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Mach number determination of hypersonic flow with a new schlieren system
Slavica Ristić Aleksandar Vitić Slobodan Vučković
The possibilities of undisturbed flow Mach number determination, in the T-34 hypersonic wind tunnel, using a shape shock wave about a test model are analyzed. The used analytical method, concerns Billig's empirical equation. The visualization of shock waves is given using the schlieren method. A new schlieren system, Toepler type is designed and made in the VTI. The new schlieren system is used for flow field visualization and the Mach number is determined in the test section of the hypersonic wind tunnel. It is proved that the Mach number of an undisturbed flow is M=7.
Key words: hypersonic flow, hypersonic wind tunnel, shock waves, flow visualization, schlieren method. |