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Dissertations / Theses on the topic 'Delta Wing Aerodynamics'

Author: Grafiati

Published: 4 June 2021

Last updated: 10 February 2022

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1

Vaughan, Jon. "Motion induced aerodynamics of a pitching delta wing." Thesis, University of Bath, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.338376.

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Current trends in modem combat aircraft design have seen a move towards canard configurations with all moving foreplanes, providing a manoeuvre advantage with reduced stability. At the same time, with rapid advances in the field of assisted flight control and emphasis now placed on computer controlled, fly-by-wire aircraft, there is an unprecedented requirement for detailed knowledge of motion dependent aerodynamics, such as may be experienced on a foreplane undergoing rapid corrective motions. In this study, investigations have been carried out into the rigid body, motion dependent aerodynami

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2

Allan, Mark. "A CFD investigation of wind tunnel interference on delta wing aerodynamics." Thesis, University of Glasgow, 2002. http://theses.gla.ac.uk/4081/.

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To explore the influence of wind tunnel test facilities on delta wing aerodynamics, the interference has been separated into two distinct types, wall interference and support structure interference. The wall interference effects have been split into three further components, tunnel blockage, side wall interference, and roof and floor interference. Splitting the tunnel influence in this way allows us to determine the most detrimental interference effects, thus allowing the wind tunnel engineer to design experiments accordingly. Euler and more realistic RANS simulations of tunnel interference ha

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3

Worley, John C. Ahmed Anwar. "Yaw-roll coupled oscillations of a slender delta wing." Auburn, Ala, 2008. http://repo.lib.auburn.edu/EtdRoot/2008/SUMMER/Aerospace_Engineering/Thesis/Worley_John_37.pdf.

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4

Le, 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.

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<p>This 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.</p><p>Simulations of the for

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5

Görtz, Stefan. "Realistic simulations of delta wing aerodynamics using novel CFD methods." Doctoral thesis, KTH, Aeronautical and Vehicle Engineering, 2005. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-125.

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<p>The overall goal of the research presented in this thesis is to extend the physical understanding of the unsteady external aerodynamics associated with highly maneuverable delta-wing aircraft by using and developing novel, more efficient computational fluid dynamics (CFD) tools. More specific, the main purpose is to simulate and better understand the basic fluid phenomena, such as vortex breakdown, that limit the performance of delta-wing aircraft. The problem is approached by going from the most simple aircraft configuration - a pure delta wing - to more complex configurations. As the flow

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6

Görtz, Stefan. "Realistic simulations of delta wing aerodynamics using novel CFD methods /." Stockholm, 2005. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-125.

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7

Trussa, Colin Weidner. "Low-Speed Aerodynamic Characteristics of a Delta Wing with Deflected Wing Tips." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1586450691890636.

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8

Williams, Nathan M. "Active flow control on a nonslender delta wing." Thesis, University of Bath, 2009. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.501373.

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The effects of active flow control by oscillatory blowing at the leading edge of a nonslender delta wing with a Λ=50° sweep angle have been investigated. Pressure measurements and Particle Image Velocimetry measurements were conducted on a half wing to investigate the formation of leading edge vortices for oscillatory blowing, compared to the stalled flow for the no blowing case. Stall has been delayed by up to 8, and significant increases in the upper surface suction force have been observed. Velocity measurements show that shear layer reattachment is promoted with forcing, and a vortex flow

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9

Jupp, Martyn Leonard Edward. "A statistical approach to the analysis of surface pressure measurements on a pitching delta wing." Thesis, University of Glasgow, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.341739.

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10

Hubner, James Paul. "An investigation of quasiperiodic structures in the vortical flow over Delta wing configuration." Diss., Georgia Institute of Technology, 1995. http://hdl.handle.net/1853/12243.

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11

Eddy, Andito Donisha. "AN INVESTIGATION INTO DELTA WING AERODYNAMICS WITH APPLICATION TO UNMANNED AIRCRAFT IN HIGH ALTITUDE FLIGHT." The Ohio State University, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=osu1532037956695845.

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12

Sung, Bongzoo. "Analysis of the vortical flow around a 60 degree delta wing with vortex flap." Diss., Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/49932.

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Subsonic wind tunnel investigations were conducted on a 60° swept, flat plate, delta wing with a leading edge vortex flap. The pressure distributions were measured over a range of angles of attack starting from zero to 40° in 5° interval and flap deflection angles from zero to 45° with 5° increments at a Reynolds number of about 2.14 x 10‘ based on the root chord. The flow visualization experiments were performed from zero degree to the stall angle, with ten different flap deflection angles at the same Reynolds number. The mean flow field was measured at angles of attack l0° and 15° with the f

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13

Musaj, Mimoza. "Computational and experimental investigation of the aerodynamics of a W-shaped leading edge reversed delta plan-form wing." Thesis, City, University of London, 2010. http://openaccess.city.ac.uk/18110/.

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A feasibility analysis for an unconventional W-shaped leading edge, reversed delta plan-form wing has been carried out. The wing is believed to aid the Vertical/Short Take-off and Landing (V/STOL) capabilities of small aircraft. The main focus of the research was to carry out computational investigations of the flow phenomena associated with this unique shaped wing at cruise, take-off, and landing configurations. An interactive numerical and experimental method was used to baseline the important flow-field structures associated with this wing, and to identify the necessary areas for further co

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14

東, 大輔, Daisuke AZUMA, 佳朗中村 та 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.

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15

Schaeffler, 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.

