Surface temperature effect on subsonic stall.

This paper presents the results of an analytical and experimental study of boundary-laye r flow over an aerodynamic surface rejecting heat to a cool environment. Analytical studies involving both laminar and turbulent boundary layers revealed that a surface to freestream temperature ratio, TWIT^9 greater than unity tended to destabilize the boundary layer, hastening transition and separation. The boundary-layer displacement thickness was found to increase in direct proportion to TwjT-fJ while the momentum thickness remained unaffected. The effect of heat transfer was to accentuate the effect of an adverse pressure gradient. Windtunnel tests of 0012-64 NACA airfoil showed that the stall angle was significantly reduced while drag tended to increase for T^T^ up to 2.2.

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