Pub Date : 2018-11-16DOI: 10.4172/2168-9792.1000209
M. Torres, Franco-Urquiza Ea, H. Hernández-Moreno, González-Villa Ma
The present project sets out the analysis of mechanical behaviour of a carbon-epoxy stiffened panel under bending load. For this purpose, the National Polytechnic Institute of Mexico counts with a non-airworthy B727-200 as experimental platform. The first step was to calculate the aerodynamics loads and flight envelope of the aircraft. Secondly, the selection of the fuselage section is performed in order to identify an adequate stiffened panel for the study. The structural elements of the panel, skin and stiffeners were manufactured by VARTM and glued with high strength adhesive. The load, in bending condition, was imposed by a structural testing machine in order to emulate, at lab scale, the flight conditions responsible for debonding the stiffeners from the skin. The displacement field was determined by Digital Image Correlation (DIC) and the strains values at key zone of the fuselage by gages measurements. Finally, the failure mechanisms were analyzed with the goal to improve the knowledge of the stiffened-skin glued joint solution.
{"title":"Mechanical Behavior of a Fuselage Stiffened Carbon-Epoxy Panel under Debonding Load","authors":"M. Torres, Franco-Urquiza Ea, H. Hernández-Moreno, González-Villa Ma","doi":"10.4172/2168-9792.1000209","DOIUrl":"https://doi.org/10.4172/2168-9792.1000209","url":null,"abstract":"The present project sets out the analysis of mechanical behaviour of a carbon-epoxy stiffened panel under bending load. For this purpose, the National Polytechnic Institute of Mexico counts with a non-airworthy B727-200 as experimental platform. The first step was to calculate the aerodynamics loads and flight envelope of the aircraft. Secondly, the selection of the fuselage section is performed in order to identify an adequate stiffened panel for the study. The structural elements of the panel, skin and stiffeners were manufactured by VARTM and glued with high strength adhesive. The load, in bending condition, was imposed by a structural testing machine in order to emulate, at lab scale, the flight conditions responsible for debonding the stiffeners from the skin. The displacement field was determined by Digital Image Correlation (DIC) and the strains values at key zone of the fuselage by gages measurements. Finally, the failure mechanisms were analyzed with the goal to improve the knowledge of the stiffened-skin glued joint solution.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"26 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114903856","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2018-11-09DOI: 10.4172/2168-9792.1000213
Arif Nadia, Rosu Iulian, Lebon Fred´eric, Elias-Birembaux Helene
Light aircrafts are designed to be used in both developed and undeveloped areas of a country. Hard landing conditions such as shocks and rebounds may occur. In this context, a good, efficient, robust and easy to maintain landing gear is vital. Its main role is to dissipate the energy of the impact. The aim of this work is to study an innovative light aircraft landing gear equipped with a damper. The study includes comparing its dissipation performance with two traditional light aircraft landing gears: a classical flat spring landing gear and a landing gear with Sandow cords. These systems’ modeling is carried out through three steps. Firstly, Bush tire is modeled with finite elements considering tire geometry and material specificities. Secondly, combined finite elements with structural elements are used to model the different landing gear systems. Thus, stress, deformation and energy within landing gears components could be obtained. Finally, aircraft rolling simulations are conducted. Systems’ transient responses while rolling over ramp are evaluated, as well as the efforts and rebound displacements transmitted to the aircraft. A dissipation efficiency comparative study between the landing gears is conducted. In addition, the influence of simulation’ conditions such as inflation pressure, rolling velocity or runway flatness is investigated.
