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Convective Heating at the Deflecting Surface of a Rocket Launch-Pad

Published online by Cambridge University Press:  04 July 2016

G. Jepps  and
M. L. Robinson
G. Jepps
Affiliation:
Weapons Research Establishment
M. L. Robinson
Affiliation:
Weapons Research Establishment
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Summary:

When a large rocket or missile is fired, the hot exhaust gases must be allowed to escape without damaging structures or equipment in the vicinity of the firing area. Generally, the exhaust gases are directed harmlessly away from the launching installation by water-cooled deflecting surfaces fabricated in steel. In arid areas such as Woomera, where water is not available in large quantities, there is the possible danger that a steel efflux deflector will melt, and other materials such as refractories may be more suitable for the deflecting surface.

To provide data for the design of uncooled efflux deflectors, a heating rate investigation of the Blue Streak installation at Woomera has been carried out theoretically and experimentally. The heat transfer coefficient and stagnation temperature at the efflux deflecting surface are calculated theoretically with the aid of model test results. Heat transfer coefficients derived from temperature measurements on steel plates embedded in the deflecting surface are compared with the theoretical results. It is concluded that simple aerodynamic heat transfer theory can provide an effective engineering estimate of the temperature rise of an efflux deflecting surface.

Type
Research Article
Information
The Aeronautical Journal , Volume 71 , Issue 679 , July 1967 , pp. 469 - 475
Copyright
Copyright © Royal Aeronautical Society 1967

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References

1.van Driest, E. R. The Problem of Aerodynamic Heating. Aeronautical Engineering Review, October 1956.Google Scholar
2.Eckert, E. R. G. Survey of Heat Transfer at High Speeds. WADC Tech Rep 54-70, April 1954.Google Scholar
3.Anderson, A. R. and Johns, F. R.Characteristics of Free Supersonic Jets Exhausting into Quiescent Air. Jet Propulsion, Vol 25, No 1, January 1955.CrossRefGoogle Scholar
4.Richards, T. E. Use of the RTV 1 Rocket Motor Exhaust Jet to Simulate Aerodynamic Heating. WRE TN PD41, February 1960.Google Scholar
5.Evans, R. L. and Sparks, O. L. launch Deflector Design Criteria and their Application to the Saturn C-l Deflector. NASA TN D-1275, March 1963.Google Scholar
6.Handbook of Supersonic Aerodynamics. Navord Report 1488, Vol 5, US Government Printing Office, Washington, August 1953.Google Scholar
7.Smithells, C. J.Metals Reference Book, Vol 2. Butterworths Scientific Publications, London, 1955.Google Scholar
8.Jepps, G. Some Approximate Solutions for Heat Conduction in Walls Heated Convectively. WRE Report HSA 21, February 1966.Google Scholar
9.Schlichting, H.Boundary Layer Theory, Fourth Edition, p 552. McGraw-Hill Book Company Inc, New York, 1960.Google Scholar