In the current globalization, we can see many innovations being introduced or implemented in every aspect of field that are considered to be existed. Every country is aiming to develop its power over all the aspects that considered for comparison with other countries in order to stand at same level of competition with others. One such power considered by all countries to develop every possible way to have a healthy competition is the military power which involves basically innovations of fast moving aircraft having a high lift coefficient and low drag coefficient. Such an aircraft having the high lift and low drag coefficient is TEJAS (HAL) developed by country India on which the purpose of paper mainly sustains. The paper mainly focuses on steady-state flow analysis over aircraft TEJAS using the computer aided modelling techniques and also the comparison of the results obtained from the modelled techniques. The paper also outlines the designing of the structural model of the TEJAS in a modelling software, creation of a finite computational domain, segmentation of this domain into discrete intervals, applying boundary conditions such as velocity in order to obtain plots and desired results determining the coefficient of pressure, lift and drag coefficient, velocity magnitude etc. This paper also aims in creating awareness to the future students about the techniques involved and knowledge required for developing a designed modelled. This paper also highlights the use of CFD techniques involved for the purpose of fluid flow simulation of the aircraft especially performing the meshing techniques, pre and post processing techniques and finally the evaluation of the simulation. Finally this paper can be seen as source by future generation students in gaining knowledge about design, analysis and simulation of the structured model on various conditions, about the field of aerospace engineering and new innovations being developed and also about the career involved when the above fields were chosen foe specialization purposes
This document provides an overview of a project report on the aerodynamics analysis of automobiles. The report was submitted by G. Srikar in partial fulfillment of the requirements for a Bachelor of Technology degree. The report includes declarations, certificates of approval, acknowledgments, and outlines the objectives, scope, and methodology of analyzing the effects of adding aerodynamic components like diffusers, vortex generators, spoilers, tire covers, and air ducts on a vehicle model using computational fluid dynamics software. The goals are to estimate the percent reductions in drag coefficient and lift coefficient, and to improve vehicle fuel efficiency, acceleration, and handling.
Cfd analysis of car body aerodynamics including effect of passive flow device...eSAT Journals
Abstract With the emphasis lying on increasing fuel efficiency of vehicles in order to combat rising fuel prices and environmental
challenges the manufacturers are thinking beyond the conventional vehicle systems by focusing on its aerodynamics. Aerodynamic
drag exceeds 50 per cent of the total resistance to motion at speeds above 70km/hr, and above 100 km/hr it is the most important
factor. The review is done to identify the various shortcomings of the automotive designers when it is in regards to flow
separation of air at the rear of the vehicle which causes most of the losses. This paper focuses on the work already done in the
field of aerodynamics starting with Ahmed Body. It is a bluff body with adjustable rear slant angle and the basis upon which the
aerodynamicists test their models. And then, moving onto passive aerodynamic enhancements for automobiles like vortex
generators and diffusers whose various dimensional modulations were discussed with several steps leading to its advancement in
vehicle body design. This brings to the simulation, Computational Fluid Dynamics (CFD) and its role in this analysis was
covered. CFD has been modified a lot from the beginning to increase the accuracy of its predictions. So the paper lists various
simulation techniques studied by the previous researchers in order to understand the wake region behind the car which has been
notoriously difficult to predict till date. Several aspects of aerodynamic drag that need further analysis to improve the
aerodynamic were highlighted.
Keywords: Drag Force, Drag Coefficient, Ahmed Body, CFD Simulation, Vehicle Aerodynamics, Passive Flow
Devices
Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehicle (UAV)Designage Solutions
Next part of "A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehicle (UAV)" with case studies.
Find previous presentation here- http://www.slideshare.net/HarshadaGurav/a-review-of-flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
Design and Enhancement of Rear Under-Run Protection Device For 15 Tonne Capac...paperpublications3
Abstract: The heavy commercial vehicles are equipped with under-run protection devices (UPD) to enhance safety of occupants in small vehicles in the event of under-run. These UPD are popularly classified as RUPD (rear under-run protection devices), SUPD (side under-run protection devices), and FUPD (front under-run protection devices). These devices primarily work to improve safety of smaller vehicles by changing its interaction with heavy vehicles thereby resulting in change in small vehicle structural engagement for energy absorption. Without UPD, smaller vehicle passenger compartment is likely to interact with stiff commercial vehicle chassis frame structures.
IRJET - Design and Computational Fluid Dynamic Simulation of Micro Air Ve...IRJET Journal
This document describes the design and computational fluid dynamic (CFD) simulation of a micro air vehicle (MAV) propeller. It begins with introductions to unmanned aerial vehicles (UAVs) and MAVs. It then discusses propellers for MAVs and the importance of thrust. The document outlines the design of the MAV propeller, including the selection of the Clark-Y airfoil section based on its aerodynamic properties. It also provides the coordinates of the Clark-Y airfoil. Finally, it describes the CFD simulation process using ANSYS Fluent software to analyze thrust performance and validate the analytical results.
A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehi...Designage Solutions
A brief study of flight dynamics and different types of simulation and analysis are presented here.
Find case studies in my next PPT.- http://www.slideshare.net/HarshadaGurav/flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
CFD Analysis of Delta Winged Aircraft – A ReviewIRJET Journal
This document reviews computational fluid dynamics (CFD) analysis that has been conducted on delta wing aircraft and airfoils with surface modifications like dimples. Several studies are summarized that used CFD to analyze how dimples affect lift and drag on airfoils at various angles of attack. Dimples function similarly to vortex generators by creating vortices that delay flow separation and reduce pressure drag. Researchers have found that dimples can increase an aircraft's aerodynamic performance characteristics and maneuverability by reducing drag and stall. The document reviews multiple studies that analyzed different dimple shapes and configurations on symmetric and asymmetric airfoil profiles.
