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Numerical predictions of transonic viscous flows around aerofoils through an Euler/boundary layer interaction method

Published online by Cambridge University Press:  04 July 2016

D. P. Coiro ,
M. Amato  and
P. De Matteis
D. P. Coiro
Affiliation:
CIRA, Centro Italiano Ricerche Aerospaziali
M. Amato
Affiliation:
CIRA, Centro Italiano Ricerche Aerospaziali
P. De Matteis
Affiliation:
CIRA, Centro Italiano Ricerche Aerospaziali
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Abstract

A semi-inverse viscous/inviscid coupling technique for the calculation of compressible flows is presented. Euler equations in integral form are solved for the inviscid part and integral compressible boundary-layer equations in direct and inverse form are solved for the viscous one. Interaction is realised using the equivalent sources approach.

The technique has been applied to the calculation of the aerodynamic characteristics of aerofoils both in cruise and take-off or landing configurations. To treat the complex geometries involved in the latter case, a multi-block approach, based on structured ‘H’ grid topology, has been developed and validated for different configurations.

Type
Research Article
Information
The Aeronautical Journal , Volume 96 , Issue 954 , April 1992 , pp. 157 - 165
Copyright
Copyright © Royal Aeronautical Society 1992 

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Footnotes

*

Currently, Research Scientist at Istituto di Progetto Velivoli, Universita degli Studi di Napoli

References

1. Holst, T. L. Viscous transonic airfoil workshop compendium of results. J Aircr, 1988, 25, (12), pp 1073–1087.Google Scholar
2. Coiro, D. P., De Matteis (12), P. and Amato, M. An Euler/ boundary layer interaction method for transonic flow calculations around airoils. Proceedings of the 10th IADAA Conference, Pisa (Italy), October 1989.Google Scholar
3. Coiro, D. P., De Matteis, P. and Amato, M. Wake effects on the prediction of transonic flows around airfoils. AIAA Paper 90-3061, to be published in J Aircr. Google Scholar
4. King, D. A. and Williams, B. R. Developments in computational methods for high-lift aerodynamics. Aeronaut J, August/September 1988, 92, pp 265–288.Google Scholar
5. Drela, M. Newton solution on coupled viscous/inviscid multielement airfoil flows. AIAA Paper 90-1470, June 1990.Google Scholar
6. Lighthill, M. J. On displacement thickness. J Fluid Mech 1958, 4, Part 4, pp 661–663.Google Scholar
7. Amato, M. Scelta ottimale del grigliato di aerodinamica, Tesi di Laurea, Instituto di Aerodinamica, Universita degli Studi di Napoli, 1988.Google Scholar
8. Jameson, A., Schmidt, W. and Turkel, E. Numerical solution of the Euler equations by finite volume methods using Runge-Kutta time-stepping schemes. AIAA Paper 81-1259, June 1981.Google Scholar
9. De Matteis, P. Metodi multigrid di fluidodinamica computazionale. Tesi di Laurea, Instituto di Aerodinamicà, Universita degli Studi di Napoli, 1988.Google Scholar
10. Rizzi, A. Numerical implementation of solid-body boundary conditions for the Euler equations. Z Angew Math Mech, 1978, 58.Google Scholar
11. Coiro, D. P. Metodi integrali di strato limite inverso eapplicazioni numeriche. Tesi di Laurea, Istituto di Gasdinamica, Università degli Studi di Napoli, 1985.Google Scholar
12. Whitfield, D. L. Analytical description of the complete turbulent boundary layer velocity profile. AIAA Paper 78-1158.Google Scholar
13. Whitfield, D. L., Swafford, T. W. and Donegan, T. L. An inverse integral computational method for compressible turbulent boundary layers. Transport Phenomena in Fluid Mechanics, Springer-Verlag, Berlin 1982.Google Scholar
14. Thomas, J. L. Transonic viscous-inviscid interaction using Euler and inverse boundary layer equations. Ph.D. Thesis, Mississippi State University, 1983.Google Scholar
15. Green, J. E., Weeks, D. J. and Broman, J. W. F. Prediction of Turbulent Boundary Layers and Wakes in Compressible Flow by Lag-Entrainment Method. RAE TR 72231, 1972.Google Scholar
16. East, L. F., Smith, P. D. and Merryman, P. J. Prediction of the Development of Separated Turbulent Boundary Layers by the Lag-Entrainment Method. RAE TR 77046. 1977.Google Scholar
17. Stewartson, K. Correlated incompressible and compressible boundary layers. Proc R Soc (Lond) A, 1949, 200, pp 213–228.Google Scholar
18. Michel, R. Etude de la transition sur les profiles d’aile. ONERA Report l/1578a, 1951.Google Scholar
19. Johnston, W. and Sockol, P. Matching procedure for viscous-inviscid interactive calculations. AIAA J, June 1979, 17, (6), pp 661–663.Google Scholar
20. Carter, J. E. A new boundary layer inviscid interaction technique for separated flows. AIAA Paper 79-1450.Google Scholar
21. Williams, B. R. An exact test case for the plane potential flow about two adjacent lifting airfoils. Aeronautical Research Council, R & M, No. 3717, 1973.Google Scholar
22. Mavriplis, D. Solution of the two dimensional Euler equations on unstructured triangular meshes. Ph.D. Thesis, Princeton University, 1987.Google Scholar
23. Experimental Data Base for Computer Program Assessment. AGARD-AR-138, 1979.Google Scholar
24. Pulliam, T. H. Euler and thin layer Navier-Stokes Codes: ARC2D, ARC3D. Notes for Computational Fluid Dynamics User’s Workshop, The University of Tennessee Space Institute, Tullahoma, Tennessee, 12-16 March 1984.Google Scholar
25. Harris, C. D. Two-dimensional aerodynamic characteristics of the NACA 0012 airfoil in the Langley 8 foot transonic pressure tunnel. NASA-TM 81927, April 1981.Google Scholar