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- W2029671458 abstract "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." @default.
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- W2029671458 date "1983-01-10" @default.
- W2029671458 modified "2023-10-16" @default.
- W2029671458 title "Experimental evaluation of shockless supercritical airfoils in cascade" @default.
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- W2029671458 doi "https://doi.org/10.2514/6.1983-3" @default.
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