An Experiment on Compressible-Flow Perturbations
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Abstract 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.
1970 ◽
Vol 317
(1531)
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pp. 545-574
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2015 ◽
Vol 57
(2)
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pp. 157-185
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1971 ◽
Vol 3
(3)
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pp. 271-362
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1963 ◽
Vol 14
(2)
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pp. 148-155
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