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The quality of the flow over a 75 degree-sweep delta wing was documented for steady angles of attack and during dynamic maneuvers with and without the use of two control surfaces. The three-dimensional velocity field over a delta wing at a steady angle of attack of 38 degrees and Reynolds number of 72,000 was mapped out using laser-Doppler velocimetry over one side of the wing. The three-dimensional streamline and vortex line distributions were visualized. Isosurfaces of vorticity, planar distributions of helicity and all three vorticity components, and the indicator of the stability of the co

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16

Crippa, Simone. "Accurate physical and numerical modeling of complex vortex phenomena over delta wings." Licentiate thesis, Stockholm : School of engineering sciences, Royal Institute of Technology, 2006. http://www.diva-portal.org/kth/theses/abstract.xsql?dbid=4164.

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17

Cetek, Cem. "Aircraft control with nonlinear indicial response model." Ohio : Ohio University, 1999. http://www.ohiolink.edu/etd/view.cgi?ohiou1175888353.

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18

Guillermo-Monedero, Daniel. "A Comparison of Euler Finite Volume and Supersonic Vortex Lattice Methods used during the Conceptual Design Phase of Supersonic Delta Wings." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1576713976622162.

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19

McClain, A. "Aerodynamics of nonslender delta wings." Thesis, University of Bath, 2004. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.401655.

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20

Vardaki, Eleni. "Aerodynamics of nonslender delta wings." Thesis, University of Bath, 2006. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.438644.

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21

Rullan, Jose Miguel. "The Aerodynamics of Low Sweep Delta Wings." Diss., Virginia Tech, 2008. http://hdl.handle.net/10919/29386.

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The aerodynamics of wings with moderately swept wings continues to be a challenging and important problem due to the current and future use in military aircraft. And yet, there is very little work devoted to the understanding of the aerodynamics of such wings. The problem is that such wings may be able to sustain attached flow next to broken-down delta-wing vortices, or stall like two-dimensional wings, while shedding vortices with generators parallel to their leading edge. To address this situation we studied the flow field over diamond-shaped planforms and sharp-edged finite wings. Possible

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22

Elliott, Michael Stephen. "An investigation into the wing rock of an 80 degree delta wing." Thesis, Imperial College London, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.341947.

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23

Srigrarom, Sutthiphong. "On the formation of vortex breakdown over delta wings /." Thesis, Connect to this title online; UW restricted, 2001. http://hdl.handle.net/1773/10004.

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24

Gresham, Nicholas T. "Free-to-roll oscillations of low aspect ratio wings." Thesis, University of Bath, 2010. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.538123.

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25

Dogar, Muneeb. "An experimental investigation of aerodynamics and flow characteristics of slender and nonslender delta wings." Thesis, McGill University, 2013. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=114507.

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The leading-edge vortical flow structure over a 65ᵒ slender (DW65) and a 50ᵒ non-slender (DW50) delta wing was investigated at Reynolds number of order 105. Particular emphasis was placed in the variation of vortex flow quantities and critical flow parameters with change in angle of attack and chordwise distance. In addition, the progression of vortex breakdown with angle of attack was documented based on pressure and three-dimensional velocity information. A glimpse of wake-vortex evolution was also discussed. Moreover, aerodynamic lift and drag forces were evaluated based on wake survey anal

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26

Hsin-AnChen and 陳信安. "Study of the Effects of Dielectric Barrier Discharge Plasma Actuators on the Aerodynamics of a Delta Wing." Thesis, 2010. http://ndltd.ncl.edu.tw/handle/33863593226869603944.

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碩士<br>國立成功大學<br>航空太空工程學系碩博士班<br>98<br>The working principle of plasma actuators is to apply a high voltage electric field to ionize the air around the surface of electrodes attached to an aerial vehicle. Ions produced at the electrode drift from the injection electrode to the collecting one under the effect of electric field. These ions exchange momentum with the neutral fluid particles and induce fluid movement, so called electric ionic wind. Its objective is to accelerate the airflow tangentially and very close to the wall, in order to modify the airflow profile inside the boundary layer and

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27

Su, Cheng-Yu, and 蘇正瑜. "An analysis of aerodynamic forces on a delta wings." Thesis, 1998. http://ndltd.ncl.edu.tw/handle/24306907334334146784.

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28

Yavuz, Mehmet Metin. "Origin and control of the flow structure and topology on delta wings /." Diss., 2006. http://gateway.proquest.com/openurl?url_ver=Z39.88-2004&rft_val_fmt=info:ofi/fmt:kev:mtx:dissertation&res_dat=xri:pqdiss&rft_dat=xri:pqdiss:3203830.

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29

Wu, Cheng-Hsien, and 吳政憲. "Experimental Investigation on Aerodynamic Characteristics of Statics and Dynamics of 76°-40° Double Delta Wing at High Angle of Attack." Thesis, 2006. http://ndltd.ncl.edu.tw/handle/30735516036754351365.

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碩士<br>國立中興大學<br>機械工程學系<br>94<br>This study is to investigate the high pitch flow field and aerodynamic characteristics of 76°- 40° double delta wing model in static and dynamic situation by employing water tunnel. The experiment is to measure vortex burst position and relevant forces with sideslip angle (β=0°, 10°), angle of attack (α=0°~ 50°) and pitch rate (K=0.023, 0.068, 0.113), while pitching up or pitching down. From the experimental results, we observe while pitch-up angle increases, vortex burst position will move closer to the front of wing. This position is basically symmetric in bo

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30

Marini, Rebeca Nunes. "Numerical Analysis of the Vortcal Flow and Aerodynamic Behaviour of a Generic Double Delta Wing with Negative Leading Edge Strakes." Dissertação, 2018. https://hdl.handle.net/10216/115510.

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31

Marini, Rebeca Nunes. "Numerical Analysis of the Vortical Flow and Aerodynamic Behavior of a Generic Double Delta Wing with Negative Leading Edge Strakes." Master's thesis, 2018. https://hdl.handle.net/10216/115510.

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