Baseflow aerothermal computations for a missile with axisymmetric and canted nozzles

Abstract

A requirement existed to accurately predict missile base flow quantities such as pffiSUre, heat transfer and drag for application to structural and thermal design of the base, and trajectory performance. Predictions were made for both axisymmetric and canted nozzles. The computations were made by exerciziig the appropriate flow options available in the GASP code. Both laminar and turbulent flow cases were computed for the axisymmetric nozzle and only Laminar flow case was computed for the canted nozzle. It was shown that the pressure and heat transfer had consistent trends with each other and that the results from the canted nozzle case made sense when compared to its axisymmtric counterpart. The drag computed here was compared with a computation from MISSILE-DATCOM showing good agreement. U