Pressure distribution and damping in steady pitch at supersonic Mach numbers of flat swept-back wings having all edges subsonic / Harold J. Walker and Mary B. Ballantyne.
The method of the superposition of conical flows is used to calculate both the pressure distribution and the derivative for the damping in steady pitch at supersonic Mach numbers of thin, flat, swept-back wings having all edges subsonic and straight. In general, the method consists ins superposing i...
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
1950.
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
2197. |
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PASCAL Offsite
| Call Number: |
Y 3.N 21/5:6/2197
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| Y 3.N 21/5:6/2197 | Available Place a Hold |