Note on the Prediction of the Local Flow Conditions at the Crest of an Aerofoil Section in a Sonic Stream-Reference-Cited by-同舟云学术

Note on the Prediction of the Local Flow Conditions at the Crest of an Aerofoil Section in a Sonic Stream

Published:1966-03 Issue:663 Volume:70 Page:444-446
ISSN:0368-3931
Container-title:The Journal of the Royal Aeronautical Society
language:en
Short-container-title:J. R. Aeronaut. Soc.

Author:

Thompson N.

Abstract

The pressure distribution on the surface of an aerofoil section at near sonic speeds is not sensitive to small changes in free-stream Mach number, and the distribution at M0=1.0 is often referred to as the sonic-range pressure distribution. Attempts to predict this form of pressure distribution have met with some success in the past, the work of Spreiter and Alksne, using an approximate solution of the non-linear equations of transonic small-disturbance theory, being of particular note. Reference 1 demonstrated the application of this theory to a family of non-lifting, sharp-nosed aerofoils and found good agreement with experiment at free-stream Mach numbers close to unity.

Publisher

Cambridge University Press (CUP)

Reference8 articles.

1. Michel R. , Marchaud F. and Legallo J. Influence de la Position du Maitre-Couple sur les Écoulements Transsoniques Autour de Profils a Pointes. ONERA Pub 72, 1954.

2. Gibbings J. C. A Correlation of Some Transonic Aerodynamic Characteristics of Two-Dimensional Symmetrical Aerofoils at Zero Incidence. ARC Report 22 744, March 1961.

3. Randall D. G. Transonic Flow over Two-Dimensional Round-Nosed Aerofoils. RAE TN Aero 2579, September 1958.

4. Spreiter J. R. and Alksne A. Y. Thin Airfoil Theory Based on Approximate Solution of the Transonic Flow Equation. NACA Report 1359, 1958

5. Boundary Layer Effect on Local Mach number Measurements on a Circular-Arc Half Profile;Carroll;Journal of the Aeronautical Sciences,1956