{"title":"On the Modeling of Light Aircraft Landing Gears","authors":"Arif Nadia, Rosu Iulian, Lebon Fred´eric, Elias-Birembaux Helene","doi":"10.4172/2168-9792.1000213","DOIUrl":"https://doi.org/10.4172/2168-9792.1000213","url":null,"abstract":"Light aircrafts are designed to be used in both developed and undeveloped areas of a country. Hard landing conditions such as shocks and rebounds may occur. In this context, a good, efficient, robust and easy to maintain landing gear is vital. Its main role is to dissipate the energy of the impact. The aim of this work is to study an innovative light aircraft landing gear equipped with a damper. The study includes comparing its dissipation performance with two traditional light aircraft landing gears: a classical flat spring landing gear and a landing gear with Sandow cords. These systems’ modeling is carried out through three steps. Firstly, Bush tire is modeled with finite elements considering tire geometry and material specificities. Secondly, combined finite elements with structural elements are used to model the different landing gear systems. Thus, stress, deformation and energy within landing gears components could be obtained. Finally, aircraft rolling simulations are conducted. Systems’ transient responses while rolling over ramp are evaluated, as well as the efforts and rebound displacements transmitted to the aircraft. A dissipation efficiency comparative study between the landing gears is conducted. In addition, the influence of simulation’ conditions such as inflation pressure, rolling velocity or runway flatness is investigated.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"2009 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-11-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130179079","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2018-08-14DOI: 10.4172/2168-9792-C2-024
V. Karar
{"title":"Various aspects of situation awareness with respect to human-machine-interaction while using optoavionic cockpit instrumentation in aircraft","authors":"V. Karar","doi":"10.4172/2168-9792-C2-024","DOIUrl":"https://doi.org/10.4172/2168-9792-C2-024","url":null,"abstract":"","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-08-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122480409","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2018-05-02DOI: 10.4172/2168-9792.1000210
A.H. Ahmed, B. Gamal, A. Ouda, A. Kamel, Y. Elhalwagy
In this paper, a complete system of quad rotor stability mechanism was designed and implemented. Starting with a Single-axis Implementation of a Quad rotor, SISO approach is implemented for control structure to achieve desired objectives. The tradition PID, modified PID controllers and Adaptive Neural fuzzy inference system (ANFIS) were executed on simulation model of Quadrotor. The performance of the designed control structure is evaluated through processor in loop experiment and through the time domain factors such as overshoot, settling time. The evaluation results reveal that the designed modified PID controller has the best performance, more robust, higher stability and less control effort compared to the original and designed ANFIS controller. Three axis test and implementation of the algorithm has been performed and the results are discussed.
{"title":"Autopilot Design of Unmanned Aerial Vehicle","authors":"A.H. Ahmed, B. Gamal, A. Ouda, A. Kamel, Y. Elhalwagy","doi":"10.4172/2168-9792.1000210","DOIUrl":"https://doi.org/10.4172/2168-9792.1000210","url":null,"abstract":"In this paper, a complete system of quad rotor stability mechanism was designed and implemented. Starting with a Single-axis Implementation of a Quad rotor, SISO approach is implemented for control structure to achieve desired objectives. The tradition PID, modified PID controllers and Adaptive Neural fuzzy inference system (ANFIS) were executed on simulation model of Quadrotor. The performance of the designed control structure is evaluated through processor in loop experiment and through the time domain factors such as overshoot, settling time. The evaluation results reveal that the designed modified PID controller has the best performance, more robust, higher stability and less control effort compared to the original and designed ANFIS controller. Three axis test and implementation of the algorithm has been performed and the results are discussed.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-05-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126722007","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2018-01-31DOI: 10.4172/2168-9792.1000206
Baig Az, T. A. Cheema, Z. Aslam, Khan Ym, H. SajidDar, Khaliq Sb
The blended wing body (BWB) concept is a relatively new concept of an aircraft. The wings and the fuselage blend into one integral structure greatly reduce drag and increases lift thus making it a highly efficient design. The aim of the research was to design a radio controlled small scale BWB aircraft for use over long ranges at low altitudes in order to deliver payloads. The BWB was divided into the center body and the outer wing. Four airfoils, HS522, LA2573A, NACA 25111 and MH78 were analyzed in XFLR5. In consideration of their lift and moment characteristics, NACA 25111 and MH78 were selected for the center body and the wing respectively. The stall speed and wing loading were the primary factors used in determining the area and size of the aircraft which converged to a design having a five feet wingspan. Center of gravity was placed ahead of aerodynamic center to provide static and dynamic stability in pitch. Twist, dihedral and sweep were given to increase stability and controllability. The final design was tested in XFLR5 for stability and in commercial computational fluid dynamic code ANSYS-Fluent for comparison. These simulation results were compared to wind tunnel tests of a 20% scaled down prototype. 3D Panel Method results in XFLR5 were found to be very close to wind tunnel results but CFD results were seen to be not conforming to the wind tunnel results after 10° angle of attack. Thus, CFD was deemed to be unnecessary for designing a plane of this size. Ultimately, a larger test prototype was made out of polystyrene foam and a successful flight was achieved.
