Numerical and experimental study to evaluate aerodynamic characteristics in supersonic\now over a double wedge airfoil is carried out using Fluent software and a supersonic\nwind tunnel, respectively. The Schlieren visualization method was also used\nto develop the experimental step of this study. The supersonic wind tunnel reached a\nproximately a Mach number of 1.8. The result got showed oblique shock waves visualization\non double-wedge airfoil and the numerical simulation, the flow behavior as\nfunction of Mach number, pressure, temperature and density in the flow field on the\ncomputational model. The simulation allowed to observe the shock wave and the\nexpansion fan in the leading and tailing edge of double-wedge airfoil. From the numerical\nand experimental comparison, an agreement at the shock wave angle and\nMach number was observed, with a difference about 1.17% from the experimental\nresults
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