Robert L. Trimpi

Nathaniel B. Cohen

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 data 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 2.5 x 106

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

William L. Grose

Charts for the Analysis of Isentropic One-dimensional Unsteady Expansions in Equilibrium Real Air with Particular Reference to Shock-initiated Flows

Linwood B. Callis

A Modification to the Expansion Tube

A Perfect-gas Analysis of the Expansion Tunnel

United States. National Advisory Committee for Aeronautics

A. E. Potter

Alfred Gessow

Bernard Lubarsky

Harry L. Runyan

Kenneth Margolis

Leslie W. Lassiter

M. J. Queijo

Richard E. Kuhn

A. P. Young

Donald S. Woolston

Harvey H. Hubbard

John W. Draper

Percy J. Bobitt

Robert J. Tapscott

Samuel J. Kaufman

A. D. Schwope

A. Gerald Rainey

Theoretical and Experimental Investigation of the Effect of Tunnel Walls on the Forces on an Oscillating Airfoil in Two-dimensional Subsonic Compressible Flow

Robert L. Trimpi

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