Theoretical analysis, based on linearized equation for supersonic flow; by restriction to case for which Mach lines from wing apex lie behind leading edge, simplified treatment was possible.
Characteristics of thin triangular wings with triangular-tip control surfaces at supersonic speeds with Mach lines behind leading edge
Nat Advisory Committee Aeronautics -- Tech Note
1948
33 pages
Article (Journal)
English
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Engineering Index Backfile | 1952
|Engineering Index Backfile | 1948
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