TY - JOUR
T1 - A grid strategy for predicting the space plane's hypersonic aerodynamic heating loads
AU - Qu, Feng
AU - Chen, Jiaojiao
AU - Sun, Di
AU - Bai, Junqiang
AU - Zuo, Guang
N1 - Publisher Copyright:
© 2019 Elsevier Masson SAS
PY - 2019/3
Y1 - 2019/3
N2 - In the design of the hypersonic space plane which can conduct repeatable space exploration, how to predict aerodynamic heating loads accurately is of significance to devise the thermal protection system. In this paper, the grid strategy specific to structured grids for predicting the hypersonic aerodynamic heating loads is studied. The three-dimensional Navier–Stokes (NS) equations are simulated. The widely used flux schemes, such as Roe, AUSM+, and AUSMPW+, are adopted and the code employed is validated. Numerical test cases, including hypersonic viscous flow over a blunt body and hypersonic viscous flow over a blunt cone, are conducted. By adopting different cell Reynolds numbers and different aspect ratios of cells near the shock, results of these two test cases suggest that in hypersonic heating loads’ predictions, it is better to adopt grids with the cell Reynolds number no larger than 20. Also, the aspect ratio of cells near the shock should be larger than 6. Hypersonic viscous flow over the X33 vehicle indicates that the aerodynamic heating loads of the hypersonic space plane can be accurately predicted by adopting the grid strategy proposed in this study.
AB - In the design of the hypersonic space plane which can conduct repeatable space exploration, how to predict aerodynamic heating loads accurately is of significance to devise the thermal protection system. In this paper, the grid strategy specific to structured grids for predicting the hypersonic aerodynamic heating loads is studied. The three-dimensional Navier–Stokes (NS) equations are simulated. The widely used flux schemes, such as Roe, AUSM+, and AUSMPW+, are adopted and the code employed is validated. Numerical test cases, including hypersonic viscous flow over a blunt body and hypersonic viscous flow over a blunt cone, are conducted. By adopting different cell Reynolds numbers and different aspect ratios of cells near the shock, results of these two test cases suggest that in hypersonic heating loads’ predictions, it is better to adopt grids with the cell Reynolds number no larger than 20. Also, the aspect ratio of cells near the shock should be larger than 6. Hypersonic viscous flow over the X33 vehicle indicates that the aerodynamic heating loads of the hypersonic space plane can be accurately predicted by adopting the grid strategy proposed in this study.
KW - Aspect ratio
KW - Cell Reynolds number
KW - Grid strategy
KW - Hypersonic heating prediction
UR - https://www.scopus.com/pages/publications/85061525981
U2 - 10.1016/j.ast.2019.01.049
DO - 10.1016/j.ast.2019.01.049
M3 - 文章
AN - SCOPUS:85061525981
SN - 1270-9638
VL - 86
SP - 659
EP - 670
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
ER -