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- W1973669969 abstract "Flow-field measurements are presented for a symmetrical NACA 64A010 airfoil section at transonic conditions. Measurements were obtained for three angles of attack with the free-stream Mach number fixed at 0.8. The cases studied included a weak shock wave/boundary layer interaction, an interaction of medium strength with mild separation, and an interaction of sufficient strength to produce a shock-induced stall situation. Two nonintrusive optical techniques, laser velocimetry and holographic interferometry, were used to characterize the flows. The results include Mach number contours and flow angle distributions in the inviscid flow regions, and turbulent flow properties, including the turbulent Reynolds stresses, of the upper surface viscous layers, and of the near-wake. The turbulent flow measurements reveal that the turbulence fluctuations attain equilibrium with the local mean flow much faster than previously expected." @default.
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- W1973669969 date "1978-07-10" @default.
- W1973669969 modified "2023-09-23" @default.
- W1973669969 title "Transonic flow about a two-dimensional airfoil inviscid and turbulent flow properties" @default.
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- W1973669969 doi "https://doi.org/10.2514/6.1978-1117" @default.
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