This work investigates the differences between hypersonic aerodynamic coefficients computed with two different tools, having two different levels of fidelity: a high fidelity code implementing the Direct Simulation Monte Carlo method and a low fidelity one based on the approximated hypersonic local surface inclination technique. Different multivariate correction factors to reduce the low-fidelity tool error have been defined using a High Dimensional Model Representation algorithm. The low fidelity approach with the implemented correction factor has been tested on different space objects, the Gravity field and steadystate Ocean Circulation Explorer satellite and a 3U CubeSat with a deployed drag sail; the results are presented and commented.
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