Cfd analysis of rae 2822 supercritical airfoil at transonic mach speedseSAT Journals
This document describes a CFD analysis of a RAE 2822 supercritical airfoil with and without wedge profiles at transonic Mach speeds. The analysis seeks to improve airfoil stability when flow approaches transonic Mach numbers. Key findings include observation of shock wave formation when free stream reaches transonic Mach, and drastic changes in pressure, temperature, and density across shocks. Results show lift is reduced in the transonic regime from Mach 0.7 to 1.4. Lift is higher for airfoils with wedge profiles compared to without, and for higher angles of attack. The airfoil with wedge is more stable at 150 angle of attack, with lift drop at Mach 1.1 versus 0.8 without wedge.
This document provides an overview of a project report on the aerodynamics analysis of automobiles. The report was submitted by G. Srikar in partial fulfillment of the requirements for a Bachelor of Technology degree. The report includes declarations, certificates of approval, acknowledgments, and outlines the objectives, scope, and methodology of analyzing the effects of adding aerodynamic components like diffusers, vortex generators, spoilers, tire covers, and air ducts on a vehicle model using computational fluid dynamics software. The goals are to estimate the percent reductions in drag coefficient and lift coefficient, and to improve vehicle fuel efficiency, acceleration, and handling.
Cfd analysis of car body aerodynamics including effect of passive flow device...eSAT Journals
Abstract With the emphasis lying on increasing fuel efficiency of vehicles in order to combat rising fuel prices and environmental
challenges the manufacturers are thinking beyond the conventional vehicle systems by focusing on its aerodynamics. Aerodynamic
drag exceeds 50 per cent of the total resistance to motion at speeds above 70km/hr, and above 100 km/hr it is the most important
factor. The review is done to identify the various shortcomings of the automotive designers when it is in regards to flow
separation of air at the rear of the vehicle which causes most of the losses. This paper focuses on the work already done in the
field of aerodynamics starting with Ahmed Body. It is a bluff body with adjustable rear slant angle and the basis upon which the
aerodynamicists test their models. And then, moving onto passive aerodynamic enhancements for automobiles like vortex
generators and diffusers whose various dimensional modulations were discussed with several steps leading to its advancement in
vehicle body design. This brings to the simulation, Computational Fluid Dynamics (CFD) and its role in this analysis was
covered. CFD has been modified a lot from the beginning to increase the accuracy of its predictions. So the paper lists various
simulation techniques studied by the previous researchers in order to understand the wake region behind the car which has been
notoriously difficult to predict till date. Several aspects of aerodynamic drag that need further analysis to improve the
aerodynamic were highlighted.
Keywords: Drag Force, Drag Coefficient, Ahmed Body, CFD Simulation, Vehicle Aerodynamics, Passive Flow
Devices
Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehicle (UAV)Designage Solutions
Next part of "A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehicle (UAV)" with case studies.
Find previous presentation here- http://www.slideshare.net/HarshadaGurav/a-review-of-flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
Design and Enhancement of Rear Under-Run Protection Device For 15 Tonne Capac...paperpublications3
Abstract: The heavy commercial vehicles are equipped with under-run protection devices (UPD) to enhance safety of occupants in small vehicles in the event of under-run. These UPD are popularly classified as RUPD (rear under-run protection devices), SUPD (side under-run protection devices), and FUPD (front under-run protection devices). These devices primarily work to improve safety of smaller vehicles by changing its interaction with heavy vehicles thereby resulting in change in small vehicle structural engagement for energy absorption. Without UPD, smaller vehicle passenger compartment is likely to interact with stiff commercial vehicle chassis frame structures.
IRJET - Design and Computational Fluid Dynamic Simulation of Micro Air Ve...IRJET Journal
This document describes the design and computational fluid dynamic (CFD) simulation of a micro air vehicle (MAV) propeller. It begins with introductions to unmanned aerial vehicles (UAVs) and MAVs. It then discusses propellers for MAVs and the importance of thrust. The document outlines the design of the MAV propeller, including the selection of the Clark-Y airfoil section based on its aerodynamic properties. It also provides the coordinates of the Clark-Y airfoil. Finally, it describes the CFD simulation process using ANSYS Fluent software to analyze thrust performance and validate the analytical results.
A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehi...Designage Solutions
A brief study of flight dynamics and different types of simulation and analysis are presented here.
Find case studies in my next PPT.- http://www.slideshare.net/HarshadaGurav/flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
CFD Analysis of Delta Winged Aircraft – A ReviewIRJET Journal
This document reviews computational fluid dynamics (CFD) analysis that has been conducted on delta wing aircraft and airfoils with surface modifications like dimples. Several studies are summarized that used CFD to analyze how dimples affect lift and drag on airfoils at various angles of attack. Dimples function similarly to vortex generators by creating vortices that delay flow separation and reduce pressure drag. Researchers have found that dimples can increase an aircraft's aerodynamic performance characteristics and maneuverability by reducing drag and stall. The document reviews multiple studies that analyzed different dimple shapes and configurations on symmetric and asymmetric airfoil profiles.
Cfd analysis of rae 2822 supercritical airfoil at transonic mach speedseSAT Journals
This document describes a CFD analysis of a RAE 2822 supercritical airfoil with and without wedge profiles at transonic Mach speeds. The analysis seeks to improve airfoil stability when flow approaches transonic Mach numbers. Key findings include observation of shock wave formation when free stream reaches transonic Mach, and drastic changes in pressure, temperature, and density across shocks. Results show lift is reduced in the transonic regime from Mach 0.7 to 1.4. Lift is higher for airfoils with wedge profiles compared to without, and for higher angles of attack. The airfoil with wedge is more stable at 150 angle of attack, with lift drop at Mach 1.1 versus 0.8 without wedge.
This document discusses aerodynamic modeling and simulation of aircraft at high angles of attack. It outlines some of the challenges, including developing accurate mathematical models from wind tunnel data and flight tests. Nonlinear effects like separated and unsteady flow require dynamic modeling approaches. Qualitative analysis of the nonlinear dynamics can reveal critical flight conditions like departures and spins. Flight simulations are used alongside flight tests to evaluate control laws and train pilots. Accurate modeling of phenomena like aerodynamic asymmetry is important for understanding spin behavior.
