Downwash in the vertical and horizontal planes of symmetry behind a triangular wing in supersonic flow

Harvard Lomax, Loma Sluder
naca-tn-1803
Jan 1949


A method developed in a previous report for finding the induced velocity field behind a supersonic wing with known load distribution is used to find the downwash behind a triangular wing with subsonic leading edge. Results are given for the chord plane in the extended vortex wake of the wing and for the vertical plane of symmetry up to about 20 percent of the wing span above the plane of the wing.

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