Wind-tunnel investigation of a number of total-pressure tubes at high angles of attack -- subsonic, transonic, and supersonic speeds

William Gracey
naca-report-1303
jan 1957

The effect of inclination of the airstream on the measured pressures of 54 total-pressure tubes has been determined for angles of attack up to 60 degrees and over a Mach number range from 0.26 to 1.62. The investigation was conducted in five wind tunnels at the Langley Aeronautical Laboratory.

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