Dissertations / Theses on the topic 'High angle of attack'
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Atesoglu, Ozgur Mustafa. "High Angle Of Attack Maneuvering And Stabilization Control Of Aircraft." Phd thesis, METU, 2007. http://etd.lib.metu.edu.tr/upload/12608575/index.pdf.
Full textWalter, Daniel James, and Daniel james walter@gmail com. "Study of aerofoils at high angle of attack in ground effect." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2007. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20080110.145138.
Full textPetterson, Kristian. "The aerodynamics of slender aircraft forebodies at high angle of attack." Thesis, Cranfield University, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.392234.
Full textMohmad, Rouyan Nurhana. "Model simulation suitable for an aircraft at high angle of attack." Thesis, Cranfield University, 2016. http://dspace.lib.cranfield.ac.uk/handle/1826/9722.
Full textStucke, Russell Andrew. "High Angle-of-Attack Yaw Control Using Strakes on Blunt-Nose Bodies." University of Toledo / OhioLINK, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1167777201.
Full textRavi, R. "High Angle of Attack Forebody Flow Physics and Design Emphasizing Directional Stability." Diss., This resource online, 1997. http://scholar.lib.vt.edu/theses/available/etd-01252008-163458/.
Full textYip, Pui-Chuen Patrick. "A comparison of control design options for high angle-of-attack flights." Thesis, Massachusetts Institute of Technology, 1991. http://hdl.handle.net/1721.1/13431.
Full textIncludes bibliographical references (p. 168-170).
by Pui-Chuen Patrik Yip.
M.S.
Stagg, Gregory A. "An Aerodynamic Model for Use in the High Angle of Attack Regime." Thesis, Virginia Tech, 1998. http://hdl.handle.net/10919/35596.
Full textMaster of Science
Ko, Joon Soo. "Analysis of the dynamic stability derivatives for high angle of attack aircraft." Diss., Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/52300.
Full textPh. D.
Sirangu, Vijaya. "AERODYNAMIC CONTROL OF SLENDER BODIES AT HIGH ANGLES OF ATTACK." University of Toledo / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1271365316.
Full textJouannet, Christopher. "Model based aircraft design : high angle of attack aerodynamics and weight estimation methods /." Linköping : Dept. of Mechanical Engineering, Linköping University, 2005. http://www.bibl.liu.se/liupubl/disp/disp2005/tek968s.pdf.
Full textJohnson, Dan A. "Flowfield measurements in the wake of a missile at high angle of attack." Thesis, Monterey, California. Naval Postgraduate School, 1989. http://hdl.handle.net/10945/27059.
Full textFan, Yigang. "Identification of an Unsteady Aerodynamic Model up to High Angle of Attack Regime." Diss., Virginia Tech, 1997. http://hdl.handle.net/10919/29830.
Full textPh. D.
MAY, CAMERON. "HIGH ANGLE OF ATTACK FLIGHT CONTROL OF DELTA WING AIRCRAFT USING VORTEX ACTUATORS." University of Cincinnati / OhioLINK, 2005. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1109166873.
Full textRosti, Marco. "Direct numerical simulation of an aerofoil at high angle of attack and its control." Thesis, City, University of London, 2016. http://openaccess.city.ac.uk/15843/.
Full textLego, Zachary Michael. "Analysis of High Angle of Attack Maneuvers to Enhance Understanding of the Aerodynamics of Perching." University of Dayton / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1355101333.
Full textCoutley, Raymond L. "Numerical studies of compressible flow over a double-delta wing at high angle of attack." Thesis, Monterey, California. Naval Postgraduate School, 1990. http://hdl.handle.net/10945/30688.
Full textThe objective of this work is the investigation of vortical flows at high angles of attack using numerical techniques. The first step for a successful application of a numerical technique, such as fimite difference or finite volume, is the generation of a computational mesh which can capture adequately and accurately the important physics of the flow. Therefore, the first part of this work deals with the grid generation over a double-delta wing and the second part deals with the visualization of the computed flow field over the double-delta wing at different angles of attack. The surface geometry of the double-delta wing is defined algebraically. The developed surface grid generator provides flexibility in distributing the surface points along the axial and circumferential directions. The hyperbolic grid generation method is chosen for the field grid generation and both cylindrical and spherical grids are constructed. The computed low speed (M = 0.2) flow results at different angles of attack over the double-delta wing are visualized. Important flow characteristics of the leeward side flow field are discussed while the development of vortex interaction, occurrence and progression of vortex breakdown as the angle of attack increases is demonstrated. The computed results at different fixed angles of attack are presented.
Lung, Ming-Hung. "Flowfield measurements in the vortex wake of a missile at high angle of attack in turbulence." Thesis, Monterey, California. Naval Postgraduate School, 1988. http://hdl.handle.net/10945/23235.
