Howard W. Emmons
The effects of compressibility on the flow about the NACA 0012 airfoil in a wind tunnel and in free air have been investigated by the relaxation method. The details of how the numerical work is carried out have been described previously. The solutions obtained cover the incompressible case, the cases when the entire flow is subsonic, the case when supersonic regions are present, and several cases when the supersonic region terminates in shock waves, that is, post-critical flow.
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