Hostname: page-component-78c5997874-94fs2 Total loading time: 0 Render date: 2024-11-09T07:25:30.541Z Has data issue: false hasContentIssue false
  • English
  • Français

A two-dimensional air intake in a sonic stream

Published online by Cambridge University Press:  28 March 2006

L. E. Fraenkel
L. E. Fraenkel
Affiliation:
Aeronautics Department, Imperial College, London
Get access Rights & Permissions [Opens in a new window]

Abstract

In this paper transonic small-disturbance theory is applied to a simplified model of the flow near the front of a ducted body. The body is assumed to consist simply of two parallel flat plates which extend from the inlet station to infinity downstream. The velocity far upstream is sonic, and the velocity far downstream in the duct, which is assumed to be known, is slightly subsonic. Air is therefore ‘spilled’ around the intake edges. An analytic solution is found for the resulting flow field up to the ‘limiting Mach wave’, and asymptotic solutions are found for the supersonic flow and for the shock wave far from, and near, the intake edges. The pressure distribution along the outside walls is then known at both ends, and its computation is completed by an empirical procedure. Distributions of pressure along the centre-line and along the inside and outside walls are shown. These results may be used to compute the drag of sharp-edged intakes with a very small frontal area.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 4 , Issue 6 , November 1958 , pp. 629 - 649
Copyright
© Cambridge University Press

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

Barish, D. T. & Guderley, G. 1953 Asymptotic forms of shock waves in flows over symmetrical bodies at Mach one, J. Aero. Sci. 20, 491.
Erdélyi, A. (Ed.) 1953 Higher Transcendental Functions, Vol. 1. New York: McGraw-Hill.
Erdélyi, A. (Ed.) 1954 Tables of Integral Transforms, vol. 1. New York: McGraw-Hill.
Frankl, F. I. 1947 An investigation of the theory of a wing of infinite span moving at the speed of sound, Doklady Akad. Nauk. SSSR (N.S.) 57, 661.Google Scholar
Germain, P. & Bader, R. 1952 Sur quelques problemes relatifs a l’équation de type mixte de Tricomi, O.N.E.R.A. Publication no. 54.Google Scholar
Germain, P. 1957 Lectures on transonic flow at the California Institute of Technology.
Guderley, G. 1948 Singularities at the sonic velocity, Wright-Patterson Air Force Base Tech. Rep. no. F-TR-1171-ND.Google Scholar
Guderley, G. 1954 The flow over a flat plate with a small angle of attack at Mach number one, J. Aero. Sci. 21, 261.Google Scholar
Nonweiler, T. R. F. 1958 The sonic flow about some symmetric half-bodies, J. Fluid Mech. 4, 140.Google Scholar
Spreiter, J. R. 1954 On alternative forms of the basic equations of transonic flow theory, J. Aero. Sci. 21, 70.Google Scholar
Tricomi, F. 1923 Sulle equazioni lineari alle derivate parziali di 2° ordine di tipo misto, Mem. Real. Acad. Lincei; classe Fis. Mat. e. Nat., 14 (5), 133.Google Scholar