Effect of Mach number on the flow and application of compressibility corrections in a two-dimensional subsonic-transonic compressor cascade having varied porous-wall suction at the blade tips / William B. Briggs.
A 65-(12)10 compressor blade cascade was evaluated at design geometry for Mach numbers from 0.12 to 0.89 with the boundary layer controlled through upstream slots and porous walls. The suction control was specified by a two-dimensionality criterion. The data show the effect of Mach number on turning...
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| Other title: | Technical report archive and image library. |
| 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) ;
2649. |
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Internet
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| Call Number: |
Y 3.N 21/5:6/2649
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