Reynolds number effect on vortex dominant flow on the SST configurations

Numerical studies were performed to understand the Reynolds number effect at high angles of attack and low-speed flight conditions for supersonic aircraft configurations where vortex flow dominates overall flow field. Two aircraft configurations were used; one is a simple geometry consisting of the wing and body, and other is complex geometry consisting of the wing, body and tails. The RANS computations were conducted at several Reynolds number from experimental test conditions to flight conditions. The Reynolds number effects were strongly observed at wing and tail plane. Especially, the flow separation and vortex formation at the leading edge was depended on the Reynolds number. The flow at the tail plane obviously changed by Reynolds number. Because, the flow at the tail was interacted with the leading edge separated vortex oriented from the main wing which trajectory depends on the Reynolds number. Those Reynolds number effects caused by the vortex behaviors were induced to the nonlinear change of the aerodynamics.