Recent advances in lifting surface methods

Aeronautical Journal

Volumn 100, Issue 998, 1996, Pages 327-339

  Liu, D D ^a   Chen, P C ^b   Yao, Z X ^b   Sarhaddi, D ^b  

^a Arizona State University   (United States)

^b ZONA TECHNOLOGY INC   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

FLUTTER (AERODYNAMICS); HYPERSONIC AERODYNAMICS; NEWTONIAN FLOW; ROBUSTNESS (CONTROL SYSTEMS); SUBSONIC AERODYNAMICS;

AERODYNAMICS LIFTING SURFACE METHODS; SUBSONIC CONSTANT PRESSURE LIFTING SURFACE METHOD; SUPERSONIC HYPERSONIC LIFTING SURFACE METHOD;

LIFT;

EID: 0030264170     PISSN: 00019240     EISSN: None     Source Type: Trade Journal    
DOI: None     Document Type: Article

References (26)

1. ASHLEY, H., WIDNALL, S. and LANDAHL, M.T. New directions in lifting surface theory, AIAA J, 1965, 3, (1), pp 3-16.
2. LANDAHL, M.T. and STARK, V.J.E. Numerical lifting surface theory - problem and progress, AIAA J, 1968, 6, (11), pp 2049-2060.
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.
4. RODDEN, W.P., GIESING. J.P. and KALMAN, T.P. New method for nonplanar configurations, AGARD Conference Proceedings, CP-80-71, Part H, No 4, 1971.
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.
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.
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.
8. LIOHTHILL, M.J. Oscillating aerofoils at high Mach number, J Aero Sci, 1953, 20, (6), pp 402-406.
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.
10. THEODORSEN, T. General Theory of Aerodynamic Instability and the Mechanism of Flutter, NACA Report No 496, 1940.
11. Aeroelasticity in MSC-Nastran - seminar notes the MacNeal-Schwendler Corporation NA1/000/ASN, October 1990.
12. MILES, J.W. Potential Theory of Unsteady Supersonic Flow, Cambridge University Press, 1959.
13. JOHNSON, E.H. and VENKAYYA, V. B. Automated structural optimisation system (ASTROS) theoretical manual, AFWAL-TR-88-3028, 1, December 1988.
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.
15. TSIEN, H.S. Similarity laws of hypersonic flows, J Maths Phys, 1946, 25, pp 247-251.
16. LIGHTHILL, M.J. A technique for rendering approximate solutions to physical problems uniformly valid, Phil Mag, 40, pp 1179-1201.
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.
18. LINNELL, R.D. Two-dimensional aerofoils in hypersonic flow, J Aero Sci, 1949, 16, pp 22-30.
19. BUSEMANN, A. Aerodynamischer Auftrieb bei Überschall-geschwindigkeit, Luftfahrtforschung, 1935, 12, p 210.
20. VAN DYKE, M.D. A Study of Second-Order Supersonic Flow Theory, NACA Report 1081, 1952.
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.
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.
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.
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.
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.
26. RODDEN, W.P. Correction factors for supersonic thickness effects, MSC-Nastran - WPR-3, April 1, 1991.