construction methods, as well as the stresses and loads placed on helicopter structures.
The document provides information on the F-35 Lightning II strike fighter program, including its vision, mission statement, and key attributes and capabilities. It describes the three variants - Conventional Take-Off and Landing (CTOL), Carrier Variant (CV), and Short Take-Off and Vertical Landing (STOVL) - and notes their commonality. It outlines requirements from the US and international partners and discusses how the F-35 enables true joint and coalition operations.
The document provides an overview of aircraft structures and their key components. It discusses the fuselage, wings, empennage, landing gear, and powerplants. For each component, it describes the basic design and functions. It also covers important aircraft structural concepts like stressed skin construction, monocoque vs semi-monocoque design, and choices of lightweight metal materials. Overall the document serves as a high-level introduction to aircraft structures and the major structural components of airplanes.
This document discusses the importance of air dominance for the US military and argues that procuring 381 F-22 Raptors and 1,763 F-35 Lightning IIs is the required course of action. It notes that threats to air dominance are increasing as competitors develop new fighters and air defense systems. Maintaining aging US fighter fleets has high costs and risks. The F-22 and F-35 are presented as complementary systems needed to ensure air superiority and support ground forces against evolving threats now and in the future.
This document provides training material on helicopter structures for the Malaysian Institute of Aviation Technology. It discusses the firewall and landing gear systems. The firewall functions to contain fires and protect the airframe and pipelines. Modern firewalls are made of titanium or composite honeycomb materials. Skid type landing gear is simpler but restricts aircraft movement compared to wheel type gear used on larger helicopters. The document describes constructing, installing, and maintaining firewalls and skid landing gear.
Lockheed Martin F35 Lightning II(Aerodynamics Presentation)SYEDMOEEDHUSSAIN1
Note: For best experience of animation, Proceed in Slide Show Mode Of MS Power Point
Lockheed Martin F35 Lightning II's
1. Brief History
2. Dimensions
3. Concept of Shockwave
4. Drag Coefficient
5. Reynold’s Number
6. Features
7. Capabilities
This document discusses various concepts related to aircraft structural design and airworthiness requirements. It describes how aircraft structure is divided into primary, secondary, and tertiary categories based on their importance. Primary structure, if failed, could cause loss of control or structural collapse. Examples provided stress the importance of withstanding forces like tension, compression, shear, bending, and torsion to ensure structural integrity and safety. Station identification systems are also covered to precisely locate structural components through methods like station numbering and zoning.
The document discusses the evolution of US fighter aircraft generations and the capabilities of 5th generation fighters. It highlights that the F-22 and F-35 each have complementary and optimized roles, with the F-22 focused on air superiority due to its speed, maneuverability and larger internal weapons capacity, and the F-35 focused on global precision attack thanks to its sensors and increased weapons payload. Maintaining a mix of both fighters is presented as critical to addressing 21st century air threats.
The document provides an overview of various naval aircraft, missiles, and weapons systems used by the US Navy. It describes the main categories of aircraft as fixed-wing, rotary-wing, and lighter-than-air. It then discusses different types of naval aircraft like attack planes, fighter planes, patrol aircraft, electronic warfare aircraft, and reconnaissance aircraft. The document also summarizes naval missiles from guided missiles to ballistic missiles and cruise missiles. It concludes with a brief overview of naval torpedoes and underwater warfare systems.
The document defines preventive maintenance and outlines who is authorized to perform it according to FAA regulations. It specifies that holders of pilot certificates can perform preventive maintenance on aircraft they own or operate, including private pilots. The document lists the specific preventive maintenance tasks allowed by FAA regulations and provides guidance on maintenance records, required performance standards, and additional FAA resources.
This document discusses Lockheed Martin's focus on affordability for the F-35 Lightning II fighter jet program. It summarizes the three main variants of the F-35—the F-35A conventional takeoff and landing variant, the F-35B short takeoff and vertical landing variant, and the F-35C carrier-based catapult takeoff variant. It also outlines Lockheed Martin's goals of achieving economies of scale through design commonality across variants, implementing new lean manufacturing processes to reduce costs over time, and engaging international partners in the production process.
