Analysis of circulation-controlled airfoils in transonic flow

A method developed for the analysis of the transonic viscous flow over circulation-controlled airfoils is described. A finite-differe nce method is used to solve the inviscid portion of the flow, and a combination of integral and finite-difference methods is used to calculate the development of the compressible viscous layers. An iterative procedure is employed to give solutions which satisfy the trailing-edge Kutta condition and incorporate the interaction between the viscous and potential regions of the flow. Comparisons between calculated and experimental results show good agreement for surface pressure distributions and lift coefficients over a range of blowing momentum coefficients and Mach numbers. a B c CE C = Nomenclature speed of sound