Design and Analysis of Closed-type Free Jet Test Section for Hypersonic Wind Tunnel

In this research, procedure of aerodynamics design for hypersonic wind tunnel test section is investigated by using computational fluid dynamics. The type of test section is chosen closed-type free jet. First, conceptual design is done by using the available statistical data in the hypersonic wind tunnel test section in the world. Then, quality of design is investigated by numerical simulation by solving Navier-Stokes equations in compressible, viscous (k-w SST model) and axisymmetric form. With changing the parameters of the test section, the test section dimensions have been optimized. The important parameters in test section are length of the test section, the test section diameter, the diameter of the inlet diffuser, the diffuser and the nozzle indentation inside the test section. Design criteria are chosen the formation of uniform flow, better swallow the slip line and the flow deflection in the test section. Finally, dimensions, specifications and aerodynamics functional requirements of the hypersonic wind tunnel test section have been determined at Mach 5 to 7. The effect of cone and curved nozzles is also investigated for flow quality in test section of wind tunnel.