BVR combat was, for a long time, dream of both Western and Asian air forces. Today, it seems that the dream has been finally fulfilled; but is that really so?
Blended Wing Body (BWB) - Future Of AviationAsim Ghatak
What Is Blended Wing Body, History of BWB, How Airplanes Fly, Aircraft Control Surfaces, Design and Structure of BWB, Advantages and Disadvantages, Conventional aircraft vs. BWB, Future Scope and Challenges
MiG-21 US/UM Flight Manual with W&B Manualmishanbgd
This email contains a long string of repetitive characters with no meaningful information. It appears to be spam or some type of automated message without any discernible purpose or message to summarize.
This is an email address for Marina Biblija. The email address is marina.biblija@gmail.com and it appears to belong to an individual named Marina Biblija.
This document contains 11 image links of Russian-made MiG-29 Fulcrum fighter jets from the Indian Air Force. The images show MiG-29s in flight, on the ground, and close-up shots. They provide various angles and views of the multi-role fighter aircraft type.
The document discusses the MiG-29 Fulcrum fighter jet. It provides details on production numbers and variants produced. It discusses upgrades to the MiG-29K variant for carrier operations including for the Indian Navy. It also notes potential future orders from Russia and India that could continue production of the MiG-29K.
10 fighter aircraft avionics - part iiiSolo Hermelin
This document provides a summary of fighter aircraft avionics across different generations of fighter jets. It discusses the avionics systems of third, fourth, 4.5 and fifth generation fighters. Specific avionics components covered include cockpit displays, communication systems, data entry/control, flight control, navigation, sensors and weapons systems. The document also discusses topics related to aircraft performance, flight instruments, propulsion and aerodynamics as they relate to fighter jet avionics.
The document is a table of contents for a publication about cutaway diagrams of modern aircraft from around the world. It lists over 130 aircraft from countries like the US, USSR/Russia, UK, France, Sweden, China, Iran, and Israel. The table of contents is divided into sections for different manufacturers and countries. It provides brief 1-2 word descriptions of aircraft like the F-14, F-16, Mirage 2000, MiG-21, and Su-27.
The document discusses various braking mechanisms used in aircraft, including multi-disc brakes, carbon brakes, thrust reversers, drag parachutes, air brakes, and tail hooks. It provides diagrams and photos showing the components and operation of aircraft brakes, thrust reversers, drag devices, and related systems.
The Indian Air Force document provides information on the history, structure, and missions of the Indian Air Force (IAF). It details that the IAF was established in 1932 as an auxiliary air force of the British Empire in India. After independence in 1947, it became the air force of the Republic of India. The IAF plays an important role in defending Indian airspace and providing air support to the Indian Army. It has been involved in several wars with Pakistan and one with China. The IAF is led by the Chief of Air Staff and has around 170,000 personnel and over 1,300 aircraft as of 2010-2011.
The Indian Air Force was established in 1932 under British rule as the Royal Indian Air Force. After India gained independence, it was renamed the Indian Air Force in 1950. Its motto is "Touch the Sky with Glory". The IAF has been involved in several wars and operations with neighboring Pakistan and has also participated in UN peacekeeping missions. It has a hierarchical structure led by the Air Chief Marshal and has a strength of over 1,300 aircraft across 34 squadrons. The IAF's main roles are fighter and attacker aircraft like the Sukhoi 30-MKI, Mirage 2000, and Jaguar that allow it to conduct air-to-air and air-to-surface missions.
The document summarizes five common wing planforms - rectangular, elliptical, tapered, swept, and delta wings. It provides examples of aircraft that use each type of wing and notes their aerodynamic efficiencies and manufacturing complexities. Additional wing variations discussed include trapezoidal, ogive, swept back, swept forward, and variable sweep wings.
Fixed wing Aircraft and area of their application.pptxEliyasZekaryas
The document discusses different types of fixed-wing aircraft and their applications. It begins by defining fixed-wing aircraft and their history, including the Wright Brothers' first flight. It then describes various wing configurations like monoplanes, biplanes, and triplanes. Next, it covers common fixed-wing aircraft characteristics and differentiates applications like commercial airliners, military craft, general aviation, business jets, and more specialized aircraft. In closing, it notes some classifications may overlap depending on an aircraft's capabilities and design features.