{"title":"A New Methodology for Aerodynamic Design and Analysis of a Small Scale Blended Wing Body","authors":"Baig Az, T. A. Cheema, Z. Aslam, Khan Ym, H. SajidDar, Khaliq Sb","doi":"10.4172/2168-9792.1000206","DOIUrl":"https://doi.org/10.4172/2168-9792.1000206","url":null,"abstract":"The blended wing body (BWB) concept is a relatively new concept of an aircraft. The wings and the fuselage blend into one integral structure greatly reduce drag and increases lift thus making it a highly efficient design. The aim of the research was to design a radio controlled small scale BWB aircraft for use over long ranges at low altitudes in order to deliver payloads. The BWB was divided into the center body and the outer wing. Four airfoils, HS522, LA2573A, NACA 25111 and MH78 were analyzed in XFLR5. In consideration of their lift and moment characteristics, NACA 25111 and MH78 were selected for the center body and the wing respectively. The stall speed and wing loading were the primary factors used in determining the area and size of the aircraft which converged to a design having a five feet wingspan. Center of gravity was placed ahead of aerodynamic center to provide static and dynamic stability in pitch. Twist, dihedral and sweep were given to increase stability and controllability. The final design was tested in XFLR5 for stability and in commercial computational fluid dynamic code ANSYS-Fluent for comparison. These simulation results were compared to wind tunnel tests of a 20% scaled down prototype. 3D Panel Method results in XFLR5 were found to be very close to wind tunnel results but CFD results were seen to be not conforming to the wind tunnel results after 10° angle of attack. Thus, CFD was deemed to be unnecessary for designing a plane of this size. Ultimately, a larger test prototype was made out of polystyrene foam and a successful flight was achieved.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"51 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-01-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122713764","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2017-10-27DOI: 10.4172/2168-9792.1000203
Yadav Bk
The purpose of this paper is to give a summary of aircraft collision/accidents and bird strikes in Nepal. It presents national and international registered aircraft statistics of bird strikes and aircraft collisions between 1946 and 2016 in Nepal. The paper enlightens bird strike probe risk and challenges of aircraft operations in Nepal, details of victim/ collided aircraft with/and aircraft brief specification/models. The data was collected by reviewing different sources from Civil Aviation Authority of Nepal (CAAN), International Civil Aviation Organization (ICAO), European Aviation Safety Agency (EASA), Bureau of Aircraft Accident Achieves (B3A), World Bird-Strike Association (WBA) and qualitative approach articles/newspaper/ interviews. Finally, this paper enhances safety measures to be taken by CAAN, obligation to investigate accidents with professional method of detection with prevention of such accidents in the near and the distance future from hull losses-hull fatalities to be enshrined regulators of ICAO and EASA.
{"title":"Aircraft Collisions and Bird Strikes in Nepal Between 1946-2016: A Case Study","authors":"Yadav Bk","doi":"10.4172/2168-9792.1000203","DOIUrl":"https://doi.org/10.4172/2168-9792.1000203","url":null,"abstract":"The purpose of this paper is to give a summary of aircraft collision/accidents and bird strikes in Nepal. It presents national and international registered aircraft statistics of bird strikes and aircraft collisions between 1946 and 2016 in Nepal. The paper enlightens bird strike probe risk and challenges of aircraft operations in Nepal, details of victim/ collided aircraft with/and aircraft brief specification/models. The data was collected by reviewing different sources from Civil Aviation Authority of Nepal (CAAN), International Civil Aviation Organization (ICAO), European Aviation Safety Agency (EASA), Bureau of Aircraft Accident Achieves (B3A), World Bird-Strike Association (WBA) and qualitative approach articles/newspaper/ interviews. Finally, this paper enhances safety measures to be taken by CAAN, obligation to investigate accidents with professional method of detection with prevention of such accidents in the near and the distance future from hull losses-hull fatalities to be enshrined regulators of ICAO and EASA.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"107 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-10-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127166972","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2017-10-07DOI: 10.4172/2168-9792.1000200
Behbahani-Pour Mj, G. Radice
There have been different cases of aircraft accidents, due to the water contamination in the aviation fuel. Since large transport airplanes fly at very high altitudes, where ambient temperature can reach -6°C, water may freeze causing blockages in the fuel lines, filters, booster pumps, etc., and lead to engine thrust reduction and or engine shut down. Microbiological contamination of the fuel, due to microbial growth in the fuel, it can result in fuel tank structure corrosion, and in turn, leads to fuel leak. Fuel leak on hot engine surfaces or hot brakes can result into fire or explosion. In addition, the biological microorganisms in aviation fuel, can cause other technical problems such as it leads to fuel quantity gauge malfunctions, and fuel filter clogging. Therefore, it is important to eliminate or reduce the presence of the water and microbial growth in the in the fuel. The aim of this paper is to increase flight safety by minimizing the effect of water and biological contamination in the jet fuel. The proposed methodology, water contamination is eliminated by extracting water from fuel by using water/fuel separator and in addition, microbial contamination eliminated by uses the ultrasonic technology to destroy the bacteria in the fuel. Several experiments performed by taking fuel samples checked for presence of microbes, and then subjected to ultrasonic waves. The fuel sample located in a stainless steel and where it subjected to the ultrasonic externally (ultrasonic transmitter) located outside the tank and not on direct contact with fuel. The result show ultrasonic can heat up the fuel, and destroy the microorganisms effectively. During the experiments it has been observed that, for every five minutes of subjecting the fuel sample of 600 milliliters to ultrasonic of 42 KHz with power intensity of 50 watts, the fuel temperature increased by an average of about 6.2°C.
