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Wing pressure loads in canard configurations: a comparison between numerical results and experimental data

Published online by Cambridge University Press:  04 July 2016

G. Buresti,
G. Lombardi and
P. Petagna
G. Buresti
Affiliation:
Department of Aerospace Engineering, University of Pisa, Italy
G. Lombardi
Affiliation:
Department of Aerospace Engineering, University of Pisa, Italy
P. Petagna
Affiliation:
ARIA, Aerodynamic Research for Industrial Applications, Italy
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Summary

A comparison between computed and experimental pressure distributions on straight and forward-swept wings placed in interference with a fore canard surface at M = 0·3 and Re ≈ 2·8x106 is presented. It is shown that a numerical code, based on a non-linear vortex lattice method and expressly developed for the analysis of interfering lifting surfaces, is capable, in spite of its simplicity, of very accurate predictions in all configurations which do not correspond to sufficiently high angles of attack and to a close interference between the fore wake and the wing surface. Furthermore, even in the latter cases the predictions are acceptable, and the code is shown to be extremely robust as regards the variation of all its free parameters.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 96 , Issue 957 , September 1992, pp. 271 - 279
Copyright
Copyright © Royal Aeronautical Society 1992 

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References

1. Buresti, G. and Lombardi, G. Indagine sperimentale sull'interferenza ala-canard, L'Aerotecnica, Missili e Spazio, 1988, 67, N 1–4, pp 47–57.Google Scholar
2. Buresti, G., Lombardi, G. and Petagna, P. Analisi dell'interazione fra superfici portanti mediante un modello potenziale, Proc 10th AIDAA Conference, Pisa, 1989, pp 116–124.Google Scholar
3. Buresti, G., Lombardi, G. and Polito, L. Analysis of the interaction between lifting surfaces by means of a non-linear panel method, In: Boundary Integral Methods. Theory and Applications, Morino, L. and Piva, R. (eds), Springer Verlag, 1991, pp 125–134.Google Scholar
4. Buresti, G., Lombardi, G. and Morelli, M. Pressure measurements on different canard-wing configurations in subsonic compressible flow, Atti del Dipartimento di Ingegneria Aerospaziale di Pisa, ADIA 91-4, 1991.Google Scholar
5. Hoeijmakers, H. W. M. Computational Vortex Flow Aerodynamics AGARD-CP-342, Paper 18, 1983.Google Scholar
6. Smith, J. H. B. Theoretical Modelling of Three-Dimensional Vortex Flows in Aerodynamics, AGARD-CP-342, Paper 17, 1983.Google Scholar
7. Smith, J. H. B. Modelling three-dimensional vortex flows in aerodynamics VKI Lecture Series Introduction to vortex flow aerodynamics, 1986.Google Scholar
8. Kandil, O. A., Mook, D. T. and Nayfeh, A. H. Nonlinear prediction of the aerodynamic loads on lifting surfaces, J Aircr, 1976, 13, pp 22–28.Google Scholar
9. Rajeswari, B. and Dutt, H. N. V. Nonplanar vortex-lattice method for analysis of complex multiple lifting surfaces, NAL Tech Mem TM AE8606, 1986.Google Scholar
10. Rusak, Z., Wasserstrom, E. and Seginer, A. Numerical calculation of nonlinear aerodynamics of wing body configurations AIAA J, 1983, 21, pp 929–936.Google Scholar
11. Suciu, E. O. and Morino, L. A nonlinear finite element analysis of wings in steady incompressible flows with wake rollup AIAA Paper 76–64, 1976.Google Scholar
12. Yeh, D. T. and Plotkin, A. Vortex panel calculation of wake roll-up behind a large aspect ratio wing AIAA J, 1986, 24, pp 1417–1423.Google Scholar
13. Smith, B. E. and Ross, J. C. Application of a Panel Method to Wake Vortex-Wing Interaction and Comparison With Experimental Data NASA TM 88337, 1987.Google Scholar
14. Maskew, B. Predicting aerodynamic characteristics of vortical flows on three-dimensional configurations using a surface singularity pan el method AGARD CP-342, Paper 13, 1983.Google Scholar
15. Wagner, S., Urban, Ch. and Behr, R. A vortex-lattice method for the calculation of wing-vortex interaction in subsonic flow, In Panel Methods in Fluid Mechanics with Emphasis on Aerodynamics, Ball-mann, J., Eppler, R., Hackbusch, W. (eds), Notes on Numerical Fluid Mechanics, 21, Vieweg, 1987, pp 243–251.Google Scholar
16. Mook, D.T. Unsteady aerodynamics, VKI Lecture Series Unsteady aerodynamics, 1988–07, 1988.Google Scholar
17. Baron, A., Boffadossi, M. and De Ponte, S. Numerical simulation of vortex flows past impulsively started wings, AGARD Symposium on Vortex Flow Aerodynamics, Scheveningen, paper 33, 1990.Google Scholar
18. Almosnino, D. High angle of attack calculation of subsonic vortex flow on slender bodies, AIAA J, 1985, 23, pp 1150–1156.Google Scholar
19. Moore, D.W. A numerical study of the roll-up of a finite vortex sheet” J. Fluid Mech, 1974, 63, pp 225–235.Google Scholar
20. Sarpkaya, T. and Shoaff, R.L. A discrete vortex analysis of flow about stationary and transversely oscillating circular cylinders NPS69SL79011, 1979.Google Scholar
21. Lombardi, G. A subsonic and transonic experimental study on the aerodynamic effects of a forward sweep angle, Proc 11th National Congress AIDAA, Forli, 1991.Google Scholar
22. Maskew, B. and Rao, B.M. Calculation of vortex flows on complex configurations, ICAS Proc, Seattle, Paper 6.2.3, 1982.Google Scholar