Available Technology

AERO2S - Subsonic Aerodynamic Analysis of Wings With Leading- And Trailing-Edge Flaps In Combination with Canard or Horizontal Tail Surfaces

Subsonic modified linear theory method providing estimates of the longitudinal aerodynamic characteristics of conceptual airplane lifting surface arrangements. The method is particularly well suited to configurations which, because of high speed flight requirements, must employ thin wings with highly swept leading edges. The code is applicable to wings with either sharp or rounded leading edges. The code provides theoretical pressure distributions over the wing, the canard or horizontal tail, and the deflected flap surfaces as well as estimates of the wing lift, drag, and pitching moments which account for attainable leading edge thrust and leading edge separation vortex forces.
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