Full textThe flowfield downstream of a vertically-launched surface-to-air missile model at an angle of attack of 50° and a Reynolds number of 1.1 x 10(5) was investigated in a wind tunnel of the Naval Postgraduate School. The goal of this thesis is to experimentally validate the pressure measurement system for flowfield variables with elevated levels of turbulence; to determine the location and intensity of the asymmetric vortices in the wake of the VLSAM model at a raised level of freestream turbulence; and to display the asymmetric vortices by velocity mapping and pressure contours. The purpose is to correlate the results with the force measurements of Rabang to provide a greater understanding of the vortex flowfield. The body-only configuration was tested. Two flowfield conditions were treated: the nominal ambient wind tunnel condition, and a condition with grid generated turbulence of 3.8% turbulence intensity and a dissipation length scale of 1.7 inches. The following conclusions were reached: 1) The relative strengths of the asymmetric vortices can be noted by the sharp spike shape in the ambient condition; this condition becomes diffused and becomes fatter in the turbulent condition; 2) The right side vortex has greater strength than the left side one as seen by the diffusion in the total pressure coefficient and static pressure coefficient contours with and without a turbulent condition; 3) an increase in turbulence intensity tends to reduce the strength of the asymmetric nose-generated vortices; also pushes the two asymmetric vortices closer together; 4) and crossflow velocities were examined and were found to indicate the behavior denoted by the pressure contours.
http://archive.org/details/flowfieldmeasure00lung
Lieutenant, Republic of China Navy
Takahama, Morio, Noboru Sakamoto, and Yuhei Yamato. "Attitude Stabilization of an Aircraft via Nonlinear Optimal Control Based on Aerodynamic Data." Institute of Electrical and Electronics Engineers, 2009. http://hdl.handle.net/2237/14420.
Full textNadeau, Yvan. "A comparative non-linear analytical and numerical irrotational analysis of aerofoils at high angle of attack /." Thesis, McGill University, 1989. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=55626.
Full textLopera, Javier. "Aerodynamic Control of Slender Bodies from Low to High Angles of Attack through Flow Manipulation." Connect to Online Resource-OhioLINK, 2007. http://www.ohiolink.edu/etd/view.cgi?acc_num=toledo1177504352.
Full textAtkinson, Michael D. "Control of Hypersonic High Angle-Of-Attack Re-Entry Flow Using a Semi-Empirical Plasma Actuator Model." University of Dayton / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1335283726.
Full textPilkington, David J. "Motion induced unsteady aerodynamics at high angles-of-attack." Thesis, University of Bath, 1996. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.760689.
Full textAlkhozam, Abdullah M. "Interaction, bursting and dynamic control of vortices of a cropped double-delta wing at high angle of attack." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1994. http://www.dtic.mil/cgi-bin/GetTRDoc?AD=ADA283656&Location=U2&doc=GetTRDoc.pdf.
Full textThesis advisor(s): S. K. Hebbar, M. F. Platzer. "March 1994." Cover title: Interaction, ... and control of vortices of a cropped ... Includes bibliographical references. Also available online.
東, 大輔, Daisuke AZUMA, 佳朗 中村, and Yoshiaki NAKAMURA. "前縁回転/後縁ジェットハイブリッド法によるデルタ翼揚力増加." 日本航空宇宙学会, 2006. http://hdl.handle.net/2237/13878.
Full textSchaeffler, Norman Walter. "All The King's Horses: The Delta Wing Leading-Edge Vortex System Undergoing Vortex Breakdown: A Contribution to its characterization and Control under Dynamic Conditions." Diss., Virginia Tech, 1998. http://hdl.handle.net/10919/30454.
Full textPh. D.
Ponton, Anthony J. C. "The evaluation of canard couplings at high angles of attack." Thesis, University of Bristol, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.389992.
Full textCrowther, William James. "Yaw control at high angles of attack by tangential forebody blowing." Thesis, University of Bath, 1994. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.239945.
Full textMathre, John Mark. "Computational investigation of incompressible airfoil flows at high angles of attack." Thesis, Monterey, California. Naval Postgraduate School, 1988. http://hdl.handle.net/10945/22965.
Full textCebeci's viscous/inviscid interaction program was applied to the analysis of steady, two dimensional, incompressible flow past four airfoils, the NACA 66₃-018, 0010 (Modified), 4412 and the Wortmann FX 63-137. Detailed comparisons with the available experimental results show that the essential features are correctly modelled, but that significant discrepancies are found in regions of flow separations.
http://archive.org/details/computationalinv00math
Lieutenant, United States Navy
De, Oliveira Neto Pedro Jose. "An Investigation of Unsteady Aerodynamic Multi-axis State-Space Formulations as a Tool for Wing Rock Representation." Diss., Virginia Tech, 2007. http://hdl.handle.net/10919/29600.
