Measurements of skin friction on a cambered delta wing at supersonic speeds

The measurements, using razor blade surface pitot tubes, show that the relatively mild pressure gradients and streamline convergence on the wing have a large effect on local skin friction. Application of the boundary layer momentum equation suggests that the change in skin friction arises directly from changes in the boundary layer profile....

The use of surface pilot tubes as skin friction meters at supersonic speeds

Experiments have been made, in supersonic turbulent boundary layers, on a simple type of surface pitot tube, formed by cementing a piece of razor blade over a statie pressure hole. This type of surface pitot tube has great practical advantages, as surface shear measurements may be made on any model designed for pressure measurements. A...

Boundary layer growth in the nozzles of the R.A.E. 8 ft. x 8 ft. supersonic wind tunnel

Results are given for the boundary layer allowance on the walls of the tunnel calculated by the method of Tucker. A preliminary calibration of the working section flow has shown that the calculated values of displacement thickness are correct to within about 5%. The approximate methods of Rogers and Davis and Ruptash are in fair agreement with...