Washington, D.C. : National Advisory Committee for Aeronautics, 1949.
54 p. : ill ; 28 cm.
NACA TN No. 1925.
Includes bibliographical references.
The perturbation field induced by a line vortex in a supersonic stream and the downwash behind a supersonic lifting surface are examined for the purpose of establishing approximate methods for determining the downwash behind supersonic wings. Lifting-line methods are presented for calculating supersonic downwash.
A bent lifting line and an unbent lifting line (horseshoe-vortex system) are used to compute downwash behind triangular wings. An unbent lifting line is used to compute downwash behind rectangular wings. The results are compared with the exact linearlized solutions.
Copy 1 bound with 1915. 9123542 (parent record's ckey)