Critical Mach Numbers of Circulation Control Airfoils as Determined by Finite-Difference Methods.

摘要

The critical Mach number of several circulation control elliptic airfoils is calculated for various circulation and angle-of-attack conditions. The full inviscid compressible flow equations were solved by finite-difference relaxation methods. The sections examined are candidates for use on helicopter rotor blades. Comparison with conventional sections are made. It is shown that the elliptic circulation control airfoils have a significantly higher critical Mach number. (Author)