The calculation of downwash behind supersonic wings with an application to triangular plan forms

Lomax, Harvard Sluder, Loma Heaslet, Max A
naca-report-957
1950


A method is developed consistent with the assumptions of small perturbation theory which provides a means of determining the downwash behind a wing in supersonic flow for a known load distribution. The analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading. The equivalence in subsonic and supersonic flow of the downwash at infinity corresponding to a given load distribution is proved.

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