This document provides an introduction to fluid mechanics and its applications in technology. It discusses how the optimization of flows can improve efficiency and reduce emissions in applications like transportation, industrial processes, and power generation. Examples discussed include the development of more aerodynamic airplane, train, automobile, and pipeline designs over time. The document also briefly describes experimental fluid mechanics methods like wind tunnel testing and how computational fluid dynamics is now complementing these tests.
Numerical Simulation Over Flat-Disk Aerospike at Mach 6Abhishek Jain
Above Research Paper can be downloaded from www.zeusnumerix.com
The research paper aims to study the effect of Aerospikes on hypersonic missiles in the reduction of drag and heat flux. Parametric study if the aerospike geometry has been carried out by varying the L/D ratio of the spike. The results have been compared with experimental data at Mach 6. Up to 73.6% decrease in drag is seen at zero angles of attack. The reduction becomes lesser at higher angles of attack. There is a significant increase in pitching moment at an angle of attack and this needs to be further studied. Authors - Vivek Warade (Zeus Numerix), Rahul Pawar and Prof NR Gilke (KJ Somaiya COE)
This document summarizes a study on the underbody aerodynamics of sports cars. It discusses how earlier aerodynamic studies focused on the upper surfaces of cars, but understanding of underbody aerodynamics has improved in recent years. The document outlines the basic concepts of aerodynamics and computational fluid dynamics (CFD) modeling. It describes different turbulence models that can be used in CFD simulations, including k-epsilon models. It also discusses how diffusers can improve aerodynamic properties by enhancing the transition of airflow under the car.
An Analysis of Runway Capacity at International Airport Sultan Aji Sulaiman B...irjes
This document analyzes the runway capacity at Sultan Aji Sulaiman International Airport in Balikpapan, Indonesia. The airport has experienced 12.2% annual growth in aircraft movements over the last 5 years. However, the single runway and five exit taxiways limit its capacity. To increase capacity, the study examines runway occupancy times for landing and takeoff and different exit taxiway configurations. Reconstructing one exit taxiway into a rapid exit taxiway could increase the runway's capacity from 21 to 28 aircraft movements per hour. Literature on runway and taxiway design is also reviewed to understand factors that influence capacity such as taxiway layout, location and type.
The document summarizes the design of L.A.S.E.R. 5, a solar-powered unmanned aerial vehicle (UAV) being constructed by students. The goals are to break the world record for longest straight-line distance by a solar-powered UAV and to safely charge the onboard battery using solar panels and hydrogen fuel cells. The design process involves conceptual optimization under FAI regulations, aerodynamic and structural analysis using software, and selection of an efficient airfoil for long-range gliding performance at low speeds. The composite sailplane design incorporates lessons from previous L.A.S.E.R. iterations to advance renewable energy applications for aircraft.
Design and Computational Fluid Dynamic Analysis of Spiroid Winglet to Study i...IRJET Journal
This document describes a study on the design and computational fluid dynamic (CFD) analysis of a spiroid winglet to analyze its effects on aircraft performance. Spiroid winglets are bio-inspired wingtip devices that can reduce lift-induced drag. The study involves modifying an existing spiroid winglet design with a 3600 blended wingtip and conducting CFD simulations to evaluate the aerodynamic performance. The CFD analysis is conducted using commercial software Fluent to simulate airflow around the modified spiroid winglet design. Results are compared to an earlier study to validate the CFD methodology. Preliminary results show the modified spiroid winglet design improves aircraft performance by further reducing wingtip vortices and
International Refereed Journal of Engineering and Science (IRJES)irjes
This document describes a CFD analysis of air flow and temperature distribution in an air conditioned passenger car cabin with varying human loads. The study uses computational fluid dynamics software to simulate air flow patterns and temperature distributions inside a 3D modeled car cabin with 1-4 human occupants. Results from the CFD model are compared to experimental temperature and velocity measurements taken inside a real car cabin under different human loading conditions. The CFD model is shown to accurately predict temperature distribution and air flow patterns inside the passenger cabin compared to experimental data.
Research Proposal for Turbulence Examination of Class-8 VehiclesSalman Rahmani
This proposal outlines a study to reduce drag on Class-8 vehicles through the use of cylindrical modifications to the trailer. The researcher will computationally simulate and analyze two designs: 1) dual rotating cylinders mounted vertically along the trailing edge with a plate between, and 2) four rotating cylinders (two vertical, two horizontal) along the trailing edge with a plate. Simulations of each design will be run at various rotational speeds (alphas) to analyze the effects on drag. The goal is to gain insights into fluid dynamics around large objects to help reduce pollution from transportation vehicles. The timeline spans from September 2016 to May 2017 for modeling, simulations, data analysis and reporting.
Aerodynamic Study about an Automotive Vehicle with Capacity for Only One Occu...IJERA Editor
The presented study describes the aerodynamic behavior of a compact, single occupant, automotive vehicle. To
optimize the aerodynamic characteristics of this vehicle, a flow dynamics study was conducted using a virtual
model. The outer surfaces of the vehicle body were designed using Computer Aided Design (CAD) tools and its
aerodynamic performance simulated virtually using Computational Fluid Dynamics (CFD) software. Parameters
such as pressure coefficient (Cp), coefficient of friction (Cf) and graphical analysis of the streamlines were used
to understand the flow dynamics and propose recommendations aimed at improving the coefficient of drag (Cd).
The identification of interaction points between the fluid and the flow structure was the primary focus of study to
develop these propositions. The study of phenomena linked to the characteristics of the model presented here,
allowed the identification of design features that should be avoided to generate improved aerodynamic
performance.
The document discusses 12 key factors that should be considered when selecting a site for a new airport: 1) Atmospheric and meteorological conditions, 2) Availability of land for expansion, 3) Availability of utilities, 4) Development of the surrounding area, 5) Economy of construction, 6) Ground accessibility, 7) Presence of other airports, 8) Regional plan, 9) Soil characteristics, 10) Surrounding obstructions, 11) Topography, and 12) Use of airport. Careful consideration of these factors will help guide the determination of the proper location and size of a new airport.
