HEAT TRANSFER IN SUPERSONIC COMBUSTION PROCESSES
The momentum-integral method of solution for turbulent boundary layers has been extended to obtain heat transfer in supersonic flows with chemical reactions. An integral solution of the boundary layer equations is obtained simultaneously with a pseudo-one dimensional solution for heat addition in supersonic flow to obtain local heat transfer coefficients. Results from the analysis are compared with experimental measurements obtained in an arc heated supersonic flow with gaseous hydrogen combustion. Reasonable agreement between theory and experiment is shown. Data are presented for both cross-stream, discrete-hole injection and partially downstream injection from a narrow circumferential slot.