Aero-Thermodynamic Loss Analysis in Cases of Normal Shock Wave-Turbulent Shear Layer Interaction

[+] Author and Article Information
J. K. Kaldellis

Laboratory of Soft Energy Applications, Department of Mechanical Engineering, Technological Education Institute of Piraeus, Pontou 58, Hellinico, Athens, Greece 16777

J. Fluids Eng 119(2), 297-303 (Jun 01, 1997) (7 pages) doi:10.1115/1.2819134 History: Received February 18, 1995; Revised January 21, 1997; Online December 04, 2007


Transonic-supersonic decelerating flow cases appearing in modern turbomachines are some of the most complex flow cases in fluid mechanics which also present practical interest. In the present work, a closed and coherent shock loss model is proposed based on the complete viscous flow simulation using some fast and reliable computational tools. The resulting model describes accurately the entropy rise and the total pressure loss in cases of strong shock-shear layer interaction and cancels the need to use low speed correlations modified for compressibility effects and extrapolated to transonic-supersonic flow cases. The accuracy and the reliability of the proposed shock-loss model are verified using detailed experimental data concerning various flow cases which present either flow separation or industrial interest.

Copyright © 1997 by The American Society of Mechanical Engineers
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