This document is the dissertation submitted by Jose Javier Bracho for the Master of Science in Automotive Engineering at Oxford Brookes University. It analyzes the steady aerodynamic forces generated on road cars in crosswind conditions using computational fluid dynamics (CFD) and a bicycle vehicle dynamics model. The dissertation includes a literature review on ground vehicle aerodynamics and previous studies on crosswinds. It then describes the methodology used, which involves CFD simulations of three vehicle models in crosswinds and coupling the aerodynamic forces to a bicycle vehicle dynamics model. Results show that rear side area distribution is inversely proportional to yaw moment experienced. Stability is linked to both aerodynamic features and vehicle dynamics properties like tire size
Forecasting Hybrid Aircraft: How Changing Policy is Driving InnovationAndrew Wilhelm
Forecast of hybrid and fully electric aircraft engines. Research relies on regulations set by the International Civil Aviation Organization and the United States Environmental Protection Agency.
Infrastructure Requirements for Urban Air Mobility: A Financial EvaluationAndrew Wilhelm
The purpose of this research is to determine the financial feasibility of an urban air mobility (UAM) system. The evaluation will consider the infrastructure requirements and how they relate to those of existing urban mass transit services. Forces driving this innovation involve the long commute times within metropolitan areas. To rectify the problem, public mass transportation is commonly implemented in these localities. Cost for this solution is economically justified by improvements to travel time, operating, environmental, noise, and accident factors as compared to individual automobiles. A financial model for urban mass transportation is built around these characteristics and is the basis for UAM. To be competitive with the incumbent technology, new designs must meet four benchmark requirements. These entail an air vehicle that costs less than $10 million, travel that is three times faster than ground-based services, seating for 55 adults, and the capability of continuous operation. Should these criteria be met, the proposed solution will have an economic value roughly equal to that of those currently in place. The implementation of UAM can be conducted by either a clean slate or incremental approach. A real options analysis indicates that the project NPV will be similar between the two, but the latter carries less financial risk. Maintaining both systems until UAM is made sustainable attributes to this reduction. Other risks considered involve regulatory, operating, and performance concerns. The largest of which is the lack of information on future UAM air vehicle maintenance. During the financial modeling, it is assumed that the proposed operating cost is equivalent to the existing service, which is not necessarily the case. Given proper risk mitigation, the incremental implementation plan details how UAM will satisfy regulatory requirements and transition into operation. Governmental authorities are expected to take between six and eight years validating the system. In all, the proposed UAM solution will take ten years to implement and have an economic value of $48.2 million.
This document provides an overview of the field of mechanical engineering. It discusses the many scopes and applications of mechanical engineering, including flows of mechanisms, heat, work, money, forces, ideas, goods, and more. It also lists examples of applications ranging from nano technology to aerospace like the Three Gorges Dam and NASA's space shuttle. The document outlines that mechanical engineers can work in a wide variety of industries and that virtually every modern product or service is touched by mechanical engineering. It provides statistics on employment prospects for mechanical engineers both in Nepal and globally.
International Journal of Computational Engineering Research(IJCER)ijceronline
This document summarizes research on the crosswind sensitivity of passenger cars and the influence of vehicle chassis characteristics. Experimental crosswind testing was conducted on seven vehicle configurations with seven drivers. A crosswind "gauntlet" test procedure exposed drivers to alternating crosswinds over 350 feet, eliciting stronger impressions than clustered wind pulses. Driver preferences linked certain chassis properties like weight distribution and suspension characteristics to lower measured responses. The research recommends a two-stage design process using static turning analyses and dynamic simulations to predict crosswind sensitivity.
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
The papers for publication in The International Journal of Engineering& Science are selected through rigorous peer reviews to ensure originality, timeliness, relevance, and readability.
IRJET-CFD Analysis of conceptual Aircraft bodyIRJET Journal
The document analyzes the aerodynamic performance of a conceptual aircraft model through computational fluid dynamics (CFD). CFD analysis is performed on the aircraft model at different angles of attack and taper ratios to determine lift and drag forces. The results show that lift force increases with angle of attack up to stall angle, while drag force also increases. Higher taper ratios are found to generate more lift force and less drag force compared to lower taper ratios. The CFD results provide valuable data to evaluate the aircraft design for applications in fighter jets, commercial aircraft, and drones.
CFD Analysis of conceptual Aircraft bodyIRJET Journal
The document analyzes the aerodynamic performance of a conceptual aircraft model through computational fluid dynamics (CFD). CFD analysis is performed on the aircraft model at different angles of attack and taper ratios to determine lift force, drag force, pressure distribution, and other parameters. The results show that lift force increases with angle of attack up to the stall point, while drag force also increases. Higher taper ratios are found to generate more lift force and less drag force compared to lower taper ratios. The CFD results provide valuable data to evaluate the design of the conceptual aircraft for applications such as fighter jets, commercial aircraft, and drones.
IRJET- Aerodynamic Analysis of Aircraft Wings using CFDIRJET Journal
This document discusses computational fluid dynamics (CFD) analysis of aircraft wings using NACA 4412 airfoils at various angles of attack. The study uses ANSYS software to simulate air flow over the airfoil and calculate lift and drag coefficients. The results show that lift increases with angle of attack up to 25 degrees, at which point lift is highest before drag starts to dominate as the airfoil stalls. Contour plots of pressure and velocity are presented for the airfoil at angles of attack of 0, 8, 16, and 20 degrees. The CFD analysis provides insight into airfoil aerodynamic performance without requiring expensive wind tunnel testing.
