Perturbation field induced by line vortex in supersonic stream and downwash behind supersonic lifting surfaces are examined for purpose of establishing approximate methods for determining downwash behind supersonic wings; lifting line methods are presented for calculating supersonic downwash.
Line vortex theory for calculation of supersonic downwash
Nat Advisory Committee Aeronautics -- Tech Note
1949
54 pages
Diagrs, Charts
Report
English
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