An experimental study of the lift and pressure distribution on a double-wedge profile at Mach numbers near shock attachment

Walter G. Vincenti, Duane W. Dugan, E. Ray Phelps
naca-tn-3225
Jul 1954


An account is given of wind-tunnel measurements at low supersonic speeds of the pressure distribution on a doubly symmetrical double-wedge profile of approximately 8-percent thickness. The results cover the Mach number range form 1.166 to 1.377, which brackets the value (1.221) given by exact inviscid theory for attachment of the shock wave to the leading edge at zero angle of attack.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1954/naca-tn-3225.pdf