Surface temperature effect on subsonic stall.Results of an analytical and experimental study of boundary layer flow over an aerodynamic surface rejecting heat to a cool environment. This occurs following reentry of a Space Shuttle vehicle. Analytical studies revealed that a surface to freestream temperature ratio, greater than unity tended to destabilize the boundary layer, hastening transition and separation. Therefore, heat transfer accentuated the effect of an adverse pressure gradient. Wind tunnel tests of a 0012-64 NACA airfoil showed that the stall angle was significantly reduced while drag tended to increase for freestream temperature ratios up to 2.2.
Document ID
19720058691
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Macha, J. M.
Norton, D. J. (Texas A & M University College Station, Tex., United States)
Young, J. C. (NASA Manned Spacecraft Center Aerodynamics and Entry Section, Houston, Tex., United States)