Lift Hysteresis at Stall as an Unsteady Boundary-Layer Phenomenon
Description:
"Analysis of rotating stall of compressor blade rows requires specification of a dynamic lift curve for the airfoil section at or near stall, presumably including the effect of lift hysteresis. Consideration of the Magnus lift of a rotating cylinder suggests performing an unsteady boundary-layer calculation to find the movement of the separation points of an airfoil fixed in a stream of variable incidence. The consideration of the shedding of vorticity into the wake should yield an estimate of …
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Date:
August 17, 1955
Creator:
Moore, Franklin K.
Item Type:
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Report
Partner:
UNT Libraries Government Documents Department