Abstract: The interaction between supersonic external flow and an exhaust jet forms a complex flowfield region near the missile afterbody. In this paper, the research about this interaction flows was completed with finite-difference method to solve N-S equations. The flowfield structures observed in experiment and it's relation with jet pressure ratio p_j/p_∞ were obtained. For freestream, M_∞=1.94, R_e∞=2.2×10⁵, for jet flow, M_j=3.0, three p_j/p_∞(1.03, 0.527 and 0.15) were selected. The numerical algorithm used is a modified Beam-Warming scheme. The nozzle base pressure coeficient and shock reflection length were compared with experimental data, good agreements were reached.

Key words: jet flow, wake flow, numerical simulation