DSMC computations for regions of shock/shock and shock/boundary layer interaction

Author:

Moss James1

Affiliation:

1. NASA, Langley Research Center, Hampton, VA

Publisher

American Institute of Aeronautics and Astronautics

Reference61 articles.

1. where

2. Figures 2 through 8 present results of the calculations first reported in Refs. 4 and 5 that describe the flow-field features and surface results for the ONERA hollow cylinder-flare test case. The experimental value for free-stream Reynolds number is 18916. where the viscosity (3.29 x 106Pa * s) is given by the Sutherland expression and the characteristic dimension is the cylinder length L. Also presented are comparisons of the surface results forheating, pressure, and the extent of separation with the experimental measurements described in Refs. 6, 7, and 19. The current results are those obtained with the finest grid resulting from the grid resolution study described in Ref. 4. The previous calculations show that the extent of separation is quite sensitive to the grid a much smaller separation region is obtained with a coarse grid. Data included in Fig. 2 provide information concerning the grid and simulation parameters for the finest grid solution. A four-region computational domain was used where each cell was subdivided into four subcells (2 x 2). The time step in each of the four regions had values of 75, 75, 28, and 15 ns, respectively.

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1. Global stability of supersonic flow over a hollow cylinder/flare;Journal of Fluid Mechanics;2023-11-21

2. On an Axisymmetric Direct Simulation Monte Carlo Method;International Journal of Computational Fluid Dynamics;2021-05-28

3. Factors influencing flow steadiness in laminar boundary layer shock interactions;AIP Conference Proceedings;2016

4. Shock-shock interactions for a double wedge configuration in different gases;53rd AIAA Aerospace Sciences Meeting;2015-01-03

5. Progress in shock wave/boundary layer interactions;Progress in Aerospace Sciences;2015-01

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