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A Centrifugal Hypersonic Wind Tunnel Facility for Investigating Effects of Inertia on Ablating Bodies

Published online by Cambridge University Press:  04 July 2016

Joseph Scott Ford II  and
Wilfred H. Horton
Joseph Scott Ford II
Affiliation:
USAF
Wilfred H. Horton
Affiliation:
Stanford University, Stanford, California
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Extract

A most important aspect of space technology is the development of methods for atmospheric re-entry. In this phase of flight very severe structural and material requirements exist. The origin of the problem lies in the intense aerodynamic heating which occurs as the body enters the denser regions of the atmosphere. High stagnation temperatures at the nose, shear effects in the boundary layer, radiation from the hot gas in the shock wave, and heat liberated by the recombination of dissociated and ionised gases give rise to conditions which will result in the destruction of the body unless some form of heat protection is provided.

Type
Research Article
Information
The Aeronautical Journal , Volume 67 , Issue 636 , December 1963 , pp. 745 - 753
Copyright
Copyright © Royal Aeronautical Society 1963

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References

1.Allen, H. J. and Eggers, A. J. Jr. A Study of The Motion and Aerodynamic Heating of Ballistic Missiles Entering the Earth's Atmosphere at High Supersonic Speeds. NACA REP 1381, 1958.Google Scholar
2.Chapman, D. R. An Approximate Analytical Method for Studying Entry Into Planetary Atmospheres. NACA TN 4276, 1958.Google Scholar
3.Stalder, J. R.Re-entry Environments. Materials, Science and Technology for Advanced Applications, p. 215, Edited by Mash, Donald R., Prentice Hall, 1962.Google Scholar
4.Roberts, L., Peters, R. W. and Hopko, R. N. A Discussion of Ablation Research, Langley Research Center, NASA.Google Scholar
5.Cheng, Sin-I. On the Mechanism of Atmospheric Ablation. IX International Aeronautical Congress. Amsterdam 1958.Google Scholar
6.Chapman, Dean R. and Larson, Howard K. The Lunar Origin of Tektites. NASA TN-D-1556, Feb. 1963.Google Scholar
7.Anliker, Max and Beam, R. M.On the Stability of Liquid Layers Spread Over Simple Curved Bodies. Journal of the Aerospace Sciences , Vol. 29, No. 10, Oct. 1962.Google Scholar
8.Nardo, S. V., Erickson, B. and Kempner, J. Experimental Pressure, Temperature and Strain Measurements on Ablating Hemispherical Nose Cones in Hypersonic Flow. PIBAL REP 574, Polytechnic Institute of Brooklyn, July 1961.Google Scholar
9.Feldman, Saul. On the Instability of the Melted Surface of an Ablating Body When Entering the Atmosphere. Journal of Fluid Mechanics, Vol. 6, Part 1, 1959.Google Scholar
10.Cotter, R. A. Manager-Systems Division, Personal Communication, The Rucker Company.Google Scholar
11.Dowling, D. L., Herrick, D. B. and Rose, W. E.Evacuating Large Space Chambers With Positive Displacement Blowers. 1961 Transactions of the Eighth Vacuum Symposium and Second International Congress, Vol. 2, p. 1235.Google Scholar
12.A Large Air Arc for Hypersonic Wind Tunnels. Missile and Space Vehicle Department. The General Electric Company.Google Scholar
13.John, Richard R. and Bade, William L.Recent Advances in Electric Arc Plasma Generation Technology. ARS Journal, Vol. 31, p. 4, 1961.Google Scholar
14.Rose, P. H., Powers, W. E. and Hritzay, D. The Large High Pressure Arc Plasma Generator: A Facility for Simulating Missile and Satellite Re-Entry. AVCO Corp., Research Rep. 56, June 1959.Google Scholar
15.Cordero, Julio, Diederich, F. W., Hurwicz, H.Aerothermodynamic Test Techniques for Re-Entry Structures and Materials. Aerospace Engineering, Vol. 22, No. 1, p. 166, Jan. 1963.Google Scholar
16.Smith, I. L.Pressure Control System for a Hypersonic Wind Tunnel. Engineers Thesis, Aeronautics and Astronautics Dept, Stanford University, January 1963.Google Scholar