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In this article computer modeling of the aerodynamic coefficients for a high-speed aircraft model, which is analog to X-43 at Mach number M = 7 is performed. Calculation was realized using original and modified copyright computer codes (UST3D and UST3D-AUSMPW), which allow modeling the aerothermodynamic characteristics of aircraft with random geometry using three-dimensional unstructured tetrahedral grids. These copyright computer codes implement a model of viscous compressible heat-conducting gas, described by a spatial non-stationary system of Navier ‒ Stokes equations. The theoretical aspects of aerothermodynamics computer modeling for high-speed aircraft are considered. Cross-verification copyright computer codes was implemented using distribution of the aerodynamic parameters, values of aerodynamic characteristics, as well as the time of solution. Both copyright computer codes gives a fairly reliable picture of the distribution for sought-for quantities fields, and also calculate the aerodynamic characteristics with high accuracy relative to each other.

Calculation of aerothermodynamics for high-speed aircraft X-43 using computer code UST3D and UST3D-AUSMPW