In order to estimate the change in effectiveness of the jet in providing control forces and moments

force-testing and oil-flow tests were carried out in 2m×2m supersonic wind tunnel. The effects of a number of parameters such as the angle of attack

jet to crossflow static pressure ratio (PR) and nozzle location

were studied. Mach number ranged from 1.5 to 4.0

angle of attack from -8° to 27°

and pressure ratio from 5 to 17.6. Numerical simulation was performed and compared with tests to obtain streamlines on the surface and interaction flowfield near nozzle exit. Pitching motion effect of the missile model on jet interaction was also investigated. Result showed that the effectiveness was enhanced for the conditions considered

as the nozzles were located at the rear body; larger crossflow Mach number resulted in more drastic change with the changing angle of attack. Interaction amplification factors decreased with the increasing PR; upward jet had greater effect than downward jet. In addition

the transverse jet interaction during pitching oscillation was obviously different from the steady interaction

especially during pitching down motion and at high angle of attack. Basic aerodynamic characteristics as well as force and moment amplification factors showed hysteresis properties. Motion effect should be considered when applying the combined utilization of transverse jet and traditional fin technique.