Four Factors That Make the A-10 Thunderbolt II Hard to ReplaceLee Cloer
Efficience, Armament, Protection, Camouflage - 4 factors that make the A-10 Thunderbolt, AKA Warthog, hard to replace
http://duotechservices.com/news-and-events/general-interest/four-factors-that-make-the-a-10-thunderbolt-ii-hard-to-replace
This document provides information about T-tail aircraft configurations. It defines a T-tail as having horizontal control surfaces mounted to the top of the vertical stabilizer, resembling the letter T. T-tails are common on gliders and airliners with rear-mounted engines. Advantages include smoother airflow and better pitch control. Disadvantages include potential susceptibility to deep stalls and reduced low-speed control for some aircraft. Examples of planes using T-tails are listed.
The document describes using aircraft modelling software to simulate a plane crash accident involving a Piper PA-31-325 Navajo. The objectives were to model the roll, pitch, yaw and flight path resulting from detachment of the left wing. The software was used to build an aerodynamic model of the Navajo using collected geometry and performance data. Tests were run detaching the wing and applying detachment forces to match investigator findings and evaluate pilot experience. The model supported and supplemented the accident evidence.
The document analyzes the aerodynamic design and purpose of 5 aircraft: the B-2 bomber, Concorde airliner, Antonov An-225 cargo plane, Su-47 fighter jet, and Focke-Wulf Triebflügel interceptor. The B-2 uses a flying wing design for high lift efficiency. The Concorde's delta wing and slim fuselage allow for supersonic flight. The An-225 has a large wing area and 6 engines for heavy cargo loads. The Su-47 has forward-swept wings for increased maneuverability. The Focke-Wulf uses adjustable rotor blades and tailplanes for vertical take-off and landing as an interceptor
As the proficiency of Syria’s armed opposition has increased, the Assad regime has been forced to rely on more of its arsenal to combat the opposition.
171705017 appendix-14-mi g-21-airworthiness-certificationwaqas ahmed
This document provides background information on the Mikoyan-Gurevich MiG-21 aircraft. The MiG-21 was a supersonic jet fighter that served as the mainstay of Soviet fighter aviation from the 1960s-1970s. Over 10,000 MiG-21s were produced and it was exported to over 50 countries. While early versions were considered first and second generation jets, later versions were third and fourth generation. The MiG-21 had short range but was capable of Mach 2 speed. It continues to serve in many air forces globally despite being replaced by newer fighters in the Soviet Union in the 1970s-1980s.
The document describes the design and construction of a tri-craft unmanned aerial vehicle (UAV) with vertical take-off and landing capabilities. It includes the history of UAVs and vertical take-off aircraft, the initial and updated project schedules, drawings of the tri-craft design, calculations for components, construction steps, and recommendations. The tri-craft UAV is designed to have three motors, with the front two capable of 90 degree rotation to enable both vertical and horizontal flight.
Fighter jet Swept back wing design and Analysis by using of Xflr5Mani5436
This document summarizes the wing design of a proposed fighter jet. It describes the selection of the wing geometry, including the wing area, aspect ratio, chords, and sweep, dihedral, and twist angles. It also discusses the selection of two airfoil profiles and calculates the aerodynamic characteristics of the wing. Additionally, it describes the selection of a mid-mounted wing configuration and sizes the horizontal and vertical tails. The landing gear system and performance parameters are also analyzed and justified.
The document summarizes the history and development of gyro gunsights used in aircraft from World War 2 through the Cold War. Gyro gunsights automatically calculated the lead angle and bullet drop needed for a pilot to hit a moving target. The first operational gyro gunsight was the British Mark I in 1941. Improved models like the Mark II saw widespread use through the end of WWII. Germany developed the EZ 42 gyro sight but it did not see full deployment. The US developed the AN/ASG-26 for the F-4 Phantom, which provided targeting information via a head-up display.
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Prepare a presentation or a paper using research, basic comparative analysis, data organization and application of economic information. You will make an informed assessment of an economic climate outside of the United States to accomplish an entertainment industry objective.