Static and Dynamic Analysis of Floor Beam (Cross beam) of AircraftIRJET Journal
This document summarizes a study analyzing the static and dynamic behavior of floor beams used in aircraft. Floor beams experience bending stresses and support the weight of the aircraft. The researchers modeled a floor beam in CATIA and analyzed it in ANSYS to study stresses under different loads. They also analyzed a carbon fiber reinforced plastic floor beam. Modal analysis determined the beam's natural frequencies under vibration to ensure it can withstand operating conditions. The study aims to optimize floor beam design and materials to reduce weight while maintaining strength.
This document discusses aerodynamic modeling and simulation of aircraft at high angles of attack. It outlines some of the challenges, including developing accurate mathematical models from wind tunnel data and flight tests. Nonlinear effects like separated and unsteady flow require dynamic modeling approaches. Qualitative analysis of the nonlinear dynamics can reveal critical flight conditions like departures and spins. Flight simulations are used alongside flight tests to evaluate control laws and train pilots. Accurate modeling of phenomena like aerodynamic asymmetry is important for understanding spin behavior.
This document provides an introduction to fluid mechanics and its applications in technology. It discusses how the optimization of flows can improve efficiency and reduce emissions in applications like transportation, industrial processes, and power generation. Examples discussed include the development of more aerodynamic airplane, train, automobile, and pipeline designs over time. The document also briefly describes experimental fluid mechanics methods like wind tunnel testing and how computational fluid dynamics is now complementing these tests.
Numerical Simulation Over Flat-Disk Aerospike at Mach 6Abhishek Jain
Above Research Paper can be downloaded from www.zeusnumerix.com
The research paper aims to study the effect of Aerospikes on hypersonic missiles in the reduction of drag and heat flux. Parametric study if the aerospike geometry has been carried out by varying the L/D ratio of the spike. The results have been compared with experimental data at Mach 6. Up to 73.6% decrease in drag is seen at zero angles of attack. The reduction becomes lesser at higher angles of attack. There is a significant increase in pitching moment at an angle of attack and this needs to be further studied. Authors - Vivek Warade (Zeus Numerix), Rahul Pawar and Prof NR Gilke (KJ Somaiya COE)
This document summarizes a study on the underbody aerodynamics of sports cars. It discusses how earlier aerodynamic studies focused on the upper surfaces of cars, but understanding of underbody aerodynamics has improved in recent years. The document outlines the basic concepts of aerodynamics and computational fluid dynamics (CFD) modeling. It describes different turbulence models that can be used in CFD simulations, including k-epsilon models. It also discusses how diffusers can improve aerodynamic properties by enhancing the transition of airflow under the car.
An Analysis of Runway Capacity at International Airport Sultan Aji Sulaiman B...irjes
This document analyzes the runway capacity at Sultan Aji Sulaiman International Airport in Balikpapan, Indonesia. The airport has experienced 12.2% annual growth in aircraft movements over the last 5 years. However, the single runway and five exit taxiways limit its capacity. To increase capacity, the study examines runway occupancy times for landing and takeoff and different exit taxiway configurations. Reconstructing one exit taxiway into a rapid exit taxiway could increase the runway's capacity from 21 to 28 aircraft movements per hour. Literature on runway and taxiway design is also reviewed to understand factors that influence capacity such as taxiway layout, location and type.
The document summarizes the design of L.A.S.E.R. 5, a solar-powered unmanned aerial vehicle (UAV) being constructed by students. The goals are to break the world record for longest straight-line distance by a solar-powered UAV and to safely charge the onboard battery using solar panels and hydrogen fuel cells. The design process involves conceptual optimization under FAI regulations, aerodynamic and structural analysis using software, and selection of an efficient airfoil for long-range gliding performance at low speeds. The composite sailplane design incorporates lessons from previous L.A.S.E.R. iterations to advance renewable energy applications for aircraft.
Design and Computational Fluid Dynamic Analysis of Spiroid Winglet to Study i...IRJET Journal
This document describes a study on the design and computational fluid dynamic (CFD) analysis of a spiroid winglet to analyze its effects on aircraft performance. Spiroid winglets are bio-inspired wingtip devices that can reduce lift-induced drag. The study involves modifying an existing spiroid winglet design with a 3600 blended wingtip and conducting CFD simulations to evaluate the aerodynamic performance. The CFD analysis is conducted using commercial software Fluent to simulate airflow around the modified spiroid winglet design. Results are compared to an earlier study to validate the CFD methodology. Preliminary results show the modified spiroid winglet design improves aircraft performance by further reducing wingtip vortices and
International Refereed Journal of Engineering and Science (IRJES)irjes
This document describes a CFD analysis of air flow and temperature distribution in an air conditioned passenger car cabin with varying human loads. The study uses computational fluid dynamics software to simulate air flow patterns and temperature distributions inside a 3D modeled car cabin with 1-4 human occupants. Results from the CFD model are compared to experimental temperature and velocity measurements taken inside a real car cabin under different human loading conditions. The CFD model is shown to accurately predict temperature distribution and air flow patterns inside the passenger cabin compared to experimental data.
Research Proposal for Turbulence Examination of Class-8 VehiclesSalman Rahmani
This proposal outlines a study to reduce drag on Class-8 vehicles through the use of cylindrical modifications to the trailer. The researcher will computationally simulate and analyze two designs: 1) dual rotating cylinders mounted vertically along the trailing edge with a plate between, and 2) four rotating cylinders (two vertical, two horizontal) along the trailing edge with a plate. Simulations of each design will be run at various rotational speeds (alphas) to analyze the effects on drag. The goal is to gain insights into fluid dynamics around large objects to help reduce pollution from transportation vehicles. The timeline spans from September 2016 to May 2017 for modeling, simulations, data analysis and reporting.
Aerodynamic Study about an Automotive Vehicle with Capacity for Only One Occu...IJERA Editor
The presented study describes the aerodynamic behavior of a compact, single occupant, automotive vehicle. To
optimize the aerodynamic characteristics of this vehicle, a flow dynamics study was conducted using a virtual
model. The outer surfaces of the vehicle body were designed using Computer Aided Design (CAD) tools and its
aerodynamic performance simulated virtually using Computational Fluid Dynamics (CFD) software. Parameters
such as pressure coefficient (Cp), coefficient of friction (Cf) and graphical analysis of the streamlines were used
to understand the flow dynamics and propose recommendations aimed at improving the coefficient of drag (Cd).
