Base-heating measurements on Apollo Block II command module

Lockman, W. K.

doi:10.2514/3.29875

Cited by 7 publications

(3 citation statements)

References 4 publications

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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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Section: Newtonian Impact Theorymentioning

confidence: 99%

Computational Simulations and Applications

Zhu¹

2011

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“…Supersonic near wakes have a trailing shock in the recirculating zone that can increase the base heat transfer rates . Base‐stagnation heat transfer rates of hypersonic vehicles vary from approximately 2% to 5.9% of the forebody stagnation heat flux, whereas the base pressure is of the order of the freestream pressure . Transitional/turbulent shear layers separating from corners of such vehicles can result in a turbulent wake.…”

Section: Introductionmentioning

confidence: 99%

Base heat flux measurement techniques in impulse hypersonic test facilities

Irimpan

Menezes

Srinivasan

2019

Heat Trans. Asian Res.

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Safe and efficient hypersonic missions require exhaustive testing to capture the surface heat flux used in optimizing thermal protection systems. Though low, base heat transfer rates are still relevant and their estimation is of the utmost importance. Impulse hypersonic test facilities like the shock tunnel are commonly used for such estimation tests. The present paper compares contemporary heat flux measurement techniques, namely, E‐type coaxial thermocouples, Pt‐thin films, and atomic layer thermopiles in a hypersonic shock tunnel at the base of a scaled‐down re‐entry capsule. Base flow establishment is ensured using pressure measurements. The measurements indicated that the base‐stagnation point heat flux was approximately 2% to 3% of the forebody stagnation heat flux and it stabilized at an approximate nondimensional establishment time of 43.2 ± 2.4.

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Section: Newtonian Impact Theorymentioning

confidence: 99%