A reduced order modeling for aerothermodynamic of hypersonic vehicles based on surrogate method

Accurate and efficient estimation of aerodynamic heating is the basic prerequisite of theaerothermo-elasticity analysis. In order to solve the engineering adaptability problems of hypersonic aerothermodynamics calculation, numerical superprecision calculation and experimental investigation, a novel estimation method based on surrogate method for aerothermdynamic was proposed. Furthermore, a reduced order modeling (ROM) framework for aerothermodynamic was developed. Test results for the three-dimensional aerothermodynamics over a typical hypersonic control surface indicate that the average absolute errors, L_∞ and NRSME by SLE are all smaller than those by lhsdesign using the same samlping points and the same sorrogate methods. So the SLE sampling method can help to improve the precision of ROM. Comparing the results of ROMs for the three-dimensional aerothermodynamics over a hypersonic control surface, it is indicated that the precision of Kriging is better than that of RBF. The developed ROMs for the three-dimensional surface show higher precision and efficiency for hypersonic aerothermodynamic.