Hostname: page-component-7f64f4797f-6fdxz Total loading time: 0 Render date: 2025-11-04T16:08:42.720Z Has data issue: false hasContentIssue false
  • English
  • Français

A vortex lattice method for thin wings oscillating in ideal flow

Published online by Cambridge University Press:  04 July 2016

M. K. Laha
M. K. Laha*
Affiliation:
Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur, India
Get access Rights & Permissions [Opens in a new window]

Summary

The planar vortex lattice method is extended to the case of wings in small-amplitude oscillations in ideal flow. Vortex rings are used to represent the bound vorticity on the wing and the trailing vorticity in the wake. A modified procedure for solving the unknown vortex strengths gives greater computing efficiency. Comparisons with results reported in the literature show good agreement for the various test cases considered. Convergence with increasing lattice density is uniform.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 97 , Issue 969 , November 1993 , pp. 314 - 320
Copyright
Copyright © Royal Aeronautical Society 1993 

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.)

Article purchase

Temporarily unavailable

References

1. Multhopp, H. Methods for calculating the lift distribution of wings (subsonic lifting surface theory), ARC R&M 2884, January 1950.Google Scholar
2. Garner, H.C. Multhopp’s lifting surface theory of wings in slow pitching oscillations, ARC R&M 2885, July 1952.Google Scholar
3. Laschka, B. Zur Theorie der harmonische schwingenden tragenden Flache bei Unterschallstromung, Z Flugwiss, 1963, 11, pp 265–292.Google Scholar
4. Albano, E., and Rodden, W.P. A doublet-lattice method for calculating lift distribution on oscillating surfaces in subsonic flows, AIAA J, February 1969, 7, (2), pp 279–285.Google Scholar
5. Jones, W.P., and Moore, J.A. Simplified aerodynamic theory of oscillating thin surface in subsonic flow, AIAA J, September 1973, 11, (9), pp 1305–1309.Google Scholar
6. Geissler, W. Methods for inviscid subsonic flows about aircraft configurations, AGARD-R-679, October 1980.Google Scholar
7. Singh, N. Aikat, S. and Basu, B.C. Oscillating thin wings in inviscid incompressible flow, Aeronaut J, August/September 1989, 93, (927), pp 272–277.Google Scholar
8. Rubbert, P.E. Theoretical Characteristics of Arbitrary Wings by a Nonplaner Vortex Lattice Method, Boeing Company Report D 6-9224, 1964.Google Scholar
9. Levin, D. A vortex lattice method for calculating longitudinal dynamic stability derivatives of oscillating delta wings, AIAA J, January 1984, 22, (1), pp 6–12.Google Scholar
10. Konstadinopoulos, P., Mook, D.T. and Nayfeh, A.H. Subsonic wing rock of slender delta wings, J Aircr, March 1985, 22, (3), pp 223–228.Google Scholar
11. Hancock, G.J. and Lam, J.S.Y. On the application of axiomatic aerodynamic modelling to aircraft dynamics Part 2 — Longitudinal aircraft motions with attached flow, Aeronaut J, January 1987, 91, (901),pp 4–20.Google Scholar
12. Basu, B.C. and Hancock, G.J. Two-dimensional aerofoils and control surfaces in simple harmonic motion in incompressible inviscid flow, ARC CP 1392 (1978).Google Scholar
13. Bisplinghoff, R.L., Ashley, H. and Halfman, R.L. Aeroelasticity, Addison-Wesley, 1955, p 393.Google Scholar
14. Morino, L. and Kuo, C.C. Subsonic potential aerodynamics for complex configurations: a general theory, AIAA J, 1974, 2, (2), pp 191–197.Google Scholar
15. Patel, M.H. Aerodynamic forces on finite wings in oscillatory flow: an experimental study, AIAA J, November 1978, 16, (11), pp 1175–1180.Google Scholar