Full textPh. D.
Salemi, Leonardo da Costa, and Leonardo da Costa Salemi. "Numerical Investigation of Hypersonic Conical Boundary-Layer Stability Including High-Enthalpy and Three-Dimensional Effects." Diss., The University of Arizona, 2016. http://hdl.handle.net/10150/621854.
Full textTait, Sean William. "An investigation of fore-body aerodynamics during the velocity vector roll." Thesis, University of the West of Scotland, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.265929.
Full textMunro, Cameron. "Water tunnel validation and experiments at high angles of attack for aircraft conceptual design /." Linköping : Univ, 2003. http://www.bibl.liu.se/liupubl/disp/disp2002/tek847s.pdf.
Full textBean, David. "The analysis and suppression of vortex induced unsteady loads at high angles of attack." Thesis, University of Bath, 1992. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.306707.
Full textGreenwell, D. I. "Control of asymmetric vortical flow over a delta wing at high angles of attack." Thesis, University of Bath, 1993. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.334618.
Full textCetiner, Abdullah Emre. "Split Canard Design For Enhancing The Maneuverability Of A Missile At High Angles Of Attack." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12614920/index.pdf.
Full texts aerodynamic performance whereas longitudinal position of the split canards only affects the pitching moment of the missile. Finally, an enhanced semi-empirical engineering-level method, CFD-CBU, is developed for split canard mounted missiles in order to predict the normal force and the pitching moment coefficients. The developed method is validated with NDCM test case model. After this validation, the method is applied to the split canard mounted generic missile in case of no control deflection and pitch control deflection. The results of this method are compared with CFD results and it is seen that the results are in good agreement with each other.
Chang, Wen-Huan. "Effect of juncture fillets on double-delta wings undergoing sideslip at high angles of attack." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1994. http://handle.dtic.mil/100.2/ADA286165.
Full textThesis advisor(s): S. K.Hebbar, Max F. Platzer. "September 1994." Includes bibliographical references. Also available online.
Mondoloni, Stéphane Lucien. "A numerical method for modelling wings with sharp edges maneuvering at high angles of attack." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/49922.
Full textHooper, Jack Charles. "Vertical landing flight envelope definition." Thesis, Luleå tekniska universitet, Rymdteknik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-80717.
Full textLe, Moigne Yann. "Adaptive Mesh Refinement and Simulations of Unsteady Delta-Wing Aerodynamics." Doctoral thesis, KTH, Aeronautical and Vehicle Engineering, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3786.
Full textThis thesis deals with Computational Fluid Dynamics (CFD)simulations of the flow around delta wings at high angles ofattack. These triangular wings, mainly used in militaryaircraft designs, experience the formation of two vortices ontheir lee-side at large angles of attack. The simulation ofthis vortical flow by solving the Navier-Stokes equations isthe subject of this thesis. The purpose of the work is toimprove the understanding of this flow and contribute to thedesign of such a wing by developing methods that enable moreaccurate and efficient CFD simulations.
Simulations of the formation, burst and disappearance of thevortices while the angle of attack is changing are presented.The structured flow solver NSMB has been used to get thetime-dependent solutions of the flow. Both viscous and inviscidresults of a 70°-swept delta wing pitching in anoscillatory motion are reported. The creation of the dynamiclift and the hysteresis observed in the history of theaerodynamic forces are well reproduced.
The second part of the thesis is focusing on automatic meshrefinement and its influence on simulations of the delta wingleading-edge vortices. All the simulations to assess the gridquality are inviscid computations performed with theunstructured flow solver EDGE. A first study reports on theeffects of refining thewake of the delta wing. A70°-swept delta wing at a Mach number of 0.2 and an angleof attack of 27° where vortex breakdown is present abovethe wing, is used as testcase. The results show a strongdependence on the refinement, particularly the vortex breakdownposition, which leads to the conclusion that the wake should berefined at least partly. Using this information, a grid for thewing in the wind tunnel is created in order to assess theinfluence of the tunnel walls. Three sensors for automatic meshrefinement of vortical flows are presented. Two are based onflow variables (production of entropy and ratio of totalpressures) while the third one requires an eigenvalue analysisof the tensor of the velocity gradients in order to capture theposition of the vortices in the flow. These three vortexsensors are successfully used for the simulation of the same70° delta wing at an angle of attack of 20°. Acomparison of the sensors reveals the more local property ofthe third one based on the eigenvalue analysis. This lattertechnique is applied to the simulation of the wake of a deltawing at an angle of attack of 20°. The simulations on ahighly refined mesh show that the vortex sheet shed from thetrailing-edge rolls up into a vortex that interacts with theleading-edge vortex. Finally the vortex-detection technique isused to refine the grid around a Saab Aerosystems UnmannedCombat Air Vehicle (UCAV) configuration and its flight dynamicscharacteristics are investigated.
