Theoretical and experimental investigation of aerodynamic-heating and isothermal heat-transfer parameters on a hemispherical nose with laminar boundary layer at supersonic Mach numbers

Abstract

Note presenting a determination of the effect of a strong, negative pressure gradient on the local rate of heat transfer through a laminar boundary layer on the isothermal surface of an electrically heated, cylindrical body of revolution with a hemispherical nose from wind-tunnel tests at a Mach number of 1.97. Results regarding pressure distributions, temperature distributions and recovery factor, and heat transfer are provided.