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Dissertations / Theses on the topic 'Attack angle'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

Sims, J. P. "In-flight measurement of angle of attack." Thesis, Swansea University, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.639041.

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Three possible techniques for measuring angle of attack (AOA) have been investigated with a view to establishing a low-cost method for use in light aircraft. Basically, methods using new silicon bonded pressure transducers and low cost inertial components have been compared with a standard AOA system. An Inertial Measurement Unit (IMU) and a differential pressure AOA system have been designed and constructed using the low-cost transducers and both have been installed in a twin engined general aviation aircraft along with the Teledyne AOA cone probe. A series of flight tests have been conducted

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2

Hoang, Ngoc T. "The hemisphere-cylinder at an angle of attack." Diss., This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-08062007-094404/.

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3

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.

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In this study, the implementation of modern control techniques, that can be used both for the stable recovery of the aircraft from the undesired high angle of attack flight state (stall) and the agile maneuvering of the aircraft in various air combat or defense missions, are performed. In order to accomplish this task, the thrust vectoring control (TVC) actuation is blended with the conventional aerodynamic controls. The controller design is based on the nonlinear dynamic inversion (NDI) control methodologies and the stability and robustness analyses are done by using robust performance (RP) a

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4

Ganji, Farid 1967. "Control of the space shuttle angle-of-attack during reentry." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/89340.

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5

Walter, 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.

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Aerodynamic devices, such as wings, are used in higher levels of motorsport (Formula-1 etc.) to increase the contact force between the road and tyres (i.e. to generate downforce). This in turn increases the performance envelope of the race car. However the extra downforce increases aerodynamic drag which (apart from when braking) is generally detrimental to lap-times. The drag acts to slow the vehicle, and hinders the effect of available drive power and reduces fuel economy. Wings, in automotive use, are not constrained by the same parameters as aircraft, and thus higher angles of attack can b

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6

Petterson, 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.

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7

Mohmad, 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.

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Simulation of a dynamic system is known to be sensitive to various factors and one of them could be the precision of model parameters. While the sensitivity of flight dynamic simulation to small changes in aerodynamic coefficients is typically not studied, the simulation of aircraft required to operate in nonlinear flight regimes usually at high angles of attack can be very sensitive to such small differences. Determining the significance and impact of the differences in aerodynamic characteristics is critical for understanding the flight dynamics and designing suitable flight control laws. Th

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8

Cohen, David E. II. "Trim Angle of Attack of Flexible Wings Using Non-Linear Aerodynamics." Diss., Virginia Tech, 1998. http://hdl.handle.net/10919/30404.

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Multidisciplinary interactions are expected to play a significant role in the design of future high-performance aircraft (Blended-Wing Body, Truss-Braced wing, High Speed Civil transport, High-Altitude Long Endurance aircraft and future military aircraft). Also, the availability of supercomputers has made it now possible to employ high-fidelity models (Computational Fluid Dynamics for fluids and detailed finite element models for structures) at the preliminary design stage. A necessary step at that stage is to calculate the wing angle-of-attack at which the wing will generate the desired lift

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9

Yip, 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.

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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1991, and Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Electrical Engineering and Computer Science.<br>Includes bibliographical references (p. 168-170).<br>by Pui-Chuen Patrik Yip.<br>M.S.

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10

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.

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Harmonic oscillatory tests for a fighter aircraft using the Dynamic Plunge--Pitch--Roll model mount at Virginia Tech Stability Wind Tunnel are described. Corresponding data reduction methods are developed on the basis of multirate digital signal processing. Since the model is sting mounted, the frequencies associated with sting vibration are included in balance readings thus a linear filter must be used to extract out the aerodynamic responses. To achieve this, a Finite Impulse Response (FIR) is designed using the Remez exchange algorithm. Based on the reduced data, a state--space model is

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11

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.

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Modern, high performance aircraft are required to be able to fly and be controlled over a wide variety of flight conditions. In order to predict the aircraft behavior and control requirements over the entire flight regime it is necessary to have a proper aerodynamic model. Flight conditions at high angles of attack lead to separated flows making the aerodynamic model more difficult to obtain. In this research wind tunnel experiments are performed on an F-5 air-craft model at high angles of attack, with small oscillations about the body oriented roll axis. In addition the free stream environmen

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12

Stucke, 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.

