Possible Types of Flow at Swept Leading Edges-Reference-Cited by-同舟云学术

Possible Types of Flow at Swept Leading Edges

Published:1964-02 Issue:1 Volume:15 Page:72-82
ISSN:0001-9259
Container-title:Aeronautical Quarterly
language:en
Short-container-title:Aeronautical Quarterly

Author:

Stanbrook A.,Squiref L. C.

Abstract

SummaryExisting experimental data on the occurrence of attached flow around the leading edges of swept plane thin wings is summarised. It is shown that the change from separated to attached flow occurs while the Mach number normal to the leading edge is subsonic and that the Mach number required for the change increases with incidence. It is also shown that the Mach number and incidence conditions which hold on the boundaries dividing the two types of flow on wings with straight edges also apply locally at points on the leading edges of “Gothic” wings. The implications of this result on the flow over general curved-edge wings is briefly discussed.

Publisher

Cambridge University Press (CUP)

Subject

General Engineering

Reference8 articles.

1. Larsson P. O. A Note on Supersonic and Transonic Flow Around Delta Wings. Seminar on Wind-Tunnel Techniques and Aerodynamics. Royal Institute of Technology, Stockholm. May 1954.

2. Lindsey W. F. and Landrum E. J. Compilation of Information on the Transonic Attachment of Flows at the Leading Edges of Airfoils. N.A.C.A. T.N. 4204, February 1958.

3. Henshall B. D. Observations of the Flow Past a Two-Dimensional 4 per cent Thick Bi-convex Aerofoil at High Subsonic Speeds. R. & M. 3092, 1957.

4. Hall I. M. and Rogers E. W. E. The Flow Pattern on a Tapered Swept-Back Wing at Mach Numbers Between 0·6 and 1·8. R. & M. 3271, 1957.

5. Squire L. C. , Jones J. G. and Stanbrook A. An Experimental Investigation of the Characteristics of Some Plane and Cambered 65° Delta Wings at Mach Numbers from 0·7 to 2·0 . R. & M. 3305, 1961.

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