Transonic flows, shock wave-turbulent boundary layer interaction

• Autorzy: Doerffer P. , Kaczyński J.
• Języki publikacji: EN

Abstrakty

EN

Shock wave-boundary layer interaction is one of the most important phenomenon in transonic flows. Due to its complexity it is difficult as well for experimental as for numerical study. The growing potential of CFD is therefore of great importance. Different aspects of shock wave-boundary layer interaction should be studied in different flow configurations. Therefore results concerning profile flow, helicopter rotor at hovering and forward flight and internal flows are presented in this paper. These are to illustrate our ability in CFD in general. Besides flow simulation the development of codes is carried out.

Słowa kluczowe

EN

transonic flows; shock waves; turbulent boundary layer interaction; computational fluid dynamics CFD; CFD; flow configurations; profile flow; helicopter rotor; hovering; forward flight; internal flows

• Wydawca: Politechnika Gdańska
• Czasopismo: TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk
• Rocznik: 1998
• Tom: Vol. 2, No 2
• Strony: 271--286
• Opis fizyczny: Bibliogr. 11 poz., rys.

Twórcy

autor

Doerffer P.

• Institute of Fluid Machinery, Polish Academy of Sciences, J. Fiszera 14, 80-952 Gdańsk, Poland

autor

Kaczyński J.

• Institute of Fluid Machinery, Polish Academy of Sciences, J. Fiszera 14, 80-952 Gdańsk, Poland

Bibliografia

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• [2] A. Pronska, Interfejs KAPPA - Visual 3, nr arch.: 466/97
• [3] J. Kaezyhski, Numerical analysis of dissipative phenomenon in selected flow configurations, doctor thesis, IMPPAN, October 1995
• [4] F.X. Caradona Application of Transonic Flow Analysis to Helicopter Rotor Problem, Progress in Astronautics and Aeronautics, Vol. 120, pp: 263-285
• [5] P. DocrtTer, J Zierep An experimental investigation of the Reynolds number effect on a normal shock wave - turbulent boundary layer interactions on a curved wall. Act Mechanica 73, pp. 77-93 (1988)
• [6] P. Doerffer, An experimental investigation of the Mach number effect upon a normal shock wave - turbulent boundary layer interaction on a curved wall, Acta Mechanica 76, pp. 35-51 (1989)
• [7] P. Doerffer, Not mid shock *-foot topography at turbulent boundary layer, Acta Mechanica (1994) [Suppl] 4: pp 133-140
• [8] P. Doerffer, .1. Amecke, Secondary flow control and streannvise vortices formation. ASME TURBO-EXPO '94, International Gas Turbine and Aeroengine Congress ant Exposition, the Hague, Netherlands - June 13-16, 1994, ASME Paper 94-GT-376
• [9] P. Doerffer, U. Dallmann, Reynolds number effect on separation structures in normal shock wave-turbulent boundary layer interaction, AIAA Journal, Vol. 27, No. 9, W
• [10] P. Doerffer, U. Dallmannn, Secondary corner and channel flow effects on shock induced turbulent flow separation. Proceedings of the IUTAM Symposium on Separated Flows and Jets, Novosybirsk, 1990, Springer Verlag
• [11] P. Doerffer, R. Bohning, Passive control of a normal shock wave-turbulent howulm layer interaction, RRDPAE '96, Warsaw 1996, 25-27 November