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13

Ravi, 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/.

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14

Jouannet, 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.

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15

Johnson, 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.

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16

Fan, Yigang. "Identification of an Unsteady Aerodynamic Model up to High Angle of Attack Regime." Diss., Virginia Tech, 1997. http://hdl.handle.net/10919/29830.

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The harmonic oscillatory tests for a fighter aircraft configuration using the Dynamic Plunge-Pitch-Roll (DyPPiR) model mount at Virginia Tech Stability Wind Tunnel are described and analyzed. The corresponding data reduction methods are developed on the basis of multirate digital signal processing techniques. Since the model is sting-mounted to the support system of DyPPiR, the Discrete Fourier Transform (DFT) is first used to identify the frequencies of the elastic modes of sting. Then the sampling rate conversion systems are built up in digital domain to resample the data at a lower rate wit

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17

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.

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18

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.

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19

Rosti, 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/.

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Detailed analysis of the flow around a NACA0020 aerofoil at moderate low chord Reynolds number (Rec = 2×104) in completely stalled conditions has been carried out by means of Direct Numerical Simulations. The stalled condition is either a steady configuration at a fixed angle of attack (α = 20o) or it is reached via a ramp-up manoeuvre, increasing the angle of attack from 0o to 20o. Concerning this last case, new insights on the vorticity dynamics leading to the lift overshoot, lift crisis and the damped oscillatory cycle that gradually matches the steady condition, are discussed using a numbe

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20

Wilks, Brett Landon Burkhalter Johnny Evans. "Aerodynamics of wrap-around fins in supersonic flow." Auburn, Ala., 2005. http://repo.lib.auburn.edu/2005%20Fall/Thesis/WILKS_BRETT_54.pdf.

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21

Rabe, Angela C. "Effectiveness of a Serpentine Inlet Duct Flow Control Scheme at Design and Off-Design Simulated Flight Conditions." Diss., Virginia Tech, 2003. http://hdl.handle.net/10919/28653.

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An experimental investigation was conducted in a static ground test facility to determine the flow quality of a serpentine inlet duct incorporating active flow control for several simulated flight conditions. The total pressure distortion at the aerodynamic interface plane (AIP) was then used to predict the resulting stability for a compression system. This study was conducted using a model of a compact, low observable, engine inlet duct developed by Lockheed Martin. A flow control technique using air injection through microjets at 1% of the inlet mass flow rate was developed by Lockheed Ma

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22

Coutley, 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.

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Approved for public release, distribution is unlimited<br>The 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-d

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23

Lego, 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.

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24

Nadeau, 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.

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25

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.

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Approved for public release; distribution is unlimited<br>The 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

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26

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.

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27

Whale, James Callum Andrew. "How to make a tuna burst : the role of angle of attack in the production of thrust." Thesis, University of British Columbia, 2016. http://hdl.handle.net/2429/58577.

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Tuna—along with whales and lamnid sharks—utilise thunniform locomotion, a mode of swimming that optimises efficiency at high speed and isolates thrust production to the caudal fin. Thunniform performance is controlled by adjustments in the way the caudal fin interacts with fluid flow which, in turn, determines thrust and efficiency. The effect of tail motion on performance provides insight into the link between locomotor muscle biomechanics and hydrodynamics; these insights can be used to mimic and optimise animal motion in a robotic context. This study focuses on how the maximum angle of

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28

Contreras, Daimer Mauthsud Leovan Ospina. "Angle of attack impact in the aerothermodynamics of a hypersonic vehicle with surface discontinuity-like a cavity." Instituto Nacional de Pesquisas Espaciais (INPE), 2017. http://urlib.net/sid.inpe.br/mtc-m21b/2017/04.12.00.58.

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The study described in this dissertation was undertaken with the purpose to investigate the impact of discontinuities present on the surface of hypersonic space vehicles. With this perspective in mind, computational simulations of a non-reacting rarefied hypersonic flow over a flat plate with a cavity have been performed by using the Direct Simulation Monte Carlo method. Simulations provided a comprehensive description about the nature of the flowfield structure and the aerodynamic surface properties on the cavity resulting from changes in the length-to-depth (L/H) ratio and changes in the ang

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29

Atkinson, 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.

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30

Lopera, 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.

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31

Alkhozam, 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.