Mig-21and fighter maneuverability in today's terms
1. MiG-21 and Fighter Maneuverability in
Today's Terms
Predrag Pavlovic, dipl.ing. and Nenad Pavlovic, dipl.ing, JAT Airways
Maneuverability of modern fighter is measured by how slow it can fly and how high
angle of attack it can sustain and still turn. During some war situations, US evaluation
and Aggressor use, MiG-21 has shown it can keep pace with modern planes in this
area. Aircraft manufacturer at one time considered this irrelevant and imposed
restrictions on angle of attack. Flying above allowed 28-33 degrees local angle of
attack at low speeds makes possible to relatively safely achieve a maneuverability once
considered privilege of modern fighters.
Couple years ago reports and testimonies appeared in the media about a dogfight during
the Israeli-Arab War '73. when the Egyptian MiG-21 pilot managed to do a Split-S
maneuver at the start altitude of 3000 feet, less than half minimum airspace the manual
says (about 6750 ft). Appropriate simulation can be found on the internet:
http://www.youtube.com/watch?v=bQMzK2WfYYM&feature=player_embedded
1
2. Figure 1.
Initiated by this event, some American and Israeli enthusiasts (once pilots of their AF
fighters), one of which has a private squadron of various Russian fighters, attempted to
replicate that minimum altitude needed to complete Split-S figure in the two-seater MiG-
21. Previous consultation with Israeli ace, who participated in that dogfight in '73. war,
did not help test to be successful. Attempts were carried out at the higher altitude (5 km)
and the height loss during the figure was in accordance with flight manual. It remained
unclear whether ’73 event was result of "special skills or superhuman strength of the
Egyptian pilot needed to withstand the required g-loads”.
Recently disclosed files of the official MiG-21 evaluation in the U.S. revealed some
unexpected capabilities that can be correlated with the "inexplicable" ’73. maneuver.
MiGs were brought to America via Israel, in the late '60s as a result of pilot error or fled
from Iraq and Algeria. Later they were bought from Indonesia. The MiG-21 in the U.S.
Air Force is designated YF-110.
The report of a MiG-21F shows nothing particularly unusual, except for maneuvering
capabilities and behavior/handling at low speeds described as "class above competition”.
Besides that, if competitors tried to follow MiG-21F at high alpha, their engine
experienced shutdown or compressor stall. MiG could perform "hammerhead" turn (wing
over/stall turn/renversement) at 100 knots (knot = 1.852 km/h), figure where at the end of
the vertical climb pilot add rudder (with the opposite aileron and forward stick) to push
the plane in the dive. Rudder is effective from 30 knots. With the stick fully backward,
the plane flies at 210 km/h, the rolling oscillations are present, but there is no lift
breakdown or the tendency towards spin. If during the evaluation, loss of control due to
2
3. uncoordinated controls occurred, it was in the form of roll-off (usually for 180°) instead
of much more dangerous yaw-off. To put the plane back under control it was necessary
only to release controls. MiG-21 proved to be docile, safer to fly than MIG-17. During
the hundred flight tests engine compressor stall was never experienced.
U.S. of course, used MiGs in dogfight evaluation against their aircraft. Latter, they
formed "Aggressor" squadron of MiGs and other fighters for the dogfight simulation with
regular American aircraft.
Figure 2, 3. MiG-21 on testing in the U.S.
3
4. During MiG testing, it was clear that U.S. pilots have not relied on Soviet pilot’s manuals
or they did not have one at the beginning. That is why the aircraft ability was fully
exploited. Test pilots had thousands of flight hours experience on dozens of types of
aircraft. Those who have survived the testing of U.S. supersonic fighters
F-100/101/104/4 (many of planes were called "widow makers"), learned to recognize the
pre-stall/spin signs and use rudder for rolling the aircraft at higher angles of attack.
Figure 4. Some of the results of MiG-21 testing in the United States
4
5. Reportedly, if Vietnamese pilots had adequate training, the U.S. fighter shot-down ratio
figures would be much worse in that war. In the hands of the well trained pilots, MiG
would always outmaneuvered Phantom. US unveils graphs depicting not only far better
instantaneous turn performance of Fishbed C compared to F-4D but also better sustained
maneuverability. MiG-21 Aggressor pilots respected only the most modern fighters
because they do not lose so much speed in turn even at low speeds. However, appearance
of all-aspect infrared missiles reduced the importance of sustained turns (M2000, F-18E,
Gripen …are not brilliant in the maintaining speed in turn). If MiG-21 had R-73 missile,
it could easily take advantage of first shoot opportunity at close range against any new
fighter.
