Hostname: page-component-cd9895bd7-7cvxr Total loading time: 0 Render date: 2024-12-28T05:53:10.036Z Has data issue: false hasContentIssue false
  • English
  • Français

Recent Advances in the Knowledge of Transonic Air Flow

Published online by Cambridge University Press:  28 July 2016

C. H. E. Warren
C. H. E. Warren*
Affiliation:
Royal Aircraft Establishment, Farnborough
Get access Rights & Permissions [Opens in a new window]

Extract

The most powerful theoretical tool in the solution of the aerodynamic problems of aircraft is the theory of small perturbations, which states that if a wing is thin (or a body slender), and if the incidence is small, then in inviscid flow the fluid velocity at any point can be treated as a small perturbation from the stream velocity. The backbone of our knowledge of the aerodynamics of aircraft is provided by this theory, to which the effects of thick wings and large incidences, and the effect of viscosity, introducing as it does the concept of boundary layers, can be added as additional or correction effects. It is known that at subsonic and again at supersonic speeds, the theory of small perturbations is a linear theory; that is, the assumptions implicit in it lead to a linear partial differential equation for the velocity potential, with linear boundary conditions.

Type
Research Article
Information
The Aeronautical Journal , Volume 60 , Issue 544 , April 1956 , pp. 241 - 252
Copyright
Copyright © Royal Aeronautical Society 1956