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Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, March 1994.<br>Thesis 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.

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32

Torres, Luis Carlos Roldan. "Angle of attack effect in the aerothermodynamics of a hypersonic vehicle with a surface discontinuity of gap type." Instituto Nacional de Pesquisas Espaciais (INPE), 2017. http://urlib.net/sid.inpe.br/mtc-m21b/2017/05.23.23.55.

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The development of hypersonic vehicles has become a topic of interest in recent years, since has made it possible to reach inaccessible places such as orbital flights. The construction of these vehicles must be made with specials materials, and must have an efficient aerodynamic shape to withstand high speeds, high temperatures and significant pressure changes. The study described in this dissertation was undertaken with the objective to investigate the impact of discontinuities present on the surface of hypersonic space vehicles. In pursuit of this goal, computational simulations of a low-den

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33

Lewis, Daniel Russell. "Tip clearance and angle of attack effects upon the unsteady response of a vibrating flat plate in crossflow." Thesis, Virginia Tech, 1993. http://hdl.handle.net/10919/43198.

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<p>The influence of tip clearance and angle of attack upon the mid-span unsteady pressure response of a vibrating flat plate was investigated experimentally. Unsteady pressure measurements were taken for a variety of incidence angles, vibration frequencies and tip clearances over a Mach number range of 0.2 to 0.6.</p> <p> It was found that changes in tip clearance had an effect on measured pressure fluctuations at higher angles of attack and larger Mach numbers. It was also observed that the amplitude of the unsteady pressure increased as the incidence angle was increased.</p> <p> The plate wa

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34

Lewis, Daniel Joseph. "Tip clearance and angle of attack effects upon the unsteady response of a vibrating flat plate in crossflow /." This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-06112009-063924/.

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35

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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36

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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37

Webb, Charles. "Separation and Vorticity Transport in Massively-Unsteady Low Reynolds Number Flows." Wright State University / OhioLINK, 2009. http://rave.ohiolink.edu/etdc/view?acc_num=wright1244864717.

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38

Najarzadegan, Farshid. "Circulation Dependence of the Interaction Between a Wing-Tip Vortex and Turbulence." UKnowledge, 2019. https://uknowledge.uky.edu/me_etds/145.

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Vortices are present in many fluid flows and depending on the context they may be either beneficial or harmful for different systems or processes. Planar particle image velocimetry was used to examine the vortex evolution and its decay under different turbulence intensities and vortex circulation. The vortex decayed faster in the presence of high turbulence intensity. Vortex trajectories were impacted by turbulence intensity and vortex strength. Trajectories with no turbulence intensity had less variation. The vortex wandering amplitude decreased with growth of vortex strength. The vortex deca

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39

Findlay, David Bruce. "A numerical study of aircraft empennage buffet." Diss., Georgia Institute of Technology, 1999. http://hdl.handle.net/1853/10926.

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40

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.

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The objective of the present research is to investigate unsteady aerodynamic models with state equation representations that are valid up to the high angle of attack regime with the purpose of evaluating them as computationally affordable models that can be used in conjunction with the equations of motion to simulate wing rock. The unsteady aerodynamic models with state equation representations investigated are functional approaches to modeling aerodynamic phenomena, not directly derived from the physical principles of the problem. They are thought to have advantages with respect to the physic

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41

Mogili, Prasad. "RANS and DES computations for a three-dimensional wing with ice accretion." Master's thesis, Mississippi State : Mississippi State University, 2004. http://library.msstate.edu/etd/show.asp?etd=etd-07102004-145100.

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42

Reuter, William H. Howard Richard M. Hobson Garth V. Buning Pieter G. "Flowfield computations over the space shuttle Orbiter with a proposed canard at a Mach number of 5.8 and 50 degrees angle of attack /." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School; Available from the National Technical Information Service, 1993. http://handle.dtic.mil/100.2/ADA258058.

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Thesis (Degree of Aeronautical and Astronautical Engineer) Naval Postgraduate School, June 1993.<br>Thesis advisors, Richard M. Howard, Garth V. Hobson and Pieter G. Buning. AD-A258 058. Includes bibliographical references. Also available online.

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43

Reuter, William H. IV. "Flowfield computations over the space shuttle Orbiter with a proposed canard at a Mach number of 5.8 and 50 degrees angle of attack." Thesis, Monterey, California. Naval Postgraduate School, 1993. http://hdl.handle.net/10945/39837.

