Hostname: page-component-7b7567c8c-fvjsw Total loading time: 0 Render date: 2026-11-14T22:09:26.026Z Has data issue: false hasContentIssue false
  • English
  • Français

Computational analysis of unsteady supersonic cavity flows driven by thick shear layers

Published online by Cambridge University Press:  04 July 2016

X. Zhang and
J. A. Edwards
X. Zhang
Affiliation:
Department of Engineering, University of Cambridge
J. A. Edwards
Affiliation:
Department of Engineering, University of Cambridge
Get accessRights & Permissions [Opens in a new window]

Abstract

Supersonic cavity flows driven by a thick shear layer at Mach 1·5 and 2·5 are studied by solving the two-dimensional unsteady compressible Navier-Stokes equations in terms of mass-averaged variables. The length to depth ratio of the rectangular cavity is three. The numerical scheme used is the finite-difference algorithm by Brailovskaya. A two-layer eddy-viscosity turbulence model is used. The results are compared with experimental data. The computations show the self-sustained oscillations at Mach 1·5 and 2·5. The continuous formation and downstream shedding of leading edge vortices is demonstrated. The oscillatory modes are correctly predicted. The first mode is attributed to a large unsteady trailing edge vortex moving in the transverse direction. Based on the analysis, it is considered that the oscillation in the length to depth ratio three cavity is a longitudinal one and is controlled by a fluid dynamic mechanism rather than a purely acoustic one.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 92 , Issue 919 , November 1988, pp. 365 - 374
Copyright
Copyright © Royal Aeronautical Society 1988 

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.)

Article purchase

Temporarily unavailable

Footnotes

*

Now in the Dept. of Aeronautics and Astronautics, University of Southampton

†

Now at the College of Aeronautics, Cranfield Institute of Technology, Cranfield, Bedford

References

1. Krishnamurty, K. Acoustic Radiation from Two-Dimensional Cutout in Aerodynamic Surface. NACA TN 3487, 1955.Google Scholar
2. Borland, C. S. Numerical Prediction of the Unsteady Flow field in an Open Cavity. AIAA Paper 77-673, 1977.Google Scholar
3. Hankey, W. and Shang, J. S. An analysis of pressure oscillation in an open cavity. AIAA J, 1980, 18, (8), 892–898.Google Scholar
4. Gatski, T. B. and Grosch, C. E. Embedded cavity drag in steady laminar flow. AIAA J, July 1985, 23, (7), 1028–1037.Google Scholar
5. Brailovskaya, I. Yu. A difference scheme for numerical solution of the two-dimensional nonstationary Navier-Stokes equations for a compressible flow. Sov Phys-Doklady, Aug 1965, 10, (2), 107–110.Google Scholar
6. Diewert, G. S. Computation of separated transonic turbulent flows. AIAA J. June 1976, 14, (6), 735–740.Google Scholar
7. Zhang, X. An Experimental and Computational Investigation into Supersonic Shear Layer Driven Single and Multiple Cavity Flowfields. PhD Thesis, Department of Engineering, University of Cambridge, 1987.Google Scholar
8. Narasimha, R. and Prabhu, A. Equilibrium and relaxation in turbulent wakes. J Fluid Mech, 1972, 54, (1), 1–17.Google Scholar
9. Allen, J. S. and Cheng, S. I. Numerical solutions of the compressible Navier-Stokes equations for the laminar near wake. Phys Fluid, Jan 1970, 13, (1), 37–52.Google Scholar
10. Brailovskaya, I. Yu. Flow in the near wake. Sov Phys-Doklady, Sept 1971, 16, (3), 197–199.Google Scholar
11. Carter, J. E. Numerical Solutions of the Navier-Stokes Equations for the Supersonic Laminar Flow over a Two-Dimensional Compression Corner. NASA TR R-385, July 1972.Google Scholar
12. Dawes, W. N. Private Communication, 1986.Google Scholar
13. Vest, C. M. Holographic Interferometry, John Wiley & Sons. 1982.Google Scholar
14. Bryanston-Cross, P. J., Edwards, J. A. and Squire, L. C. Measurements in an unsteady two dimensional shock/boundary layer interaction. In: Whitehead, (ed). IUTAM Symposium 'Unsteady Aerodynamics of Turbomachines and Propellers'. Jesus College, Cambridge, 1984.Google Scholar
15. Franke, M. E. and Carr, D. L. Effects of Geometry on Open Cavity Flow Induced Pressure Oscillations. AIAA Paper 75-492, 1975.Google Scholar
16. Block, P. J. W. Noise Response of Cavities of Varying Dimensions at Subsonic Speeds. NASA-TN-D-8351, Dec. 1976.Google Scholar