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

1. Wood, A. D. and Lyster, H. C. (1950). Transonic Similarity Relations for Wings of Finite Span. N.R.C. Rep. MR.-9. February 1950.Google Scholar
2. Berndt, S. B. (1950). Similarity Laws for Transonic Flow Around Wings of Finite Aspect Ratio. K.T.H. Aero. Tech. Note 14. February 1950.Google Scholar
3. Spreiter, J. R. (1951). Similarity Laws for Transonic Flow About Wings of Finite Span. N.A.C.A. T.N. 2273 (A.R.C. 13968). January 1951.Google Scholar
4. Oswatitsch, K. and Berndt, S. B. (1950). Aerodynamic Similarity at Axisymmetric Transonic Flow Around Slender Bodies. K.T.H. Aero. Tech. Note 15, May 1950.Google Scholar
5. Moeckel, W. E. (1949). Approximate Method for Predicting Form and Location of Detached Shock Waves Ahead of Plane or Axially Symmetric Bodies. N.A.C.A. T.N. 1921, July 1949.Google Scholar
6. Vincenti, W. G., and Wagoner, C. B. (1952). Transonic Flow Past a Wedge Profile With Detached Bow Wave. N.A.C.A. Rep. 1095 (supersedes N.A.C.A. T.N. 2339 and 2588), 1952.Google Scholar
7. Griffith, W. C. (1952). Transonic Flow Over Wedge Profiles. Journal of the Aeronautical Sciences, Vol. 19, No. 4, pp. 249–257, 264, April 1952.Google Scholar
8. Alperin, M. (1951). A Study of Detached Shock Waves Due to Supersonic Motion of Two-Dimensional Bluff Bodies. Californian Institute of Technology Jet Propulsion Laboratory Report 20-60, November 1951.Google Scholar
9. Solomon, G. E. (1954). Transonic Flow Past Cone Cylinders. N.A.C.A. T.N. 3213, September 1954 .Google Scholar
10. Heberle, J. W., Wood, G. P. and Gooderum, P. B. (1950). Data on Shape and Location of Detached Shock Waves on Cones and Spheres. N.A.C.A. T.N. 2000, January 1950.Google Scholar
11. The Staff of the Supersonics Division Flight Section, Royal Aircraft Establishment (1950). Flight Trials of a Rocket-Propelled Transonic Research Model: The R.A.E.- Vickers Rocket Model. A.R.C. R. & M. 2835, March 1950.Google Scholar
12. Busemann, A. (1949). A Review of Analytical Methods for the Treatment of Flows with Detached Shocks. N.A.C.A. T.N. 1858, April 1949.Google Scholar
13. Spreiter, J. R. (1954). On Alternative Forms for the Basic Equations of Transonic Flow Theory. Journal of the Aeronautical Sciences, Vol. 21, No. 1, pp. 70–72, January 1954.Google Scholar
14. Jones, R. T. (1949). Properties of Low-Aspect-Ratio Pointed Wings at Speeds Below and Above the Speed of Sound. N.A.C.A. Rep. 835 (supersedes N.A.C.A. T.N. 1032), 1949.Google Scholar
15. Robinson, A. and Young, A. D. (1951). Note on the Application of the Linearised Theory for Compressible Flow to Transonic Speeds. A.R.C. R. & M. 2399 (supersedes College of Aeronautics Rep. 2), 1951.Google Scholar
16. Spreiter, J. R. (1952). The Aerodynamic Forces on Slender Plane- and Cruciform-Wing and Body Combinations. N.A.C.A. Rep. 962 (supersedes N.A.C.A. T.N. 1662 and 1897), 1952.Google Scholar
17. Heaslet, M. A., Lomax, H. and Spreiter, J. R. (1950). Linearised Compressible-Flow Theory for Sonic Flight Speeds. N.A.C.A. Rep. 956 (supersedes N.A.C.A. T.N. 1824), 1950.Google Scholar
18. Mangler, K. W. (1954). Calculation of the Pressure Distribution over a Wing at Sonic Speeds. A.R.C. R. & M. 2888, 1954.Google Scholar
19. Adams, M. C. and Sears, W. R. (1953). Slender-Body Theory—Review and Extensions. Journal of the Aeronautical Sciences, Vol. 20, No. 2, pp. 85–98, February 1953.Google Scholar
20. Guderley, G. and Yoshihara, H. (1950). The Flow over a Wedge Profile at Mach Number 1. Journal of the Aeronautical Sciences, Vol. 17, No. 11, pp. 723–735, November 1950.CrossRefGoogle Scholar
21. Trilling, L. and Walker, K. (1953). On the Transonic Flow Past a Finite Wedge. Journal of Mathematics and Physics, Vol. 32, No. 1, pp. 72–79, April 1953.CrossRefGoogle Scholar
22. Guderley, G. (1954). The Flow over a Flat Plate with a Small Angle of Attack at Mach Number 1. Journal of the Aeronautical Sciences, Vol. 21, No. 4, pp. 261–274, April 1954.Google Scholar
23. Vincenti, W. G. and Wagoner, C. B. (1952). Theoretical Study of the Transonic Lift of a Double-Wedge Profile with Detached Bow Wave. N.A.C.A. T.N. 2832, December 1952.Google Scholar
24. Gullstrand, T. R. (1951). The Flow over Symmetrical Aerofoils Without Incidence in the Lower Transonic Range. K.T.H. Aero. Tech. Note 20, August 1951.Google Scholar
25. Gullstrand, T. R. (1952). The Flow over Symmetrical Aerofoils Without Incidence at Sonic Speed. K.T.H. Aero. Tech. Note 24, March 1952.Google Scholar
26. Gullstrand, T. R. (1952). The Flow over Two-Dimensional Aerofoils at Incidence in the Transonic Speed Range. K.T.H. Aero. Tech. Note 27, October 1952.Google Scholar
27. Gullstrand, T. R. (1952). A Theoretical Discussion of Some Properties of Transonic Flow over Two-Dimensional Symmetrical Aerofoils at Zero Lift with a Simple Method to Estimate the Flow Properties. K.T.H. Aero. Tech. Note 25, June 1952.Google Scholar
28. Maccoll, J. W. (1946). Investigations of Compressible Flow at Sonic Speeds. Proceedings of Sixth International Congress of Applied Mechanics (Paris), September 1946.Google Scholar
29. Vincenti, W. G., Dugan, D. W. and Phelps, E. R. (1954). An Experimental Study of the Lift and Pressure Distribution on a Double-Wedge Profile at Mach Numbers near Shock Attachment. N.A.C.A. T.N. 3225, July 1954.Google Scholar
30. Holder, D. W. (1954). Interaction Between Shock Waves and Boundary Layers and its Importance in High-Speed Flight. Lecture to The Royal Aeronautical Society, 30th March 1954. Unpublished.Google Scholar