A nonlinear theory for predicting the effects of unsteady laminar, turbulent, or transitional boundary layers on the attenuation of shock waves in a shock tube with experimental comparison

Robert L. Trimpi, Nathaniel B. Cohen
Sep 1958

The linearized attenuation theory of NACA Technical Note 3375 is modified in the following manner: (a) an unsteady compressible local skin-friction coefficient is employed rather than the equivalent steady-flow incompressible coefficient; (b) a nonlinear approach is used to permit application of the theory to large attenuations; and (c) transition effects are considered. Curves are presented for predicting attenuation for shock pressure ratios up to 20 and a range of shock-tube Reynolds numbers.

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