Radiation Cooling of Thrust Nozzles,
ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT PARIS (FRANCE)
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Various heat transfers by radiation occur on the wall of a propulsion system between each point on the outer surface and the ambient space, between various points on the outer surface, between the outer surface and a wall perpendicular to its axis, between the outer surface and any wall, between various points on the inner surface, and between each point on the inner surface and the outer space through the exit aperture. This study is concerned with the calculation of such heat transfers in axysymmetrical thrust nozzles, to obtain the functions for exchanges between isothermal lines on the surface of revolution or plane cross-sections slightly inclined to the parallel lines. The numerical results are given in the form of universal functions of the geometrical parameters for the meridian. In the case of the diagrammatic configurations for the most usual type of nozzles the directly usable values of the transfer functions are quoted.
- Solid Propellant Rocket Engines