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Recent advances in lifting surface methods

Published online by Cambridge University Press:  04 July 2016

D. D. Liu ,
P. C. Chen ,
Z. X. Yao  and
D. Sarhaddi
D. D. Liu
Affiliation:
Department of Mechanical and Aerospace Engineering , Arizona Stale University , Tempe, Arizona , USA
P. C. Chen
Affiliation:
ZONA Technology , Mesa, Arizona , USA
Z. X. Yao
Affiliation:
ZONA Technology , Mesa, Arizona , USA
D. Sarhaddi
Affiliation:
ZONA Technology , Mesa, Arizona , USA
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Abstract

Recent advances in two lifting surface methods are reported. The present subsonic constant pressure method improves upon the program robustness of the doublet lattice method. The present unified supersonic-hypersonic method extends the range of applicability of lifting surface theory to the Newtonian limit. Based on a uniformly-valid series formulation, the method accurately approximates the non-linear thickness effect, whereas this effect is neglected by the linear theory and overestimated by piston theory. In fact, the present results generally agree well with the trends of several Euler solutions. Among other findings, cases computed by the unified method confirm that the effect of thickness is to reduce the supersonic flutter speed.

Type
Research Article
Information
The Aeronautical Journal , Volume 100 , Issue 998 , October 1996 , pp. 327 - 340
Copyright
Copyright © Royal Aeronautical Society 1996 

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Footnotes

†

Professor, mechanical & aerospace engineering

‡

vice president

*

Member of technical staff

References

1. Ashley, H., Widnall, S. and Landahl, M.T. New directions in lifting surface theory, AIAA J, 1965, 3, (1), pp 3–16.Google Scholar
2. Landahl, M.T. and Stark, V.J.E. Numerical lifting surface theory — problem and progress, AIAA J, 1968, 6, (11), pp 2049–2060.Google Scholar
3. Albano, E. and Rodden, W.P. A doublet-lattice method for calculating lift distribution on oscillating surfaces in subsonic flows, AIAA J, 1969, 7, (2), pp 279–285.Google Scholar
4. Rodden, W.P., Giesing, J.P. and Kalman, T.P. New method for nonplanar configurations, AGARD Conference Proceedings, CP-80-71, Part II, No 4, 1971.Google Scholar
5. Chen, P.C. and Liu, D.D. A harmonic gradient method for unsteady supersonic flow calculations, J Aircr, 1985, 22, (5), pp 371–379.Google Scholar
6. Chen, P.C., Lee, H.W. and Liu, D.D. Unsteady subsonic aerodynamics for bodies and wings with external stores including wake effect, J Aircr, 1990, 27, (2), pp 108–116.Google Scholar
7. Liu, D.D., Yao, Z.X., Sarhaddi, D. and Chavez, F. Piston theory revisited and further applications, ICAS Paper 94-2.8.4, 1994.Google Scholar
8. Lighthill, M.J. Oscillating aerofoils at high Mach number, J Aero Sci, 1953, 20, (6), pp 402–406.Google Scholar
9. Chen, P.C. and Liu, D.D. Unsteady supersonic computation of arbitrary wing-body configurations including external stores, J Aircr, 1990, 27, (2), pp 108–116.Google Scholar
10. Theodorsen, T. General Theory of Aerodynamic Instability and the Mechanism of Flutter, NACA Report No 496, 1940.Google Scholar
11. Aeroelasticity in MSC-Nastran — seminar notes the MacNeal-Schwendler Corporation NA1/000/ASN, October 1990.Google Scholar
12. Miles, J.W. Potential Theory of Unsteady Supersonic Flow, Cambridge University Press, 1959.Google Scholar
13. Johnson, E.H. and Venkayya, V. B. Automated structural optimisation system (ASTROS) theoretical manual, AFWAL-TR-88-3028, 1, December 1988.Google Scholar
14. Chavez, F.R. and Liu, D.D. A unified hypersonic-supersonic method for aeroelastic applications including shock-unsteady wave interaction, AIAA Paper, 93-1317, April 1993.Google Scholar
15. Tsien, H.S. Similarity laws of hypersonic flows, J Maths Phys, 1946, 25, pp 247–251.Google Scholar
16. Lighthill, M.J. A technique for rendering approximate solutions to physical problems uniformly valid, Phil Mag, 40, pp 1179–1201.Google Scholar
17. Donov, A.E. A flat wing with sharp edges in a supersonic stream, NACA TM-1394, 1956, Translation of Izvestiia-Akademia, NAUK, USSR, 1939.Google Scholar
18. Linnell, R.D. Two-dimensional aerofoils in hypersonic flow, J Aero Sci, 1949, 16, pp 22–30.Google Scholar
19. Busemann, A. Aerodynamischer Auftrieb bei Uberschall-geschwindigkeit, Luftfahrtforschung, 1935, 12, p 210.Google Scholar
20. Van Dyke, M.D. A Study of Second-Order Supersonic Flow Theory, NACA Report 1081, 1952.Google Scholar
21. Hui, W.H. Unified unsteady supersonic-hypersonic theory of flow past double wedge aerofoils, J App Maths Phys, 1983, 34, (4), pp 458–488.Google Scholar
22. Hanson, P.W. and Levey, G.M. Experimental and calculated results of a flutter investigation of some very low aspect-ratio flat-plate surface at Mach numbers from 0-62 to 3-0, NASA TN D-2038, 1963.Google Scholar
23. Batina, J.T. An efficient algorithm for solution of the unsteady transonic small-disturbance equation, AAIA Paper 87-0109, Jan 1987; also available as NASA TM-89014, Dec 1986.Google Scholar
24. Bennett, R.M., Bland, S. R., Batina, J.T., Gibbons, M.D. and Mabey, D. G. Calculation of steady and unsteady pressure on wings at supersonic speeds with a transonic small-disturbance code, J Aircr, 1991, 28, (3), pp 175–180.Google Scholar
25. Tuovila, W.J. and McCarty, J.L. Experimental flutter results for cantilever-wing models at Mach numbers up to 3 0, NACA RM L55E11, 1955.Google Scholar
26. Rodden, W.P. Correction factors for supersonic thickness effects, MSC-Nastran —WPR-3, April 1, 1991.Google Scholar