Assessment of Store Control Surface Effectiveness in a Non-Uniform Aircraft FlowField

摘要

Comparisons of the control effectiveness for two stores in free stream and in theflow field of a parent aircraft have been performed using computational fluid dynamics (CFD). The computations were performed to assess the changes in control surface effectiveness of the store due to the highly nonlinear flow field of the parent aircraft at transonic speeds. The Navier-Stokes equations were solved using an algebraic turbulence model for an extended range air-to-ground missile (AGM-130A) mounted on the wing pylon of an F-15E aircraft and for an air-to-air missile mounted on the forward station of the inboard pylon of an F-15E aircraft. Free-stream calculations showed good agreement with wind tunnel control surface effectiveness results for both stores. Calculations of control surface effectiveness in the aircraft flow field indicate significant changes occur for the AGM-130A missile while the air-to-air missile showed very little effect. This is attributed to the fact that a large region of separated flow occurs on the lee side of the deflected flap of the AGM-130A while the flow over the air-to-air missile deflected elevator is attached.