The F-5E, fighter which does not fly above Mach 1.5, MiG-21 simulator, reportedly has
shade better subsonic sustained turn maneuverability, but inferior controllability at low
speeds. Maneuverability is the ability to change speed and direction of flight path
(velocity vector pointing) and controllability - ability of change aircraft attitude
(pitch/roll/yaw - nose pointing) and thrust (engine response - spool up time matters).
When the aircraft initial flight path in dogfight is anti-parallel flyby, combat will
inevitably develop so that someone goes in a climb with rolling scissors - turn reversals
along the opponent’s flight path to remain behind the opponent. If the F-5E does not gain
an advantage before the speed drops below 200 knots, MiG will start winning. First look
at the configuration of the aircraft, MiG – delta with the sweep near 60°, and Tiger with
nearly straight wings, would suggest the opposite, that MiG is in trouble at low speed.
Even the mighty F-15 Eagle had no solution in dogfight below 150-250 knots against
MiG-21 in US Aggressor hands. At the beginning of dogfight, at the speed of 400-500
knots MiG-21 will turn at max g loosing 70 knots per second, ending at the speed of 70
knots in less than 90º of turn (deceleration of 3.5 g, more intensive than Harrier’s VIFF
turn). Reportedly, no other aircraft can do that. This way MiG will remain behind every
opponent still having sufficient controllability for gun tracking using rudder rolls.
Opponents would think that at this speed MiG can only bring down the nose and dive, but
the MiG at less than 100 knots has sufficient pitch authority to raise the nose at enemy. If
F-15 tries to follow, ’21 should execute 'barrel-roll ' to remain behind the Eagle.
It is obvious that MiG-21 'Aggressor' pilots pulled full aft stick in turn regardless of the
lateral oscillations, roll-off and temporary loss of control.
5
7. Latter, the F-15 pilots learned (in a hard way) not to accept maneuvering at slow speeds,
not to allow to be drown into a series of turn reversals, but to withdraw and re-attack at
higher speeds using 3D turns and it’s higher thrust/weight ratio. F-15 with 45º swept
wing and low horizontal tail, at higher angle of attack becomes longitudinally
superstable, so it can not achieve more than about 30º angle of attack.
On the example of lift and stability of the aircraft with the 45º swept wing and high-set
horizontal tail it can be seen that the lift begins to decline at 10º (buffeting starts), the
wings are stalled at the 20º (the airflow separates from the wing), and max body lift is at
35-40º after which it decreases. Delta wing of MiG-21 with sweep of 57 º retains stable
airflow to very high angles of attack.
Longitudinal stability is positive where the curve has a downward slope. In this case, the
position of the horizontal tail is causing longitudinal instability at 15º, and at 35-40º angle
of attack aircraft is trimmed without tail deflection. MiG-21 has no problem with
longitudinal stability (except with air to ground armament with low fuel) and the plane in
the example would have a limit at 15º angle of attack.
Yaw stability curve shows that the aircraft is unstable at 15º, what is not uncommon.
Few modern fighters are stable at over 20º, but it is not a problem if the aircraft maintains
lateral stability i.e. roll due to yaw. Roll stability curve is increasing as the lift increase,
so it similarly comes to the instability, in this case at about 20º angle of attack. Shall the
plane have a tendency toward spin (at no deflection of the control surfaces!) show the
curve of dynamic directional stability where factors are static yaw and roll stability along
the inertial characteristics of the aircraft. In this example, the plane is at stall just above
20º angle of attack, while MiG-21 is stable at well over 30º at low Mach numbers.
Curves correspond to a particular Mach number, at some other speed they can vary
significantly.
7
9. Soviet training was based on a relatively small number of flight hours on a MiG, which is
used for training the primary purpose of aircraft, interception of fighters-bombers, under
ground control. Pilots are not encouraged to explore the flight envelope. The aircraft is
designed to fly faster and higher. Slow speeds were irrelevant, except for landing. In the
first combat manuals, the performance at altitudes only above 5 km were presented.