The identification of interaction points between the fluid and the flow structure was the primary focus of study to
develop these propositions. The study of phenomena linked to the characteristics of the model presented here,
allowed the identification of design features that should be avoided to generate improved aerodynamic
performance.
The document discusses 12 key factors that should be considered when selecting a site for a new airport: 1) Atmospheric and meteorological conditions, 2) Availability of land for expansion, 3) Availability of utilities, 4) Development of the surrounding area, 5) Economy of construction, 6) Ground accessibility, 7) Presence of other airports, 8) Regional plan, 9) Soil characteristics, 10) Surrounding obstructions, 11) Topography, and 12) Use of airport. Careful consideration of these factors will help guide the determination of the proper location and size of a new airport.
This document is the dissertation submitted by Jose Javier Bracho for the Master of Science in Automotive Engineering at Oxford Brookes University. It analyzes the steady aerodynamic forces generated on road cars in crosswind conditions using computational fluid dynamics (CFD) and a bicycle vehicle dynamics model. The dissertation includes a literature review on ground vehicle aerodynamics and previous studies on crosswinds. It then describes the methodology used, which involves CFD simulations of three vehicle models in crosswinds and coupling the aerodynamic forces to a bicycle vehicle dynamics model. Results show that rear side area distribution is inversely proportional to yaw moment experienced. Stability is linked to both aerodynamic features and vehicle dynamics properties like tire size
Forecasting Hybrid Aircraft: How Changing Policy is Driving InnovationAndrew Wilhelm
Forecast of hybrid and fully electric aircraft engines. Research relies on regulations set by the International Civil Aviation Organization and the United States Environmental Protection Agency.
Infrastructure Requirements for Urban Air Mobility: A Financial EvaluationAndrew Wilhelm
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TIME DIVISION MULTIPLEXING TECHNIQUE FOR COMMUNICATION SYSTEM
Flow Anlaysis on Hal Tejas Aircraft using Computational Fluid Dynamics with Different Angle of Attack
1. International Journal of Advanced Engineering, Management and Science (IJAEMS) [Vol-3, Issue-5, May- 2017]
https://dx.doi.org/10.24001/ijaems.3.5.31 ISSN: 2454-1311
www.ijaems.com Page | 591
Flow Anlaysis on Hal Tejas Aircraft using
Computational Fluid Dynamics with Different
Angle of Attack
Abhishek Jain1
, S. K. Sharma2
, Comandur Rajasekhar Kaushik3
, Abhishek Gour4
1,2
Assistant Professor
1,2,3,4
Mechanical and Automation Engineering, Amity University Rajasthan, Jaipur, India
Abstract— In the current globalization, we can see many
innovations being introduced or implemented in every
aspect of field that are considered to be existed. Every
country is aiming to develop its power over all the aspects
that considered for comparison with other countries in
order to stand at same level of competition with others.
One such power considered by all countries to develop
every possible way to have a healthy competition is the
military power which involves basically innovations of fast
moving aircraft having a high lift coefficient and low drag
coefficient. Such an aircraft having the high lift and low
drag coefficient is TEJAS (HAL) developed by country India
on which the purpose of paper mainly sustains. The paper
mainly focuses on steady-state flow analysis over aircraft
TEJAS using the computer aided modelling techniques and
also the comparison of the results obtained from the
modelled techniques. The paper also outlines the designing
of the structural model of the TEJAS in a modelling
software, creation of a finite computational domain,
segmentation of this domain into discrete intervals,
applying boundary conditions such as velocity in order to
obtain plots and desired results determining the coefficient
of pressure, lift and drag coefficient, velocity magnitude etc.
This paper also aims in creating awareness to the future
students about the techniques involved and knowledge
required for developing a designed modelled. This paper
also highlights the use of CFD techniques involved for the
purpose of fluid flow simulation of the aircraft especially
performing the meshing techniques, pre and post processing
techniques and finally the evaluation of the simulation.
Finally this paper can be seen as source by future
generation students in gaining knowledge about design,
analysis and simulation of the structured model on various
conditions, about the field of aerospace engineering and
new innovations being developed and also about the career
involved when the above fields were chosen foe
specialization purposes
Keywords— Ansys Fluent, Catia Software.
I. INTRODUCTION
An aircraft is a well designed structured body basically
used for moving in air by gaining the strength from
atmosphere as it moves against the force of gravity. In
earlier days aircraft were seen as transportation medium but
with the increase in new ideas and innovations, aircraft
were introduced into the military power, thus we could see
aircraft flying during the world wars. As development in the
globalization continued, the development in many fields
also enhanced. With these developments we can see many
new innovations in designs of aircraft to make it as
innovative as possible. One such innovation were, the
considerations of properties such as the static and dynamic
lift to counter the gravitational force in order to fly the
aircraft at great heights and also to withstand against the
force of thrust. Thus the present generation aircrafts include
a lot of multidisciplinary designs to achieve critical mission
requirements such as endurances, manoeuvrability, fuel
consumption, payload capacity, noise emission etc when
compared to the older ones. But these critical requirements
can only be achieved with the help of aerodynamic property
of an aircraft such as the drag, vortex, etc. The aerodynamic
force is found to be a central idea behind the design of an
aircraft. An important aspect of this aerodynamic force is
the induced drag that approximates about 33% of the total
aerodynamic force when caused by the lift and during the
low speed movement achieved at the time of landing and
takeoff situation, it accounts for 80%-90% of the total drag.
