Abstract
Flight-derived aerodynamic heat-transfer data for the Shuttle Orbiter wing lower surface, from STS-2, -3, and -5, are presented and compared with both ground-based experimental results and state-of-the-art computational flowfield results for a nominal angle of attack of 40 deg. The flight data clearly show the development of the interference heat-transfer region on the wing lower surface resulting from the downstream effects of the bowshock/wing-shock interaction. The location of the interference region is well correlated with a region of minimum static enthalpy near the boundary-layer edge as predicted by a three-dimensional, inviscid flowfield computation. The magnitude of the interference heat transfer is no greater than the undisturbed laminar heat transfer occurring during the peak aerodynamic heating portion of re-entry.
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