Experimental Investigation of a Supersonic Wind Tunnel under Different Operating Conditions

Abstract

This paper mainly describes the analysis and design of supersonic wind tunnel in order to reduce the power consumption using optimization techniques under to different operating conditions. In this analysis, a three-dimensional Navier–Stokes equation is used to investigate the flow field of a high pressure ratio centrifugal compressor for Supersonic Wind Tunnel. Such a compressor consists of a double-splitter impeller followed by a vaned diffuser. Particular attention is focused on the analysis of the vaned diffuser, size of the test section, speed of compressor, nozzle size, and velocity of air, designed for supersonic conditions. The diffuser is characterized by a complex three-dimensional flow field and influenced by the unsteady interaction with the impeller. Design of test section is based on the standard principles. The present experimental investigation has been programmed to conduct as per NASA standard and it is conducted in Aerodynamics laboratory under the Department of Aeronautical Engineering, Mount Zion College of Engineering and Technology, Pudukkottai, Tamil Nadu, India. The centrifugal compressor and vacuum pump are used to develop a supersonic velocity in the test section.