摘要：Traditionally, on the initial design stage of rocket and artillery systems are used simplified analytical techniques for the aerodynamic calculations with the adjustment of the drag-function standard for form factor or the calculation with using algebraic formulas proposed by Dorodnitsin, Krasnov and etc. However, these techniques, adapted for ranges of transonic and supersonic speeds, are give unreasonably low accuracy for the subsonic range. We have studied the possibility of using existing software packages for example, ANSYS CFX to the modeling of aerodynamics differential equations in partial derivatives in finite difference form. On the test case – the American standard form ARROW shown that the calculations in ANSYS CFX were generally in line with those ARROW using the theory of turbulence k-ε. The discrepancy at M
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