The Prediction of Aerofoil Pressure Distributions for Sub-Critical Viscous Flows-Reference-Cited by-同舟云学术

The Prediction of Aerofoil Pressure Distributions for Sub-Critical Viscous Flows

Published:1970-08 Issue:3 Volume:21 Page:291-302
ISSN:0001-9259
Container-title:Aeronautical Quarterly
language:en
Short-container-title:Aeronautical Quarterly

Author:

Lock R. C.,Wilby P. G.,Powell B. J.

Abstract

SummaryThe paper first describes an approximate method for calculating inviscid flows round arbitrary aerofoils at sub-critical Mach numbers, based on second-order theory with empirical improvements to give better agreement with exact theory; several comparisons are shown. This method is then used as the basis of an iterative procedure for calculating the effect of the boundary layer on the surface pressures and overall forces; several comparisons are given with recent experimental results.

Publisher

Cambridge University Press (CUP)

Subject

General Engineering

Reference10 articles.

1. Labrujere T. E. , Loeve W. and Slooff J. W. An approximate method for the determination of the pressure distribution on wings in the lower critical speed range. AGARD Conference Proceedings 35-17, 1968.

2. Nieuwland G. Y. Transonic potential flow around a family of quasi-elliptical aerofoil sections. NLR (Amsterdam) Technical Report T 172, 1967.

3. Powell B. J. The calculation of the pressure distribution of a thick cambered aerofoil at subsonic speeds including the effect of the boundary layer. NPL Aero Report 1238, ARC 29 300—FM 3867—Perf 2631—PA 1236, June 1967.

4. Incompressible Aerodynamics

5. Method for predicting the pressure distributions on swept wings with subsonic attached flow. Royal Aeronautical Society Transonic Data Memo. 6312, 1963.

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