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美国政府科技报告
>AN EXPERIMENTAL INVESTIGATION OF THE ZERO-LIFT PRESSURE DISTRIBUTION OVER A WEDGE AIRFOIL IN CLOSED, AND OPEN-THROAT –TUNNELS AT TRANSONIC MACH NUMBERS
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AN EXPERIMENTAL INVESTIGATION OF THE ZERO-LIFT PRESSURE DISTRIBUTION OVER A WEDGE AIRFOIL IN CLOSED, AND OPEN-THROAT –TUNNELS AT TRANSONIC MACH NUMBERS
Pressure distributions and schlieren photographs of the flow about a 10-percent-thick diamond airfoil at zero lift in two-dimensional' closed, slotted, and open-throat tunnels are presented and discussed. Uncorrected airfoil pressures obtained in 1/5 and 1/8 open slotted throat tunnels are compared at subsonic Mach numbers with corrected results from open and closed test sections of the same dimensions. The effect of varying the slot width has been investigated at Mach numbers up to 0.92. At Mach numbers up to 1.18, data obtained in test sections whose upper and lower boundaries were slotted to provide openings the combined width of which was equal to one-eighth of the tunnel width, are shown to be consistent with theory and available experiments.
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