Measurements of the effects of finite span on the pressure distribution over double-wedge wings at Mach numbers near shock attachment
Description: Report presenting results of wind-tunnel measurements of the pressure distribution at low supersonic speeds on two rectangular wings of double-wedge section and aspect ratios 2 and 4. The pressure-drag coefficient at zero lift is found to decrease with decrease in aspect ratio at all values of the test Mach number. The effect was found to be most pronounced at Mach numbers at which the shock wave is detached.
Date: September 1955
Creator: Vincenti, Walter G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department