Hostname: page-component-848d4c4894-tn8tq Total loading time: 0 Render date: 2024-07-05T02:43:09.624Z Has data issue: false hasContentIssue false
  • English
  • Français

An assessment of the use of low-order panel methods for the calculation of supersonic flows

Published online by Cambridge University Press:  04 July 2016

J. S. Smith  and
D. S. Woodward
J. S. Smith
Affiliation:
Aerodynamics Department, Royal Aircraft Establishment, Farnborough
D. S. Woodward
Affiliation:
Aerodynamics Department, Royal Aircraft Establishment, Farnborough
Get access Rights & Permissions [Opens in a new window]

Summary

Three low-order panel methods developed for the analysis of supersonic flows have been used to make calculations for a number of test configurations, with the aim of establishing the range of problems for which this class of computational method yields adequate solutions. The programs investigated were the Woodward USSAERO/C program, the related NLRAERO program, and the British Aerospace Warton supersonic panel program. Results obtained using these programs have been evaluated against theoretical and experimental data for a number of test cases covering wing-alone, body-alone and wing-body geometries. It is concluded that low-order panel methods can provide adequate solutions for supersonic flows about wings, bodies and wing-body combinations, provided the assumptions implicit in the linearised potential flow model are not violated. Examples show that the prediction of lift and pitching moment curve slopes for quite complex configurations may be acceptable, but that the detailed pressure distributions are not always predicted satisfactorily. In particular, serious problems are encountered in calculating the flow about wings with rounded supersonic leading edges due to the linearised flow model which is used.

Type
Research Article
Information
The Aeronautical Journal , Volume 91 , Issue 907 , September 1987 , pp. 314 - 320
Copyright
Copyright © Royal Aeronautical Society 1987 

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. Woodward, F. A. A unified approach to the analysis and design of wing-body combinations at subsonic and supersonic speeds. AIAA paper 68-55, 1968.Google Scholar
2. Woodward, F. A. An improved method for the aerodynamic analysis of wing-body-tail configurations in subsonic and super sonic flow. Part 1: Theory and application. NASA CR 2228 part 1, 1973.Google Scholar
3. Woodward, F. A. USSAERO computer program development versions B and C. NASA CR 3227, 1980.Google Scholar
4. Hoeijmakers, H. W. M. A panel method for the determination of the aerodynamic characteristics of complex configurations in linearized subsonic or supersonic flow. NLR TR 80124 Parts I and II, 1980.Google Scholar
5. Hoeijmakers, H. W. M. Description of computer program NLRAERO — Version A. NLR Memorandum AT-83-005, 1983.Google Scholar
6. Crowley, J. A., Marland, D. and Marchbank, W. R. Development of a supersonic panel program. Phase II: Development within the Warton Mk IICFM system, of version I of a lifting supersonic panel program (Sup PP (VI)). Unpublished BAe Warton report, 1984.Google Scholar
7. Carmichael, R. L. and Erickson, L. L. PANAIR — A higher order panel method for predicting subsonic or supersonic linear potential flows about arbitrary configurations. AIAA paper 81-1255, 1981.Google Scholar
8. Jameson, A. and Schmidt, W. Numerical solutions of the Euler equations by finite volume methods using Runge-Kutta time stepping schemes. AIAA paper 81-1259, 1981.Google Scholar
9. Ferri, A. Supersonic flows with shock waves. In: High speed aerodynamics and jet propulsion Vol VI. Sears, W. R. (Editor). Oxford University Press, 1955.Google Scholar
10. Jones, R. T. Aerodynamics of wings at high speeds. In: High speed aerodynamics and jet propulsion Vol VII. Donovan, A. F., Lawrence, H. R. (Editors). Oxford University Press, 1957.Google Scholar
11. Carlson, H. W. Pressure distributions at Mach number 2-05 on a series of highly swept arrow wings employing various degrees of twist and camber. NASA TN-D 1264, 1962.Google Scholar
12. Smith, J. S. A comparative evaluation of three panel programs for the analysis of supersonic flows. Unpublished MOD (PE) Report, 1985.Google Scholar
13. Wood, R. M. and Miller, D. S. Status review of a supersonically biased fighter wing design study. AIAA paper 83-1857, 1983.Google Scholar
14. Wood, R. M. and Miller, D. S.Wing planform effects at supersonic speeds for an advanced fighter configuration. NASA TP 2269, 1984.Google Scholar
15. Wood, R. M. and Miller, D. S. Effect of fuselage upwash on the supersonic longitudinal aerodynamic characteristics of two fighter configurations. NASA TP 2330, 1984.Google Scholar