A Numerical Study of Viscous Shock-on-shock Hypersonic Flows with a Modified Steger-Warming Flux Split Scheme PDF Download
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Author: Datta Gaitonde
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Category :
Languages : en
Pages :
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Author: Datta Gaitonde
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Datta V. Gaitonde
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Category : Aerodynamics, Hypersonic
Languages : en
Pages : 64
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The interaction of an impinging shock with the bow-shock generated by a blunt geometry is examined numerically for hypersonic (Mach 8, perfect gas) flows with modified Steger-Warming flux-split scheme. The modifications are designed to reduce numerical dissipation in the boundary layer thus improving the resolution and accuracy of the resulting algorithm. The full 2-D Navier- Stokes equations are solved in finite-volume formulation with central differencing for viscous terms and residual driven line Gauss-Seidel relaxation for time advancement. Grid resolution studies are performed. For a Type IV interaction, comparison with surface pressure and heat-transfer rates display good overall agreement with experimental values. For a Type III+ interaction, a detailed comparison is made with experimental surface quantities and a computation with Van Leer's flux-splitting algorithm. The peak amplification of pressure is modestly overpredicted with the current algorithm. The computed peak heat transfer is comparable to that obtained in previous research with Van Leer's splitting, although anomalous behavior is observed in the vicinity of the stagnation point. This behavior may be eliminated with appropriate corrections.
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Languages : en
Pages : 0
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The interaction of an impinging shock with the bow-shock generated by a blunt geometry is examined numerically for hypersonic (Mach 8, perfect gas) flows with modified Steger-Warming flux-split scheme. The modifications are designed to reduce numerical dissipation in the boundary layer thus improving the resolution and accuracy of the resulting algorithm. The full 2-D Navier- Stokes equations are solved in finite-volume formulation with central differencing for viscous terms and residual driven line Gauss-Seidel relaxation for time advancement. Grid resolution studies are performed. For a Type IV interaction, comparison with surface pressure and heat-transfer rates display good overall agreement with experimental values. For a Type III+ interaction, a detailed comparison is made with experimental surface quantities and a computation with Van Leer's flux-splitting algorithm. The peak amplification of pressure is modestly overpredicted with the current algorithm. The computed peak heat transfer is comparable to that obtained in previous research with Van Leer's splitting, although anomalous behavior is observed in the vicinity of the stagnation point. This behavior may be eliminated with appropriate corrections.
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Category : Fluid dynamics
Languages : en
Pages : 530
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Category : Aeronautics
Languages : en
Pages : 304
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Author: J. S. Shang
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Category : Maxwell equations
Languages : en
Pages : 54
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Numerical procedures for solving the time-domain Maxwell equations based on the theory of characteristics were successfully developed. Both explicit and implicit methods were formulated by the time-central and spatial-windward algorithm to better describe wave motion. A new trapezoidal consistent implicit scheme was shown to be unconditionally stable for the linear initial value system and was able to generate numerical solutions comparable to those of the established explicit method. The formulation of the three-dimensional system including generalized coordinate system was completed but not explored. The present 2-D results on Cartesian frame demonstrated a potential for numerical efficiency improvement. Time-domain Maxwell equation, Trapezoidal consistent implicit scheme, Cartesian frame.
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Category :
Languages : en
Pages : 250
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Category : Aerospace planes
Languages : en
Pages : 526
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Author: Goetz H. Klopfer
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Category : Aerodynamics, Hypersonic
Languages : en
Pages : 16
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Author: Datta V. Gaitonde
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ISBN:
Category : Viscous flow
Languages : en
Pages : 74
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This effort investigates the accuracy of some flux-split algorithms in high-speed viscous flows. Three methods are examined: (1) MacCormack and Candler's (MC) scheme, (2) the van Leer (vL) scheme and (3) the method of Roe. The problems studied include the blunt body flow at Mach 16 and the flow past a 240 compression corner at Mach 14. Higher order accuracy is obtained with the MUSCL approach. Viscous terms are centered in the full Navier-Stokes cell- centered implicit finite volume simulation. The results indicate a relative similarity of predicted surface pressure with all methods on both flows. However, considerable disparity exists in heat transfer prediction especially on the coarser meshes with van Leer's splitting exhibiting the most overprediction. Generally however, this disparity-diminishes as the grid is refined. The occurrence of anomalous carbuncle solutions with Roe's scheme may be suppressed with appropriate increase in entropy cutoff with no significant penalty in accuracy. For the ramp flow, the MC method predicts the size of the separated- flow region most accurately, though some overprediction of heat transfer is observed. Roe's algorithm, and on the finer grids, van Leer's method also exhibit comparable results.