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44

Lapinskas, Vytautas. "Sklandytuvo atakos ir slydimo kampų matavimo metodų tyrimas." Master's thesis, Lithuanian Academic Libraries Network (LABT), 2011. http://vddb.laba.lt/obj/LT-eLABa-0001:E.02~2011~D_20110615_175706-86724.

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Baigiamajame magistro darbe atliekamas sklandytuvo atakos ir slydimo kampo matavimo metodų tyrimas. Pirmoje darbo dalyje apžvelgiami atakos kampo matuokliai: virvutė, pritvirtinta ant stiklinio gaubto, atakos – slydimo kampo matuoklis su vėjarodžiu ir Pitoto vamzdelio tipo daviklis. Davikliai palyginami, aprašomi jų privalumai ir trūkumai lyginant su kitais davikliais. Antroje dalyje aprašomi alfa ir beta kampų matavimo metodai: matavimas vamzdelio tipo davikliu ir metodas, kai nenaudojami specialūs atakos, slydimo kampo davikliai. Toliau apžvelgiami veiksniai, turintys įtakos matavimo tikslum

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45

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.

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The spatial stability of hypersonic conical boundary layers is investigated utilizing different numerical techniques. First, the development and verification of a Linearized Compressible Navier-Stokes solver (LinCS) is presented, followed by an investigation of different effects that affect the stability of the flow in free-flight/ground tests, such as: high-enthalpy effects, wall-temperature ratio, and three-dimensionality (i.e. angle-of-attack). A temporally/spatially high-order of accuracy parallelized Linearized Compressible Navier-Stokes solver in disturbance formulation was developed, v

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46

Gomes, Lara Elena. "Comparação entre forças propulsivas efetivas calculadas e medida durante um palmateio de sustentação." reponame:Biblioteca Digital de Teses e Dissertações da UFRGS, 2010. http://hdl.handle.net/10183/27677.

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A força propulsiva gerada durante o palmateio é resultado do somatório das forças de arrasto e de sustentação, sendo que a componente que atua na direção do movimento desejado é igual à força propulsiva efetiva. Essas forças podem ser estimadas a partir de equações hidrodinâmicas, porém essas equações não consideram todos os mecanismos que contribuem para a propulsão. Dessa forma, o objetivo geral do presente estudo foi comparar a força propulsiva efetiva calculada a partir das equações hidrodinâmicas e a força propulsiva efetiva medida durante o palmateio de sustentação (na posição vertical,

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47

Morrison, Thomas M. "THE USE OF TELEMETRY DATA IN AN AIR DATA SYSTEM." International Foundation for Telemetering, 2006. http://hdl.handle.net/10150/604135.

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ITC/USA 2006 Conference Proceedings / The Forty-Second Annual International Telemetering Conference and Technical Exhibition / October 23-26, 2006 / Town and Country Resort & Convention Center, San Diego, California<br>Telemetry data are usually collected for analysis at some later time and can be monitored to follow the progress of a test. In the case of an Air Data System the signals from the sensors are sent to a computer that calculates the air data parameters for use on multiple LabView-generated displays, as well as to the Data Acquisition System. The readouts on the multiple displays ne

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48

BRANDL, ALBERTO. "Techniques for effective virtual sensor development and implementation with application to air data systems." Doctoral thesis, Politecnico di Torino, 2020. http://hdl.handle.net/11583/2842493.

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49

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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50

Mitori, Tiffany Leilani. "Flight and Stability of a Laser Inertial Fusion Energy Target in the Drift Region between Injection and the Reaction Chamber with Computational Fluid Dynamics." DigitalCommons@CalPoly, 2014. https://digitalcommons.calpoly.edu/theses/1154.

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A Laser Inertial Fusion Energy (LIFE) target’s flight through a low Reynolds number and high Mach number regime was analyzed with computational fluid dynamics software. This regime consisted of xenon gas at 1,050 K and approximately 6,670 Pa. Simulations with similar flow conditions were performed over a sphere and compared with experimental data and published correlations for validation purposes. Transient considerations of the developing flow around the target were explored. Simulations of the target at different velocities were used to determine correlations for the drag coefficient and Nus

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