Later, it turned out that there are many practical constraints due to which the projected
max altitudes and speeds are rarely used.
MiG-21 wing has no camber or twist along span. The relative thickness of the higher end
of the wing than in the root. There are few prestall signs. Prestall buffet begins much
earlier (at 50-100 km/h higher speed), its intensity is light and slightly decreases at higher
α. Below Mach 0.4 buffet does not develop. Just before stall α, aircraft nose would start
wandering accompanied by more noticeable wing rocking (roll oscillations that intensify
thru the stall), symptoms of dynamic directional instability.
Stalling proceeds more vigorously with fewer signs at higher subsonic speeds.
Ailerons are ineffective in countering roll oscillations and rudder would push aircraft into
a spin. Setting control surfaces to the neutral position immediately after the onset of stall
would restore normal flight conditions. The aircraft is longitudinally stable in air combat
configuration at any internal fuel quantity.
Aircraft’s stall speed (speed at which dynamic directional stability breakdown occurs) is
function of Mach number, because directional and lateral static stability usually decreases
with speed. Stall angle of attack decreases from above 30º (far beyond indicated α) at
Mach 0.2 to 20º (i.e. 33 units local angle of attack on indicator) at Mach 0.95.
In those days when MiG-21 was designed, electronic flight controls to limit the angle of
attack in function of Mach number didn’t exist. A fighter was built primarily for high
speeds, high altitude interceptions. At slower speeds previous generations MiG-19/17
were better.
Designers put the angle of attack indicator, calibrated in local angle of attack, to warn the
pilot of approaching stall limit. At recommended and allowed limit 28 units (about 17º
true angle of attack) safety margin to stall is from 13º at Mach 0.2 to 3º at Mach 0.95.
So there is large margin between allowed angle of attack and stall angles of attack
especially at lower Mach numbers.
At higher speeds, the angle of attack is limited by tail pitching power.
9
10. Mach number 0.2 0.7 0.8 0.95
Stall angle of attack (α) > 30º ~ 25º ~ 23º ~ 20º
Stall speed
233 km/h 254 km/h 260 km/h 267 km/h
weight = 7500 kg
Speed at 33 units local α 267 km/h
287 km/h 287 km/h 282 km/h
(~20º α ) (stall)
Speed at 28 units local α
311 km/h 311 km/h 305 km/h 291 km/h
(~17º α )
So, the low speed turning capabilities were not fully exploited. If situation comes, like it
happened to that Egyptian pilot during war, there is an additional lift potential.
During the Split-S figure, speed should not be increased. The closer to stall α is, the lesser
the altitude loss is during figure. Below 600 km/h CAS entry speed aircraft cannot
aerodynamically reach the allowed structural load factor so there is no need for
superhuman physical stress. At higher speeds height loss in split-S at stall angle of attack
is much more than 3000 ft.
10
14. Because of its very high stall angle of attack at lower Mach numbers and good pitch
control authority (large wing leading edge sweep produces strong vortical flow which
shifts aerodynamic centre forward at high alpha, reducing stability thus allowing the tail
to easily trim aircraft at more than 30° alpha), aircraft has a great point and shoot
potential with modern IR missiles.
Although it is often said that the MiG-21 looses a lot of energy in turn, the truth is also
that it has better sustained turn performance than most aircraft of its generation.
Tumansky engine proved almost stall/surge free at speeds far below minimums quoted in
conservative Soviet flight manuals. All U.S. and European contemporary designs flamed
out under same conditions. Engine has two shafts for optimized - different rotational
speeds of low and high pressure compressors stages for a compressor blade stall
resistance, feature that allows more compressors stages to be added for lowering specific
fuel consumption. But it has unusually low number of compressor stages for a two-shaft
design, contributing to reliability. Bad side of this philosophy is higher fuel consumption.
