Abstract

The Transonic Wind Tunnel is used to test aircraft models at speeds from Mach number 0.2 to 1.4. Transonic flows consist of mixed subsonic and supersonic flow regions. Shocks can occur in these flows but often do not have a strong enough pressure gradient to assume flow properties similar to those of supersonic flows. These regions are difficult to model mathematically because they have characteristics of subsonic and supersonic flows. In this regard, the paper is aiming towards the design and analysis of the transonic wind tunnel performance by considering two phases namely automated design and its evaluation. Modern optimization software is combined with isentropic relations; simulations are analyzed to design a Mach 1.2 nozzle with maximum test length. The optimal design has an unconventional shape described as compound curvature, which makes the contour appear slightly wavy in AutoCAD. The same is evaluated and found satisfactory for the proposed modification of the test section in the wind tunnel in fluent analysis.