Application of the Method of Integral Relations (MIR) to Transonic Airfoil Problems. Part II. Inviscid Supercritical Flow About Lifting Airfoils with Embedded Shock Wave

摘要

Numerical procedures developed in a previous part of the report for applying the method of integral relations to transonic airfoil problems are extended to lifting cases. A modification enables any desired number of strips and size of integration domain to be used. Full inviscid flow equations are approximated by second-order polynomials in transverse direction in a physical plane. Numerical procedures including iterative processes are formulated for the case of high subsonic free-stream Mach numbers. Cartesian coordinates are employed except near the leading edge region where the use of a body coordinate system is convenient. Results are presented for supercritical flows past various airfoils, including two conventional, one advanced, and two shockless airfoils. (Author)