Span load distributions resulting from angle of attack, rolling, and pitching for tapered sweptback wings with streamwise tips. : Supersonic leading and trailing edges / John C. Martin and Isabella Jeffreys.
On the basis of the linearized supersonic-flow theory the span load distributions resulting from constant angle of attack, from steady rolling, and from steady pitching were calculated for a series of thin sweptback tapered wings with streamwise tips and with supersonic leading and trailing edges. T...
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
1952.
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
2643. |
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PASCAL Offsite
| Call Number: |
Y 3.N 21/5:6/2643
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| Y 3.N 21/5:6/2643 | Available Place a Hold |