Approximate transonic profile flow at incidence with shock

The present work uses integral equation method to develop a procedure for computing approximately steady inviscid transonic supercritical profile flow with shock past a thin unsymmetrical airfoil at small incidence. Starting from the shock-free solution at non-zero incidence of Chakraborty [9] and adopting a procedure similar to that of Hosokawa [12], the present work extends the work of Mitra [13] to the general case of lifting flow. Supercritical flow past NACA 0012 profile at different Mach numbers have been computed and compared with theoretical results of Garabedian and Korn [14], [15]. The agreements are satisfactory.