Department of Aeronautics and Fluid Mechanics, University of Glasgow
Abstract
The effect of heat conduction of material on the temperature
distribution in the vicinity of a wing leading edge in hypersonic flight is
investigated. The theory is based on a conducting plate subjected to
aerodynamic heating. It is found that the role played by the conductivity
of the material and the leading edge thickness in moderating the nose
temperature is very significant. Detailed discussions of the numerical
solutions for various shapes of leading edge are given. An experimental
technique has been developed by which a number of models representing a wing
leading edge can be tested and the results thus obtained are compared with
those predicted by the theory
