Analysis of unsteady supersonic cavity flow employing an adaptive meshing algorithm

Abstract Some aspects of the numerical analysis of a supersonic cavity flow, including the effects of length scale, computational grid and time scale have been studied. A turbulent flow over a two-dimensional cavity has been analysed through solutions of the Reynolds-averaged Navier-Stokes equations. The effects of turbulence were modelled through a coupled solution of a k-ω turbulence model using compressibility corrections. A Riemann solver numerical scheme was employed. An adaptive mesh refinement technique has been used to capture the salient features of the transient fluid flow. Computational solutions have been obtained for cavities of length to depth ratios ( L D ) of 1, 3, and 5, and freestream Mach numbers of 1.5 and 2.5; conditions corresponding to experimental data. It has been found that a single mode dominated oscillation existed at solL D = 1 and that multiple mode dominated flows in the longer cavities. Frequency staging was observed for the long cavities. When the oscillation was weak at L D = 1, the predicted modes could be affected by the selection of the computational grid. The calculations were less sensitive to the grid characteristics for the longer cavities when the oscillation was strong.

[1]  P. Roe.  Approximate Riemann Solvers, Parameter Vectors, and Difference Schemes , 1997 .

[2]  X. Zhang,et al.  An investigation of supersonic oscillatory cavity flows driven by thick shear layers , 1990, The Aeronautical Journal (1968).

[3]  Xin Zhang.  An experimental and computational investigation into supersonic shear layer driven single and multiple cavity flowfields , 1988 .

[4]  David C. Wilcox,et al.  Dilatation-dissipation corrections for advanced turbulence models , 1992 .

[5]  P. Bradshaw,et al.  Turbulence Models for Compressible Boundary Layers , 1994 .

[6]  Donald P. Rizzetta,et al.  Numerical Simulation of Supersonic Flow Over a Three-Dimensional Cavity , 1987 .

[7]  K. Krishnamurty,et al.  Acoustic radiation from two-dimensional rectangular cutouts in aerodynamic surfaces , 1955 .

[8]  M. Berger,et al.  Adaptive mesh refinement for hyperbolic partial differential equations , 1982 .

[9]  D. Wilcox.  Reassessment of the scale-determining equation for advanced turbulence models , 1988 .

[10]  J. A. Edwards,et al.  Computational analysis of unsteady supersonic cavity flows driven by thick shear layers , 1988, The Aeronautical Journal (1968).

[11]  J. J. Quirk,et al.  An adaptive grid algorithm for computational shock hydrodynamics , 1991 .

[12]  J. A. Edwards,et al.  Computational analysis of unsteady cavity flows driven by thick shear layers , 1988 .

[13]  E. Covert,et al.  Flow-Induced Pressure Oscillations in Shallow Cavities , 1971 .

[14]  J. A. Edwards,et al.  Experimental Investigation of Supersonic Flow over Two Cavities in Tandem , 1992 .

[15]  W. L. Hankey,et al.  Analyses of Pressure Oscillations in an Open Cavity , 1980 .

[16]  Xin Zhang,et al.  Compressible cavity flow oscillation due to shear layer instabilities and pressure feedback , 1995 .

[17]  D. Wilcox.  Turbulence modeling for CFD , 1993 .

[18]  O. Rho,et al.  Numerical simulation of supersonic flow over double cavity , 1994 .

[19]  P. Roe.  CHARACTERISTIC-BASED SCHEMES FOR THE EULER EQUATIONS , 1986 .

[20]  A. F. Charwat,et al.  An Investigation of Separated Flows - Part I: The Pressure Field , 1961 .

[21]  Hanno H. Heller,et al.  Aerodynamically Induced Pressure Oscillations in Cavities - Physical Mechanisms and Suppression Concepts , 1975 .