| Summary: | A numerical study is performed for a sonic jet issuing from a blunted cone to provide possible directional control in
supersonic crossflow by solving the unsteady Reynolds-averaged Navier-Stokes (RANS) equations with the twoequation
k −ω turbulence model. Results are presented in the form of static aerodynamic coefficients, computed at
a free stream Mach number 4.0, with varying pressure ratios, incidence angle and keeping zero yaw and roll angles.
The morphology and flow structure for the jet exhausting in crossflow at various pressure ratios is described in
detail. The Flight control of the projectile can be accomplished by taking advantage of a complex shock-boundary
layer interaction produced by jet interacting with the oncoming crossflow by altering pressure distribution in vicinity
of the jet, a net increase in the net force can be utilized for maneuvering of vehicle and possible flight control.
Computed static aerodynamic coefficients and pressure distribution using CFD analyses is with an accuracy of ± 5%
in the supersonic range.
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