FINITE-DIFFERENCE METHOD FOR PREDICTING SUPERSONIC TURBULENT BOUNDARY-LAYER FLOWS WITH TANGENTIAL SLOT INJECTION.

An implicit finite-difference method is applied to tangential slot injection into supersonic turbulent boundary-layer flows. In addition, the effects induced by the interaction between the boundary-layer displacement thickness and the external pressure field are considered. Results are compared with experimental data at stream Mach numbers of 2. 4 and 6. 0 and with results of another finite-difference method. Good agreement is generally obtained for the reduction of wall skin friction with slot injection and with experimental Mach number and pilot pressure profiles. Calculations with the effects of pressure interaction included show these effects to be smaller than effects of changing eddy viscosity models.