Analyses Of Static Pressure In Oblique Shockwave On The Probe Tip

Abstract

This article deals with the debugging analyses of Ansys Fluent for supersonic flowanalyzes. It is about analyzes on which the debugging of Ansys Fluent was made for analyzes ofsupersonic flow circumfluent the tip of the probe compared with the theory of isoentropic onedimensionalflow as a basic step for further analyzes in low pressures. The results shown in this paperwill further serve as a basis for experimental measuring of given problem.