The effect which a slight tilting of the liners of a supersonic wind-tunnel nozzle has on the Mach-number distribution in the test-rhombus is determined on the basis of the linear-perturbation theory of reference [1]. Experiments are reported which (a) confirm that the first-order subsonic and transonic perturbations of the flow may be neglected compared with the supersonic perturbations, and (b) indicate that appreciable effects not accounted for by the first-order theory occur when the flow possesses high local pressure gradients.

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