Experimental Study of the Heat Transfer at Compressible Gas Flow with a Favorable Pressure Gradient

The parameters of heat transfer at compressible gas flow with a favorable pressure gradient have been experimentally studied. The heat transfer coefficients and the temperature of thermally insulated (adiabatic) wall are determined using the transient heat transfer method. To estimate the degree of flow laminarization, the results obtained are compared with the known dependences for the turbulent boundary layer developing on a plate in a zero-pressure gradient flow. Some regularities of the effect of flow acceleration on the heat transfer law are revealed for the studied configurations of supersonic nozzles.