NUMERICAL-ANALYSIS FOR SUPERSONIC FLOWS IN A COOLED NOZZLE

Numerical analysis is performed for fluid flows in a supersonic nozzle with cooled walls. The numerical methodology is based on a modified f orm of the SIMPLER algorithm for compressible fluid, coupled with the scheme developed by Karki et al. for a generalized nonorthogonal coord inate system. The geometry of the supersonic nozzle used for calculati ons is a hue-dimensional convergent-divergent configuration formed by linear walls with a diverging angle of 5 degrees downstream of the thr oat. Calculations are performed for the conditions where the inlet tem perature is 1200 K and walls are cooled and kept at 300 K. The back pr essure is set at various values. The adiabatic flows are calculated fo r comparison. The calculated results for the flow with cooled walls ar e compared with the experimental data and agree with each other qualit atively.