The streamline present on an aircraft is also important
aspect of design in determining difference in pressure
between upper and lower surface of the aircraft body. The
finite wings present in an aircraft also plays major role in
2. International Journal of Advanced Engineering, Management and Science (IJAEMS) [Vol-3, Issue-5, May- 2017]
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designing since at the tip of the wing, there is leakage of air
molecules. So these finite wings are provided with the wing
tip sails in order to produce the required thrust during the
generation of lift. However research are still performed in
order to bring new innovations in these designs of aircraft
body and also to increase its efficiency. Apart from these
characteristics some of the other important aspects
considered for an aircraft design are the environmental
factors such as types of pollution, sudden climatic changes
due to increase in global warming and many other factors
that play a vital role for future growth. Nowadays travelling
in air depends mostly on the environment thus making the
power factor in the aircraft design. The figure below shows
the structured model of an aircraft.
Fig.1: Modeling of F-16 HAL TEJAS Aircraft using Solid works 2015
The structured model shown above is designed from the
specifications of the model TEJAS introduced by Hindustan
Aeronautical Limited, India. The aircraft TEJAS is well
developed product which came into light from the Light
Combat Aircraft (LCA) programme in the year 1980. It was
considered as replacement to the single fighter flights since
TEJAS is a multi-role fighter. The design of TEJAS
consists of many disciplinarians out of which some
properties such as the highly supersonic, highly
manoeuvrable and also the lightest body are considered
important. It is made of composite material structures and
the aerodynamic design, is a combination of an intense
design process involving wind tunnel studies and utilization
of extensive Computational Fluid Dynamics, the subject
which basically used for the simulation of structured models
for the analysis of the fluid flow. It has Specific
aerodynamic features that provide excellent aircraft
performance in a wider flight envelope. The dimensions of
TEJAS considered during the design of structured model
are, Wing span which is about 8.20m, while length and
height measures about 13.20m and 4.40m. The weight of
the aircraft while takeoff clean is 9800kg, during empty is
6560kg and about external stores is 3500kg. Its max speed
is supersonic at all altitudes. Its service ceiling is 50,000ft
and ‘g’ limits are +8/-3.5.(12)
. Apart from the consideration
of these specifications for the design of the structured
model, the study about the area Computational Fluid
Dynamics (CFD) was also done for the further proceeding
of the paper.CFD is a branch of study of fluid mechanics
involving algorithms and numerical methods to solve and
analyse the problems of fluid flows. Nowadays CFD is
basically studied for performing advanced calculation
purposes that are achieved by running the software. With
the introduction this software, any complex scenarios
involving turbulent flows or transonic flows can be
calculated with accuracy and speed. Many of the flight tests
involving validation of the properties considered during the
design and simulation analysis of the structural body of
design on the basis of fluid flow can be achieved easily with
this CFD based software. The calculation of Navier–Stokes
equations is easily achieved through this software that is
basically used for calculating the single phase fluid flows.
Apart from these terms another term considered in this
paper is the “Angle of Attack”, on which the whole results
of the paper are been drawn. It is basically defined as the
angle between a reference line on a body (often the chord
line of an airfoil) and the vector representing the relative
motion between the body and the fluid through which it is
moving. The below figure the structured design of the
model TEJAS be shown in terms of measurement of “Angle
of Attack”.
3. International Journal of Advanced Engineering, Management and Science (IJAEMS) [Vol-3, Issue-5, May- 2017]
https://dx.doi.org/10.24001/ijaems.3.5.31 ISSN: 2454-1311
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II. ANGLE OF ATTACK
Fig.2: Showing the basic measure of Angle of Attack
III. METHODOLOGY AND BOUNDARY
CONDITIONS
A. Creation of geometry:
The structural model of TEJAS is designed using the
SOLID WORKS 2015 software for the purpose of
simulation and analysis.(11)
B. Mesh generation:
The designed model was imported into ANSYS Work
Bench and meshed appropriately. The meshing tools like
mapping and inflation cannot be employed while meshing
as it is symmetrical in shape and gives a very fine mesh.
Once the process of meshing is completed , it is then
exported to ANSYS Fluent 14, where the simulation of
fluid flow analysis is performed.(11)
C. Simulation of the Continuum:
Here the simulation of structured body is performed in
ANSYS Fluent 14. In this the meshing of the body is
checked and once the software approves it, the models,
materials and boundary conditions are set. (11)
1. Model:
The model used for this kind of simulation is the K-E
model.(11)
2. Materials:
The air is considered as a working fluid for the
purpose of simulation in this paper and is allowed to
act on the aircraft at an altitude of 50,000 ft. Only
density is considered as the material property of the air
and is constant i.e. 1.225 kg/m3. (11)
3. Boundary Conditions:
The important boundary conditions considered for the
purpose of the external flow analysis are the Mach
number which is considered as inner boundary
condition, is taken as Mach2 i.e. the velocity of inlet
taken as 553m/s and speed of sound at this altitude is
334.72 m/s. The outer boundary condition is taken as
pressure and its value taken as 0 Pascal. The rest of the
faces of continuum are considered symmetry which
means that the faces are under no-slip condition i.e.
flow condition does not apply on these faces.(11
4. Solution:
Once the boundary conditions are set, the solution
methods and controls are set for this simulation. The
solution method set for this is the coupled solver. And
as for the solution controls the courant number is set to
0.25 and the under relaxation factors for momentum
and pressure are set as 0.75 and for the turbulent
kinetic energy, turbulent dissipation rate and turbulent
viscosity is set to 0.8. (11)
5. Analysis:
The CFD Analysis and study of results are carried out
in 3 steps: (1) Pre-processing, (2) Solving and (3)
Post-processing by using fluent solver in ANSYS
work bench.(11)
Velocity Inlet: The inlet boundary conditions involve
velocity components for varying angle of attack, turbulence
intensity and turbulent viscosity ratio. (11)
Pressure Outlet: Ambient atmospheric condition is
imposed at outlet. The velocity components are calculated
for each angle attack case as follows. The x-component of
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velocity is calculated by x =ucos(x) and the y component
of velocity is calculated by y =usin(x), where (x) is the
angle of attack in degrees.(11)
Symmetry: This is the boundary wall to see the analysis. (11)
Operating condition: The inlet velocity taken for fuselage
533 m/sec, for different angle of attack of air at normal
degree, 4 degree and 8degreee and at STP
(Temperature=300k, Pressure=101325pa) as the fluid
medium.(11)
6. Properties of Air: (11)
Density: ρ = 1.225 kg/m3
Viscosity: μ= 1.7894e-05 kg/m-s
Solvers selection: Pressure based solvers.