{"title":"Fuel Contamination on the Large Transport Airplanes","authors":"Behbahani-Pour Mj, G. Radice","doi":"10.4172/2168-9792.1000200","DOIUrl":"https://doi.org/10.4172/2168-9792.1000200","url":null,"abstract":"There have been different cases of aircraft accidents, due to the water contamination in the aviation fuel. Since large transport airplanes fly at very high altitudes, where ambient temperature can reach -6°C, water may freeze causing blockages in the fuel lines, filters, booster pumps, etc., and lead to engine thrust reduction and or engine shut down. Microbiological contamination of the fuel, due to microbial growth in the fuel, it can result in fuel tank structure corrosion, and in turn, leads to fuel leak. Fuel leak on hot engine surfaces or hot brakes can result into fire or explosion. In addition, the biological microorganisms in aviation fuel, can cause other technical problems such as it leads to fuel quantity gauge malfunctions, and fuel filter clogging. Therefore, it is important to eliminate or reduce the presence of the water and microbial growth in the in the fuel. The aim of this paper is to increase flight safety by minimizing the effect of water and biological contamination in the jet fuel. The proposed methodology, water contamination is eliminated by extracting water from fuel by using water/fuel separator and in addition, microbial contamination eliminated by uses the ultrasonic technology to destroy the bacteria in the fuel. Several experiments performed by taking fuel samples checked for presence of microbes, and then subjected to ultrasonic waves. The fuel sample located in a stainless steel and where it subjected to the ultrasonic externally (ultrasonic transmitter) located outside the tank and not on direct contact with fuel. The result show ultrasonic can heat up the fuel, and destroy the microorganisms effectively. During the experiments it has been observed that, for every five minutes of subjecting the fuel sample of 600 milliliters to ultrasonic of 42 KHz with power intensity of 50 watts, the fuel temperature increased by an average of about 6.2°C.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"247 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-10-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132749956","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2017-10-07DOI: 10.4172/2168-9792.1000199
Mitikov Yo, Ivanenko Is, Pauk Ol
In this paper considered a new method for controlling the thermal stratification of oxygen in a cylindrical rocket tank. The tank is cooled outside with liquid nitrogen, and then the tank begins to fill with oxygen. The walls of the tank are covered inside with a material with certain thermophysical properties and then polished.
