To gain an insight into the complex flow structure near a supersonic l
ateral jet in a supersonic cross flow, a computational simulation was
carried out using a high-resolution Navier-Stokes solver capable of re
solving both shock waves and shear layers. A novel treatment of the je
t boundary conditions is presented by solving the jet nozzle problem u
sing an isentropic theory. Results are presented for the wind-tunnel t
est cases performed by ONERA, and comparisons are made between the num
erical simulation and the experimental measurement. Major features of
the complicated interaction attributable to the combined effects of th
e jet and the angle of attack are simulated in the computation. Multip
le vortical flow structures are observed near the jet exit, which inte
ract with the vortical flow on the leeward side of the body at relativ
e higher angles of attack.