A NONLINEAR THEORY FOR PREDICTING THE EFFECTS OF UNSTEADY LAMINAR, TURBULENT, OR TRANSITIONAL BOUNDARY LAYERS ON THE ATTENUATION OF SHOCK WAVES L:4 SHOCK TUBE WITH EXPERIMENTAL COMPARISON

摘要

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. Comparison of theory and experimental dala for shock-wave strengths between 1.5 and, 10 over a wide range of Reynolds numbers shows good, agreement with the nonlinear theory evaluated, for a transition Reynolds number of 2.5X106.