DISTORTION OF A SUPERSONIC TURBULENT BOUNDARY LAYER BY BULK COMPRESSION AND SURFACE CURVATURE.

An experimental investigation of a supersonic turbulent boundary layer experiencing the effects of bulk compression and streamline curvature is described. The incoming boundary layer had a Mach number of 2. 87 and a unit Reynolds number of 6. 3 multiplied by 10**7/m. Two different, constant-radius curved-wall models were used. Dramatic increases in the turbulent normal and shear stresses were observed. The amplification of the normal stress was about the same in both models, whereas the amplification of the shear stress was greater in Model I compared with Model II.