Experimental evaluation of shockless supercritical airfoils in cascade

Experimental evaluation of shockless supercritical airfoils in cascade

Surface Mach number distributions, total pressure loss coefficients, and schlieren images of the flow are presented over a range of inlet Mach numbers and air angles. Several different trailing edge geometries were tested. At design conditions a leading edge separation bubble was observed resulting...

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Hauptverfasser: Boldman, D. R., Buggele, A. E., Shaw, L. M.
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creator Boldman, D. R.
Buggele, A. E.
Shaw, L. M.
description Surface Mach number distributions, total pressure loss coefficients, and schlieren images of the flow are presented over a range of inlet Mach numbers and air angles. Several different trailing edge geometries were tested. At design conditions a leading edge separation bubble was observed resulting in higher losses than anticipated. The minimum losses were obtained at a negative incidence condition in which the flow was accelerating over most of the supercritical region. Relatively minor differences in losses were measured with the different trailing edge geometries studied.
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title Experimental evaluation of shockless supercritical airfoils in cascade
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