Book Description

The integral method has been applied to determine the downstream influence of homogeneous mass transfer in the stagnation region of a blunt, axisymmetric body under hypersonic flight conditions. Exponential profiles are employed in an attempt to eliminate singularities which have appeared in previous analyses utilizing polynomial profiles. These singularities arise in the presence of a favorable pressure gradient when the density at the surface is comparable t that in the external stream. The results indicate that the singularities occurring in the application of the integral method using polynomial profiles do not arise in the present analysis utilizing exponentials. The heat transfer rates obtained are compared to experimental data and are found to predict the downstream effect of the mass injection reasonably well if the results are normalized with respect to the zero mass transfer prediction. The effect, on the heat transfer rates, of varying the coolant temperature and the injection area are also investigated. It is found that decreasing the coolant temperature or increasing the injection area result in a decrease in the peak heat rate and over-all heat transferred to the body. (Author).