Performance Test of the Low-Subsonic Wind Tunnel Present at SU Campus

Abstract

The wind tunnel is a tool used in aerodynamic research to study the effects of wind moving over a solid object. This thesis work is done to performance test of a low-subsonic wind tunnel by our Sonargaon university lab. We get Mach number 0.02 and the Reynolds Number is 53578 for a designed test airfoil of 150 mm for a test section of 910 mm of length. With the target of having a flow speed about 7.02 m/s at the test section of 0.32 m2 cross-sectional area all the other sections of the wind tunnel have been designed and using a sixth-order polynomial equation. The wind tunnel operates at speeds below Mach 0.3 and using Java foil software for calculation.