Key words:delta wing, high angle of attack, vortex,pitching, mesh refinement, UCAV, vortex sensor, tensor ofvelocity gradients.
Morris, Seth Henderson. "Quasi-Transient Calculation of Surface Temperatures on a Reusable Booster System with High Angles of Attack." University of Dayton / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1324573899.
Full textLi, Feng-Hsi. "Static and dynamic flow visualization studies of two double-delta wing models at high angles of attack." Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/23777.
Full textSommers, John Douglas. "An experimental investigation of support strut interference on a three-percent fighter model at high angles of attack." Thesis, Monterey, California. Naval Postgraduate School, 1989. http://hdl.handle.net/10945/25926.
Full textWorasinchai, Supakit. "Small wind turbine starting behaviour." Thesis, Durham University, 2012. http://etheses.dur.ac.uk/4436/.
Full textHammer, Patrick Richard. "A Discrete Vortex Method Application to Low Reynolds Number Aerodynamic Flows." University of Dayton / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1311792450.
Full textFrink, William D. Jr. "Hot-wire surveys in the vortex wake downstream of a three-percent fighter aircraft model at high angles of attack." Thesis, Monterey, California: Naval Postgraduate School, 1990. http://hdl.handle.net/10945/27586.
Full textA low-speed wind tunnel investigation was conducted to examine the vortex wake downstream of a three-percent scale model of the YF-17 lightweight fighter prototype at high angles of attack. The study was in support of NASA ames Research Center's wind tunnel investigation of a full scale FA-18 as part of NASA's High Alpha Technology Program. Smoke flow visualization was used to locate the downstream vortex wake. Hot-wire surveys were taken through the vortex at two stations; one directly aft of the model and the other at a station three model lengths downstream of the model. The effect of adding a fence to the leading edge extension (LEX) was studied. Power spectra from the hot-wire were recorded for the survey station directly aft of the model. Results show that: peak turbulent fluctuation at this station occurred at 25 deg angle of attack; lateral turbulent fluctuation greatly diminished at the far downstream station; and the addition of the LEX fence shifted energy content of turbulence toward higher frequencies.
Frink, William D. "Hot-wire surveys in the vortex wake downstream of a three-percent fighter aircraft model at high angles of attack." Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA241869.
Full textThesis Advisor(s): Hebbar, Sheshagiri K. ; Platzer, Max F. "December 1990." Description based on title screen as viewed on March 31, 2010. DTIC Identifier(s): Trailling Vortices, Wake, Trubulent Flow, Jet Fighters, High Alpha (High Angle of Attack), Vortex Wake, Angle of Attack, Extendable Structures, Leading Edges, Fences, Lex Fences, Wind Tunnel Models, F-17 Aircraft, F/A-18 Aircraft, Wind Tunnel Tests, Hot Wire Anemometers, Theses. Author(s) subject terms: High Angle-of-Attack Aerodynamics, Hot-Wire Measurements, Wind Tunnel Studies. Includes bibliographical references (p. 24-25). Also available in print.
Clark, Adam. "Predicting the Crosswind Performance of High Bypass Ratio Turbofan Engine Inlets." The Ohio State University, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=osu1476265135449178.
Full textCavazos, Odilon V. "A flow visualization study of LEX generated vortices on a scale model of F/A-18 fighter aircraft at high angles of attack." Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA236534.
Full textThesis Advisor(s): Hebbar, S. K. ; Platzer, M. F. "June 1990." Description based on title screen as viewed on October 19, 2009. DTIC Descriptor(s): Angles, yaw, scale models, attack, motion, rates, moments, vortices, flow visualization, rupture, asymmetry, aerodynamic forces, leading edges, range(distance), statics, hysteresis, aerodynamics, high angles, pitch(motion). DTIC Indicator(s): Flow visualization, trailing vortices, F/A-18 aircraft. Author(s) subject terms: High angle of attack aerodynamics, effect of pitch rate and yaw, vortex development and bursting, flow visualization by dye injection, water tunnel studies, F/A-18 fighter aircraft. Includes bibliographical references (p. 44-45). Also available in print.
Russ, Thomas William. "A surface flow visualization study of boundary layer behavior on the blades of a solid-wall compressor cascade at high angles of attack." Thesis, Virginia Polytechnic Institute and State University, 1987. http://hdl.handle.net/10919/53161.
Full textMaster of Science