Despite the resistance of the compressor to the extreme conditions of airflow at the inlet,
if afterburner is engaged at almost zero speed (well below the conservative engine
envelope) other undesirable phenomena are possible. Distortions of the inlet airflow
causes disruption of relations of air and fuel in the AB chamber, which changes the speed
of combustion. Pressure fluctuations coupled to acoustic velocity fluctuation (AB
chamber is also exposed to sound fatigue, the noise is up to 180 decibels) associated with
combustion instability (called rumbling), can cause extreme resonant structural vibrations
of the engine with subsequent engine destruction and the loss of the aircraft.
The published results of American evaluation relates to the F/PF models. BIS model has
15-20% higher ratio of inertia moments in yaw to roll. It certainly results in more sideslip
during rolls and somewhat lower stall angle of attack, angle when breakdown of dynamic
directional stability occurs. But the prevailing factor in this equation is the dihedral effect
i.e. roll stability and it is the same in all models because it depends on airflow around the
delta wing, so it can be expected good behavior of BIS model at low speeds also.
It should be borne in mind that prevailing effects at high angles of attack are dihedral and
adverse yaw due to aileron deflection. Rudder is used for rolling and if the sideslip angle
or yaw rate (induced in this way) crosses critical, result is the spin. Opposite aileron
increases the roll rate through an additional sideslip angle i.e. 'adverse yaw'. In most
modern aircraft application of such cross controls for 5-15 seconds, usually causes spin.
14
15. Figure 10. MiG-21 derivatives J-7G and JL-9
In general, the plane that has a lower stall speed is more maneuverable. At some speed, it
will be able to achieve g-load equal to the square of the mentioned speeds quotient. The
U.S. experience from simulated dogfights during exercises indicates the importance of
the minimum speed and controllability at high angles of attack. That is why F-18 gets F-
15/16 although its performances are considerably lower. Latest F-18E has still weaker
performance, but better controllability. Angle of attack, at low speeds, of the F-16 and
15
16. Gripen is limited to about 26º (Rafale and the Typhoon to a shade more). F-15 has max
trimmed angle of attack 30-33º with poor roll response here. Against 'stealth' fighters F-
22/35 and corresponding new Russian (whose all planform contour lines are parallel to a
few main sweep angles - cm wavelength radar return angles, in addition to other 'stealth'
measures and cost of 50 MiG-21), none of the listed has significant chances at medium
range. Analysts agree that the close combat will remain inevitable, and that each aircraft
armed with missiles cued by helmet sight has a chance, especially if it can reach high
angles of attack. Even stealth fighters do not destroy opponents with death rays. Every
component of the fire control/weapon system chain has limitations, from fighter radar to
missile fuze. Towed mini decoy (laterally separated) with monopulse deception
jammer/repeater or just simple towed corner reflector can draw away radar return signal
centroid from towing aircraft. It could help surviving medium range combat even against
stealth fighters.
The main disadvantages of MiG-21 are poor cockpit downward visibility, a
proportionally small (but inline to generation) wingspan i.e. large induced drag
(afterburner is needed for level flight at the absolute minimum speed, as at max allowed
Mach number) and relatively slow response of two-shaft engine. All this causes poor
performance on landing, especially in the case of go-around. Small fighter size means
limited mission equipment carriage capacity.
It turns out that only important is to have a reliable and economical aircraft, a platform
for carrying payload, with attack speed in the Mach 1.5+ class (that’s why a much
younger, slower attack aircrafts are withdrawn prematurely). The modern nav-attack
equipment (simplified inertial system, GPS, displays…) is now relatively inexpensive to
install even in a small propeller planes. MiG-21 operators missed opportunity to realize
fact that with helmet cued, large acquisition angle R-73 missile that was available
upgrade, MiG could achieve 50:1 kill ratio in dogfight against F-18/Gripen/Typhoon
class fighters just because latter were 10-15 years late with similar weapon system.
Instead of making best of it, MiG-21 operators opted to admire newer fighters.
Because of its good characteristics, even 50 years after MiG-21 became operational,
some of its modifications are still in production in Asia.
Reference:
- Fighter Performance in Practice, Phantom versus MiG-21, Predrag and Nenad Pavlović,
http://books.google.com/books/about/FIGHTER_PERFORMANCE_IN_PRACTICE_Ph
antom.html?id=vjUcnGdH10wC&redir_esc=y
- Test and Evaluation Squadron, Nellis Air Force Base, Interviews;
16