Abstract
This paper is mainly focused on Supersonic Laminar Flow at Mach 3 for biconvex and double wedge airfoils. The coefficient of lift (Cl), coefficient of drag (Cd), and coefficient of moment along the respective airfoils are being analysed. The geometry of these is generated using the Designmodeler of ANSYS. Further, meshing is also achieved by ANSYS with around 50000 nodes which is satisfactory for the current flow analysis. The total number of iterations being set for the particular simulation is 1000. This article covers the approach of the Kutta-Joukowski theorem, from which we know that flow circulation impacts the lift of the airfoil and how it changes for biconvex and double wedge airfoils. Decisively, this paper delivers provides pressure, heat transfer, and velocity distribution for both the airfoils. This paper gives a comparative study of both the double wedge and the biconvex airfoils at MACH 3, zero angle of attack. The study will be analysing both the airfoils in 3D as well as in 2D.
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