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Journal of Chemical Technology and Applications
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Volume 2
J Chem Tech App 2018, Volume 2
AERODYNAMIC DATABASE GENERATION AND MANAGEMENT OF
REENTRY SPACE VEHICLE
Meisam Mohammadi-Amin
Aerospace Research Institute, Iran
F
or reentry vehicles with the wide range of flight envelope, a large number of coefficients are required to ful ll the aerodynamic
multi-dimensional tables. To reduce the number of high- delity analyses without considerable accuracy loss, a proper combi-
nation of sampling, interpolation, and data fusion methods are required. The proposed framework includes a multi-dimensional
nonlinear interpolation (Kriging), a data fusion (co-Kriging) and a sampling method (Latin Hypercube Sampling) in an integrated
structure coupled with aerodynamic solvers. The main idea is applying Kriging interpolation method on cheap data points to esti-
mate the aerodynamic coefficients’ trends over the entire space of variables, and re ning the trends with accurate sample points
and data fusion. Latin hypercube sampling method is used for optimal distribution of cheap samples and initial accurate sample
points. After a few high- delity analyses, co-Kriging data fusion method is applied for the improving aerodynamic database del-
ity via augmentation of trends with the accurate data. The process iterates using new accurate sample points (located on maxi-
mummean squared error) until the mean squared error criteria is met. Cheap data are produced by a variety of low- delity solvers
e.g. potential and Euler solvers and high- delity data are calculated by full Navier-Stokes solvers (CFD). For each regime of the
flight envelope, i.e. subsonic, transonic, supersonic and hypersonic and each type of reentry con gurations, e.g. Apollo-type,
grid studies are done separately and the optimum grid and solver settings are implemented into the framework to facilitate the
automatic aerodynamic database generation and management. All parts of the presented framework are validated independently
in compare to some reference test cases. To show the capabilities of the developed framework, Orion reentry capsule with com-
plete flight envelope is assumed as a sample. Orion aerodynamic database is generated efficiently and the obtained results are
in good agreement in comparison with experimental data.