Double Wedge Airfoil Analysis
Project Goals:The goal of this project was to write code to calculate the aerodynamic forces and coefficients of lift and drag for a double wedge airfoil given the upstream Mach number, pressure, angle of attack, and front and rear half-angles.
This project was coded in MATLAB. The code utilizes a set of original functions to calculate pressure and Mach number variations across the oblique shocks and expansion fans caused by the double wedge shape. These pressures are combined with the airfoil geometry to calculate the aerodynamic forces and coefficients. This project was completed as part of ME425: Compressible Flow and Propulsion |