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Journal of KONES

Tytuł artykułu

Identification of the boundary layer shock wave interaction type in transonic flow regime

Autorzy Placek, R.  Stryczniewicz, W. 
Treść / Zawartość
Warianty tytułu
Języki publikacji EN
EN The paper presents various approaches to wind tunnel data analysis when identifying the shock wave boundary layer interaction type. The investigation was carried out in the transonic flow regime in the N-3 Wind Tunnel of Institute of Aviation. The Mach number was 0.7 and Reynolds number was approximate equal 2.85 million. The object of the research was a laminar airfoil in configuration without and with turbuliser device mounted on the upper model surface. In order to achieve turbulent boundary layer in front of the shock wave the carborundum strip was used. The effect of the varying angle of incidence on the flow filed was investigated. During experimental research, different means and test methods were applied (pressure measurements, Schlieren and oil visualisation, Particle Image Velocimetry (PIV), hot-film anemometry). The results were analysed in terms of the shock wave boundary interaction type. Most of results were in good agreement with theoretical models reported in the literature. The study showed that combination of various measurement techniques should be used in the shock wave boundary investigations in order to achieve more consistent and reliable conclusions. The results of the presented research can also be used for better understanding other mechanisms i.e. the boundary layer shock wave separation process in transonic flow regime.
Słowa kluczowe
EN transonic flow   wind tunnel techniques   shock wave   airfoil   boundary layer interaction  
Wydawca Institute of Aviation
Czasopismo Journal of KONES
Rocznik 2016
Tom Vol. 23, No. 2
Strony 285--292
Opis fizyczny
autor Placek, R.
  • Institute of Aviation, Aerodynamics Department Krakowska Avenue 110/114, 02-256 Warsaw, Poland tel.: +48 22 8460011 int. 360, 312,
autor Stryczniewicz, W.
  • Institute of Aviation, Aerodynamics Department Krakowska Avenue 110/114, 02-256 Warsaw, Poland tel.: +48 22 8460011 int. 360, 312,
[1] Babinsky, H., Harvey, J. K., Shock Wave-Boundary-Layer Interactions, Cambridge University Press, Ch. 3, 2014.
[2] Bendiksen, O. O., Review of unsteady transonic aerodynamics: Theory and applications, Progress in Aerospace Sciences, 47, pp 135-167, 2011.
[3] Braslow, A. L., Knox, E. C., Simplified method for determination of critical height of distributed roughness particles for boundary-layer transition at Mach numbers from 0 to 5, NACA-TN-4363, 1958.
[4] Delery, J., Marvin, J. G., Shock Wave-Boundary-Layer Interactions, AGARD-AG-280, Ch. 2, 1986.
[5] Doerffer, P., Hirsch, C., Dussauge, J. P., Babinsky, H., Barakos, G. N., Unsteady Effects of Shock Wave Inducted Separation, Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 114, Springer – Verlag Berlin Heidelberg 2010.
[6] Flaszynski, P., Doerffer, P., Szwaba, R., Kaczynski P., Piotrowicz M., Shock Wave Boundary Layer Interaction on Suction Side of Compressor Profile in Single Passage Test Section, Journal of Thermal Science, Vol. 24, Is. 6, pp 510-515, 2015.
[7] Grossi, F., Numerical Study of a Laminar Transonic Airfoil, Extract from PhD Thesis, Ch. 7, pp. 122-123, 2014.
[8] Hermes, V., Klioutchnikov, I., Olivier, H. Numerical investigation of unsteady wave phenomena for transonic airfoil flow, Aerospace Science and Technology 25, pp 224-233, 2013.
[9] Huang, X. Z., Transonic Buffet of a Supercritical Airfoil, Research And Technology Organization, RTO Technical Report 26, pp. 295-339, 2000.
[10] Jacquin, L., Molton, P., Deck, S., Maury, B., Soulevant, D., Experimental Study of Shock Oscillation over a Transonic Supercritical Profile, AIAA Journal, 47, pp. 1985-1994, 2009.
[11] Jun Z., Zhenghong, G., Hao, Z., Junqiang, B., A High-speed Nature Laminar Flow Airfoil and Its Experimental Study in Wind Tunnel with Nonintrusive Measurement Technique, Chinese Journal of Aeronautics, 22, pp. 225-229, 2009.
[12] Kania, W., Aerodynamika doświadczalna w zakresie dużych prędkości., Journal of Theoretical and Applied Mechanics, 21.4, pp. 611-644, 1983.
[13] Kim, H. D., Setoguchi, T., Shock Induced Boundary Layer Separation, 8th International Symposium on Experimental and Computational Aerothermodynamics of Internal Flows, Lyon, France 2007.
[14] Lee, B. H. K., Self-sustained shock oscillations on airfoils at transonic speeds, Progress in Aerospace Liepmann, H. W., Interaction Between Boundary Layers and Shock Waves in Transonic Flow, J. Aero Sci., Vol. 13, No. 12, pp. 623-237, 1946.
[15] Ligum, T. I., Aerodynamics and flight dynamics of turbojet aircraft, Ch. 1, §13, National Aeronautics And Space Administration, 1969.
[16] Pearcey, H. H., Some Effects of Shock-induced Separation of Turbulent Boundary Layers in Transonic Flow past Aerofoils, Aeronautical Research Council Reports And Memoranda, No. 3108, London 1959.
[17] Pearcey, H. H., Osborne, J., Haines, A. B., The interaction between local effects at the shock and rear separation a source of significant scale effects in wind-tunnel tests on aerofoils and wings, AGARD, 35, pp. 18-20, Paris, France 1968.
[18] Ren, Z. Z. X., Gao, C., Xiong, J., Liu, F., Luo, S., Experimental Study of Shock Wave Oscillation on SC(2)-0714 Airfoil, 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2013.
[19] Seddon, J., The Flow Produced by Interaction of a Turbulent Boundary Layer with a Normal Shock Wave of Strength Sufficient to Cause Separation, Aeronautical Research Council Reports And Memoranda, No. 3502, London 1959.
[20] Shapiro, A. S., The dynamics and thermodynamics of compressible fluid flow, Ch. 22.8, 28.4, Ronald press company, 1954.
[21] Stryczniewicz, W., Development of Particle Imagine Velocimetry Algorithm, Problems of Mechatronics, 9, pp. 41-54, 2012.
[22] Stryczniewicz, W., Surmacz, K., PIV Measurements of the Vortex Ring State of the Main Rotor of a Helicopter, Transactions of the Institute of Aviation, 235, pp. 17-27, 2014.
[23] Sznajder, J., Kwiatkowski, T., Effects of Turbulence Induced by Micro-Vortex Generators on Shockwave – Boundary Layer Interactions, Journal of KONES Powertrain and Transport, 22, 2015.
[24] Tijdeman, H., Investigations of the transonic flow around oscillating airfoil, Part 1, Ch. 3.4., 1977.
[25] Wiśniowski, W., Specializations of the Institute of Aviation – review and conclusions, Transactions of the Institute of Aviation, 235, pp. 7-16, 2014. 292
PL Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę.
Kolekcja BazTech
Identyfikator YADDA bwmeta1.element.baztech-d5e2a2a7-c187-484c-8a0d-484c09e3552a
DOI 10.5604/12314005.1213604