Hostname: page-component-5c6d5d7d68-qks25 Total loading time: 0 Render date: 2024-08-08T21:22:31.932Z Has data issue: false hasContentIssue false
  • English
  • Français

Shockwave and Boundary Layer Interaction in the Presence of an Expansion Corner

Published online by Cambridge University Press:  07 June 2016

Y.T. Chew
Y.T. Chew*
Affiliation:
Cambridge University Engineering Department; now with University of Singapore, Singapore
Get access

Summary

An investigation has been carried out to examine one aspect of supersonic jet-engine inlet flow, namely shock-wave and boundary-layer interaction in the presence of an expansion corner. The experiment was undertaken at Mach numbers of 1.8 and 2.5. The local Reynolds number per metre varied from 2.79 to 3.13 × 107 for M = 1.8 and from 4.20 to 6.4-8 × 107 for M = 2.5. Adiabatic turbulent boundary layers of about 6 mm thick on an expansion-corner plate were disturbed at different streamwise positions by oblique shocks with deflection angles of 4°, 6° and 8°. The pressure distributions, wave patterns and the extent of the separation regions were strongly influenced by the presence of the expansion corner, especially when the shock impingement positions were upstream of the corner. The pressure rise induced by the incident shock began to decrease in level when the shock impingement position was about 3-4 boundary-layer thicknesses upstream of the corner. As the incident shock moved towards the corner, the pressure rise and the extent of the separation region decreased. When the shock impingement position was at the corner, the reflected shock was effectively neutralised by the Prandtl-Meyer expansion; especially when the deflection angle of incident shock matched that of the expansion corner. The three dimensionality of the incident shock and separation region is due to the interactions between the glancing oblique incident shock and the tunnel’s sidewall boundary layers.

Type
Research Article
Information
Aeronautical Quarterly , Volume 30 , Issue 3 , August 1979 , pp. 506 - 527
Copyright
Copyright © Royal Aeronautical Society. 1979

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1 Green, J.E. Interactions between shock waves and turbulent boundary layers. Prog. Aero. Sci., Vol 11, p 235, 1970 CrossRefGoogle Scholar
2 Gaudet, L. Humidity and scale effect on static pressures measured on the walls of a large supersonic wind tunnel. RAE TR No.6 5074, 1965 Google Scholar
3 Shaw, R. The influence of hole dimensions on static pressure measurements. J. of Fluid Mechanics, Vol. 7, p 550, 1960 CrossRefGoogle Scholar
4 Maltby, R.L. (ed.) Flow visualization in wind tunnels using indicators. AGARDograph 70, 1962 Google Scholar
5 Green, J.E. The turbulent boundary layer in two-dimensional flows with an oblique shock wave. Ph.D. dissertation, Cambridge University Engineering Department, 1966 Google Scholar
6 Chew, Y.T. The turbulent boundary layer at an expansion corner with shock waves. Ph.D. dissertation, Cambridge University Engineering Department, 1976 Google Scholar
7 Reda, D.C. and Murphy, J.D. Shock wave-turbulent boundary layer interactions in rectangular channels. AIAA paper No. 72–715, 1972 Google Scholar
8 Korkegi, R.H. Comparison of shock-induced two- and three-dimensional incipient turbulent separation. AIAA Journal, Vol. 13, p 534, 1975 CrossRefGoogle Scholar
9 Reda, D.C. and Murphy, J.D. The influence of sidewall boundary layers on incipient separation and scale of the interaction. AIAA paper No. 73–234, 1973 Google Scholar
10 Balleur, J. Delery Le Resultats sur l’Interaction choc-couche limite turbulence a des nombres de Mach moderement supersoniques. AGARD-AG-164, 1972 Google Scholar