Determination of boundary reflected disturbance lengths in the Langley 16-foot transonic tunnel | ORKG Ask

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Investigation at Mach numbers from 0.80 to 1.43 of pressure and load distributions over a thin 45©� sweptback highly tapered wing in combination with basic and indented bodies /

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Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number...

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Fischetti, Thomas L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1957

Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number...