Mass-averaging pseudo-shock model in a straight flow passage

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering

Volumn 213, Issue 6, 1999, Pages 365-375

  Matsuo, K ^a   Miyazato, Y ^a   Kim, H D ^b  

^a KYUSHU UNIVERSITY   (Japan)

^b Andong National University   (South Korea)

Author keywords

Compressible flow; Flow confinement; Mach number; Normal shock wave; Pseudo shock wave; Reynolds number

Indexed keywords

COMPUTATION THEORY; CONFINED FLOW; REYNOLDS NUMBER; SHOCK WAVES;

MACH NUMBERS; NORMAL SHOCK WAVES; PSEUDO-SHOCK MODEL;

MECHANICAL ENGINEERING;

EID: 27544480010     PISSN: 09544100     EISSN: 09544100     Source Type: Journal    
DOI: 10.1243/0954410991533089     Document Type: Conference Paper

References (24)

1. Green, J. E. Interactions between shock waves and turbulent boundary layers. Prog. in Aerospace Sci., 1970, 101, 235-340.
2. Crocco, L. One-dimensional treatment of steady gas dynamics. In Fundamentals of Gas Dynamics (Ed. H. W. Emmons), 1958, p. 115 (Princeton).
3. Matsuo, K., Miyazato, Y. and Kim, H. D. Shock train and pseudo-shock phenomena in internal gas flows. Prog. in Aerospace Sci., 1999, 35, 33-100.
4. Hataue, I. Computational study of the shock-wave/boundary-layer interaction in a duct. Fluid Dynamics Res., 1989, 5, 217-234.
5. Carroll, B. F., Fernandez, P. A. L. and Dutton, J. C. Computations and experiments for a multiple normal shock/boundary-layer interaction. J. Propulsion and Power, 1993, 9(3), 405-411.
6. Yamane, R., Oshima, S., Nakamura, Y. and Ishii, T. Numerical simulation of pseudo shock in straight channels. Jap. Soc. Mech. Engrs Int. J., Ser. B., 1995, 38(4), 549-554.
7. Ikui, T., Matsuo, K. and Nagai, M. The mechanism of pseudo-shock waves. Bull. Jap. Soc. Mech. Engrs, 1974, 17(108), 731-739.
8. Ikui, T., Matsuo, K. and Sasaguchi, K. Modified diffusion model of pseudo-shock waves considering upstream boundary layer. Bull. Jap. Soc. Mech. Engrs, 1981, 24(197), 1920-1927.
9. Tamaki, T., Tomita, Y. and Yamane, R. A study of pseudoshock, I, λ-type pseudo-shock. Bull. Jap. Soc. Mech. Engrs, 1970, 13(55), 51-58.
10. Shchetinkov, E. S. Piecewise-one-dimensional models of supersonic combustion and pseudo-shocks in a duct. Combust. Explos. and Shock Waves, 1975, 9(4), 409-417.
11. Zimont, V. L. and Ostras, V. N. Calculation of pseudo-shocks in a cylindrical duct. Fluid Mech. Sov. Res., 1976, 5(2), 78-87.
12. Nagai, M. and Yaga, M. On the pseudo shock wave relations. ASME FED. 224 Trans. and Turbulent Compressible Flows, 1995, 103-108.
13. Tyler, R. D. One-dimensional treatment of non-uniform flow. ARC, R&M 2991, 1957.
14. Ward-Smith, A. J. Internal Fluid Flow, 1980, p. 67 (Clarendon Press).
15. Torizumi, Y. One-dimensional treatment of compressible flow through a duct (in Japanese). Trans. Jap. Soc. Mech. Engrs, Ser. B, 1992, 58(549), 1650-1653.
16. Tucker, M. Approximate turbulent boundary-layer development in plane compressible flow along thermally insulated surfaces with application to supersonic tunnel contour correction. NACATN 2045, 1950.
17. Tucker, M. Approximate calculation of turbulent boundary-layer development in compressible flow. NACA TN 2337, 1951.
18. Shapiro, A. H. The Dynamics and Thermodynamics of Compressible Fluid Flow, 1953, Vol. 1, p. 1085 (Ronald Press Company).
19. McLafferty, G. Theoretical pressure recovery through a normal shock in a duct with initial boundary layer. J. Aeronaut. Sci., 1953, 20(3), 169-174.
20. Merkli, P. E. Pressure recovery in rectangular constant area supersonic diffusers. Am. Inst. Aeronaut. Astronaut. J., 1976, 14(2), 168-172.
21. Carroll, B. F. and Dutton, J. C. Characteristics of multiple shock wave/turbulent boundary layer interactions in rectangular ducts. J. Propulsion and Power, 1990, 6(2), 186-193.
22. McCormick, D. C. Shock/boundary-layer interaction control with vortex generators and passive cavity. Am. Inst. Aeronaut. Astronaut. J., 1993, 31(1), 91-96.
23. Waltrup, P. J. and Cameron, J. M. Wall shear and boundary-layer measurements in shock separated flow. Am. Inst. Aeronaut. Astronaut. J., 1974, 12(6), 878-880.
24. Om, D. and Childs, M. E. Multiple transonic shock-wave/turbulent boundary-layer interaction in a circular duct. Am. Inst. Aeronaut. Astronaut. J., 1985, 23(10), 1506-1511.