{"title":"New Way of Eliminating the Temperature Stratification of Liquid Oxygen in the Tanks of Rocket Propulsion Units","authors":"Mitikov Yo, Ivanenko Is, Pauk Ol","doi":"10.4172/2168-9792.1000199","DOIUrl":"https://doi.org/10.4172/2168-9792.1000199","url":null,"abstract":"In this paper considered a new method for controlling the thermal stratification of oxygen in a cylindrical rocket tank. The tank is cooled outside with liquid nitrogen, and then the tank begins to fill with oxygen. The walls of the tank are covered inside with a material with certain thermophysical properties and then polished.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"37 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-10-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132766475","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2017-08-31DOI: 10.4172/2168-9792.1000197
Zollars, R. Cobb, David J. Grymin
This paper identifies feasible fight paths for Small Unmanned Aircraft Systems in a highly constrained environment. Optimal control software has long been used for vehicle path planning and has proven most successful when an adequate initial guess is presented to an optimal control solver. Leveraging computer animation techniques, a large search space is discretized into a set of simplexes where a Dubins path solution is generated and contained in a polygonal search corridor free of path constraints. Direct optimal control methods are then used to determine the optimal flight path through the newly defined search corridor. Two scenarios are evaluated. The first is limited to heading rate control only, requiring the air vehicle to maintain constant speed. The second allows for velocity control which permits slower speeds, reducing the vehicles minimum turn radius and increasing the search domain. Results illustrate the benefits gained when including speed control to path planning algorithms by comparing trajectory and convergence times, resulting in a reliable, hybrid solution method to the SUAS constrained optimal control problem.
{"title":"Simplex Solutions for Optimal Control Flight Paths in Urban Environments","authors":"Zollars, R. Cobb, David J. Grymin","doi":"10.4172/2168-9792.1000197","DOIUrl":"https://doi.org/10.4172/2168-9792.1000197","url":null,"abstract":"This paper identifies feasible fight paths for Small Unmanned Aircraft Systems in a highly constrained environment. Optimal control software has long been used for vehicle path planning and has proven most successful when an adequate initial guess is presented to an optimal control solver. Leveraging computer animation techniques, a large search space is discretized into a set of simplexes where a Dubins path solution is generated and contained in a polygonal search corridor free of path constraints. Direct optimal control methods are then used to determine the optimal flight path through the newly defined search corridor. Two scenarios are evaluated. The first is limited to heading rate control only, requiring the air vehicle to maintain constant speed. The second allows for velocity control which permits slower speeds, reducing the vehicles minimum turn radius and increasing the search domain. Results illustrate the benefits gained when including speed control to path planning algorithms by comparing trajectory and convergence times, resulting in a reliable, hybrid solution method to the SUAS constrained optimal control problem.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125646095","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2017-08-31DOI: 10.4172/2168-9792.1000198
A. Rajesh, Badri Dr, Ganesha Prasad Ms
A numerical study was undertaken to study the effect of the span wise injection on the performance of a 3D wing at a velocity of 15 m/s and angle of attack of 6°, 8°, and 10°. A baseline configuration along with injection at tip was studied. A study was conducted to understand the flow field and the winglet control techniques. Based on the study, a wing configuration was chosen as baseline configurations and different injection velocities were applied to this configuration. The chord wise pressure distribution is seen to change with the span wise location from the root and this distribution is affected by the wing tip vortex. The wingtip was observed to change the pressure distribution near the tip. The velocity field, stream lines and the vortices were seen to be affected by the presence of the injection. The lift and drag values were seen to decrease with the angle of attack but the l/d ratio remained nearly constant for all the injection configurations. Maximum reduction in drag of nearly 19% could be achieved with the injection. This study proved the possibility of using span wise injection as a control method to control the wing tip vortex.
{"title":"Numerical Analysis on the Effect of Fluidic on Demand Winglet on the Aerodynamic Performance of the Wing","authors":"A. Rajesh, Badri Dr, Ganesha Prasad Ms","doi":"10.4172/2168-9792.1000198","DOIUrl":"https://doi.org/10.4172/2168-9792.1000198","url":null,"abstract":"A numerical study was undertaken to study the effect of the span wise injection on the performance of a 3D wing at a velocity of 15 m/s and angle of attack of 6°, 8°, and 10°. A baseline configuration along with injection at tip was studied. A study was conducted to understand the flow field and the winglet control techniques. Based on the study, a wing configuration was chosen as baseline configurations and different injection velocities were applied to this configuration. The chord wise pressure distribution is seen to change with the span wise location from the root and this distribution is affected by the wing tip vortex. The wingtip was observed to change the pressure distribution near the tip. The velocity field, stream lines and the vortices were seen to be affected by the presence of the injection. The lift and drag values were seen to decrease with the angle of attack but the l/d ratio remained nearly constant for all the injection configurations. Maximum reduction in drag of nearly 19% could be achieved with the injection. This study proved the possibility of using span wise injection as a control method to control the wing tip vortex.","PeriodicalId":356774,"journal":{"name":"Journal of Aeronautics and Aerospace Engineering","volume":"37 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126670742","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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