Aerodynamic Heating of a Hypersonic Projectile with Forward-Facing Ellipsoid Cavity at Nose-Reference-Cited by-同舟云学术

Aerodynamic Heating of a Hypersonic Projectile with Forward-Facing Ellipsoid Cavity at Nose

Published:2015-01 Issue:1 Volume:52 Page:157-165
ISSN:0022-4650
Container-title:Journal of Spacecraft and Rockets
language:en
Short-container-title:Journal of Spacecraft and Rockets

Author:

Yadav Rajesh¹,Guven Ugur¹

Affiliation:

1. Aerospace Engineering, University of Petroleum and Energy Studies, Dehradun 248 007, India

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Space and Planetary Science,Aerospace Engineering

Link

https://arc.aiaa.org/doi/pdf/10.2514/1.A32605

Reference19 articles.

1. AndersonJ. D., Hypersonic and High Temperature Gas Dynamics, McGraw–Hill, New York, 1989, pp. 250–258.

2. CooperM.BeckwidthI. E.JonesJ. J.GallagherJ. “Heat Transfer Measurements on a Concave Hemispherical Nose Shape with Unsteady-Flow Effects at Mach Numbers of 1.98 and 4.95,” NACA RM-L58D25a, July 1958, pp. 250–258.

3. HopkoR. H.StraussH. K. “Some Experimental Heating Data on Convex and Concave Hemispherical Nose Shapes and Hemispherical Depression on a 30° Blunted Nose Cone,” NACA RM-L58A17a, March 1958.

4. StallingsR. L.BurbankP. B. “Heat Transfer and Pressure Measurements of a Concave Nose Cylinder for a Mach Number Range of 2.49 to 4.44,” NASA TM-X-221, Oct. 1959.

5. Experimental and numerical study of hypersonic forward-facing cavity flow

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