Comparison of aerodynamic data from the Gemini flights and AEDC-VKF wind tunnels.

Griffith, B. J.

doi:10.2514/3.28988

Cited by 17 publications

(4 citation statements)

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“…In the mid to late 1960's, hypersonic wind-tunnel tests of small scale models were performed. [1][2][3][4] The tests were performed at the Arnold Engineering Development Center (AEDC) in the von Karman Gas Dynamics Facility (VKF) and involved a low density, hypersonic, continuous-flow, arc heated, and ejector-pumped windtunnel called VKF Tunnel L. For this report, the aerodynamics of three small scale models in these windtunnel tests is examined. First, descriptions of the computational approaches are given.…”

Section: Introductionmentioning

confidence: 99%

Assessment of Rarefied Hypersonic Aerodynamics Modeling and Windtunnel Data

Padilla

Boyd

2006

9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference

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Section: Introductionmentioning

confidence: 99%

Assessment of Rarefied Hypersonic Aerodynamics Modeling and Windtunnel Data

Padilla

Boyd

2006

9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference

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“…Another interesting example concerns data obtained in a low-density, hypersonic wind tunnel in the 1960s as part of the Apollo program [63][64][65][66]. A variety of very small models were tested that included cones as well as capsules such as Apollo, Gemini, and Mercury.…”

Section: A Analyses Of Hypersonic Laboratory Experimentsmentioning

confidence: 99%

Computation of Hypersonic Flows Using the Direct Simulation Monte Carlo Method

Boyd

2015

Journal of Spacecraft and Rockets

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The direct simulation Monte Carlo method has evolved over 50 years into a powerful numerical technique for the computation of complex, nonequilibrium gas flows. In this context, "nonequilibrium" means that the velocity distribution function is not in an equilibrium form due to a low number of intermolecular collisions within a fluid element. In hypersonic flow, nonequilibrium conditions occur at high altitude and in regions of flowfields with small length scales. In this paper, the theoretical basis of the direct simulation Monte Carlo technique is discussed. In addition, the methods used in direct simulation Monte Carlo are described for simulation of high-temperature, real gas effects and gas-surface interactions. Several examples of the application of direct simulation Monte Carlo to flows around blunt hypersonic vehicles are presented to illustrate current capabilities. Areas are highlighted where further research on the direct simulation Monte Carlo technique is required. Nomenclature A= surface element of area, m 2 C = particle velocity vector, m∕s e r = specific rotational energy, J∕kg f = probability density function g = relative velocity, m∕s Kn = Knudsen number k = Boltzmann's constant, J∕kg L = characteristic length scale, m m = mass of a particle, kg N = average number of particles in a cell N p = number of particles in a cell N t = number of iterations n = number density, m −3 P c = collision probability r = particle position vector, m T = temperature, K t = time, s V = cell volume, m 3 Δf = rate of change due to collision processes ε act = activation energy, J ε r = rotational energy, J ε tot = total collision energy, J λ = mean free path, m ζ = number of rotational degrees of freedom σ = collision cross section, m 2 τ r = rotational relaxation time, s ω = viscosity temperature exponent

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“…The forebody aerodynamic drag is also computed using Newtonian flow assumptions. The numerical simulation can be validated with the post flight data of the Gemini, Apollo and Star dust flights data (Griffith, 1967;Griffith & Boylan, 1968;Lockman, 1970;& Wood, 1997).…”

Section: Newtonian Impact Theorymentioning

confidence: 99%

Computational Simulations and Applications

Zhu¹

2011

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conference and colloquium presentations in 21 countries. He also served on the editorial boards of six international journals and numerous conference organizing committees. Over the last two decades, his research and education projects have been funded by over $6 million in grants from the USA federal agencies and industrial partners. ContentsPreface XIII Part Research and Numerical Algorithms in Computational Fluid Dynamics Simulations 1 Chapter Reynolds Stress Transport Modelling 3 Sharaf F. Al-Sharif Chapter Study of Some Key Issues for Applying LES to Real Engineering Problems 27 XIV Preface 9 -12), fluid heat exchange (chapter 13 -14), airborne contaminant dispersion over buildings and atmospheric flow around a re-entry capsule (chapter 15 -16), gas-solid two phase flow in long pipes (chapter 17), free surface flow around a ship hull (chapter 18), and hydrodynamic analysis of electrochemical cells (chapter 19).  Part III covers applications of non-CFD based computational simulations, including atmospheric optical communications (chapter 20), environmental studies involving climate system simulations, porous media flow, and combustion (chapter 21 -23), solidification (chapter 24), and sound field simulations for optimal acoustic effects (chapter 25). I am grateful to InTech for the opportunity to serve as the editor for this book, and I wish to sincerely thank all contributing authors around the world for their diligence in following editorial guidelines, their willingness to support open access publications, and their valuable technical contributions that made this book possible. Special thanks are due to Ms. Ana Nikolic, Mr. Zeljko Spalj, and the technical staff at InTech for their editorial efforts, detailed reviews, and professional assistance. I also would like to thank the University of Texas at Arlington for supporting my participation in this book project. Without the support from the authors, InTech staff, and the University, this book could not have become a reality.

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Comparison of aerodynamic data from the Gemini flights and AEDC-VKF wind tunnels.

Cited by 17 publications

References 4 publications

Assessment of Rarefied Hypersonic Aerodynamics Modeling and Windtunnel Data

Assessment of Rarefied Hypersonic Aerodynamics Modeling and Windtunnel Data

Computation of Hypersonic Flows Using the Direct Simulation Monte Carlo Method

Computational Simulations and Applications

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