Expressions for damping derivatives derived by means of linearized theory; wing represented by unknown distribution of doublets; integral equation containing unknown distribution is set up and solved by analogy with known incompressible flow relations.
Damping in pitch and roll of triangular wings at supersonic speeds
Nat Advisory Committee Aeronautics -- Tech Note
1948
29 pages
Report
Englisch
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Damping in pitch and roll of triangular wings at supersonic speeds
Engineering Index Backfile | 1948
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