Mathematical models: K- ε standard wall function
Solution controls: Gauss-Seidel flow turbulence energy.
Momentum: Second Order Upwind Scheme
Initialization: Inlet Values
Force Monitors: Lift and Drag
Reference values: Inlet Values
Convergence Limit: 1x10-9
IV. RESULTS AND DISCUSSION
The analysis to be performed on all cases is carried out in ANSYS FLUENT software. Results of the analysis are drawn and are
shown below using Analysis Post processor. Velocity, pressure and residual plots are plotted on all cases of study.
Test case I:
Fig.3.1: Velocity contour at a normal degree angle .
Fig.3.2: Pressure contour at normal degree angle.
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RESIDUAL PLOT:
Graph I: It shows the iterations of residual results.
Test case II:
Fig.4.1: Velocity contour at 4 degree angle.
Fig.4.2: Pressure contour at 4 degree angle
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RESIDUAL PLOT:
Graph II : It shows iterations of residual results.
Test case III:
Fig.5.1: Velocity contour at 8 degree angle.
Fig.5.2: Pressure contour at 8 degree angle
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RESIDUAL PLOT:
Graph III : It shows iterations of residual results.
The above figures and graphs show the results being drawn
in case of pressure distribution, velocity of air and density
of the aircraft. During the movement of the aircraft in the
stream of air, the velocity flows along the upper and lower
surface of the aircraft and also along the leading edge of the
aircraft. Further at downstream, the velocity moves along
the tailing edge and this velocity is considered to be high
i.e. approximately 85% of the free stream velocity.
According to Bernoulli’s equation, as velocity increases the
pressure decreases and vice versa. Thus a higher pressure is
observed at lower surface of the body which is more than
the ambient pressure at the upper surface of the aircraft
body that is considered to be low. Further by increasing the
“angle of attack”, the velocity distribution also changes
which can be seen in the above figures, shown at ‘angle of
attack’ of 0 degrees, 4 degrees, 8 degrees respectively.
From the above figures, it is observed that there is an
increase in velocity at the upper surface while a decrease at
the lower surface. Also an increase in pressure difference
will result in an increase in the lift and is found to be same
in case of density also. We can observe from the figures that
for each “angle of attack”, the flow of velocity and the
distribution of pressure vary. The value velocity at the top
and bottom surface of aircraft at normal degree of “angle of
attack” is relatively small. Hence the value of pressure
distribution at this point is also small resulting in a small
lifting force. At this point the flow over the wing still
remains dominant. On the other hand there is large amount
of energy loses during the separation of boundary layer
and this energy loss in most applications adversely affects
the aerodynamic lift and increase in drag. So an increase in
“angle of attack” increases the drag while the reduction in
the drag results in energy and fuel consumption. The above
figures show mostly the positive pressures than the negative
pressures. So an increase in “angle of attack” results an
increase in coefficient of lift, affecting the aerodynamic
characteristics of the body. At this state, the flow separation
tends to act at the bottom edge of the body since the
pressure at the bottom edge is less than the pressure at the
top edge. The resultant pressure is the sum of the top
surface positive pressure and bottom surface negative
pressure. However sometimes due to changes in the design
conditions, the bottom surface is carrying the positive
pressure while the top surface is carrying the negative
pressure. The positive pressure at the bottom edge
determines the shape and thickness of the airfoil. Large
positive values at the bottom edge imply more severe
adverse pressure gradients. Thus due the increase in “angle
of attack”, the pressure increases from the minimum at the
top edge to the value at the bottom edge which is considered
to be maximum at that point. This total region is considered
as the pressure recovery region and this pressure is
associated with the boundary layer transitions. Thus finally
the flow separation occurs when the pressure is too high at
higher “angle of attack”.
V. GRAPHS AND TABLE
After performing required simulation, the values of
Velocity, pressure and density with a different “angle of
attack” were observed. After observing the results, the
following graphs at each degree are drawn in order show
the increase and decrease in the respective values giving an
idea about the performance of the aircraft to analyse
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Graph showing the results of the test I:
Graph 1.1: Density graph of the aircraft at normal angle
Graph 1.2: Pressure graph at normal angle
Graph 1.3: Velocity magnitude graph at normal degree
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Graphs showing the results of test II:
Graph 2.1: Velocity magnitude graph of the aircraft at 4 degree angle
Graph2.2: Pressure graph at 4 degree angle
Graph2.3: Density graph at 4 degree angle
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Graph showing the results of test III:
Graph 3.1: Velocity magnitude graph at 8 degree angle
Graph3.2: Pressure graph at 8 degree angle
Graph 3.3: Density graph at 8 degree angle
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VI. CONCLUSSION
This study shows the following conclusion:
After the analysis of the simulated flow over the aircraft on
different properties considered, the following conclusions
were drawn
As “angle of attack”’ increases, the velocity increases
and centre of pressure difference moves forward. If the
angle of attack decreases the pressure difference
moves rearward i.e. towards the bottom edge. .
For a normal degree of “angle of attack” with a speed
of 533 m/s, it is observed that the maximum velocity
is 2.405e+004m/s and total pressure acting is
1.003e+008pa.
At 4degree of “angle of attack” with speed of 533
m/s, it is observed that maximum velocity is
3.592e+005m/s, and total pressure is about
1.942e+011pa.
At 8degree of “angle of attack’ with speed of 533 m/s,
it is observed that maximum velocity is
3.772e+005m/s and total pressure is about
9.406e+009pa.
Finally from the values of the result it can concluded
that the drag and lift coefficient of the aircraft depends
on the airfoil shape and also on the velocity
distribution.
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