Effects of sweep and angle of attack on boundary-layer transition on wings at Mach number 4.04 / Robert W. Dunning and Edward F. Ulmann.
Wind-tunnel tests were conducted at a Mach nmnber of 4.04 to determine the effects of leading-edge sweep, angle of attack, and leading-edge thiclmess on boundary-layer transition on flat-plate wings. In addition, some results were obtained on wings having rounded leading edges. The transition point...
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| Format: | Government Document Book |
| Language: | English |
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Washington, D.C. :
National Advisory Committee for Aeronautics,
1955.
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
3473. |
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PASCAL Offsite
| Call Number: |
Y 3.N 21/5:6/3473
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| Y 3.N 21/5:6/3473 | Available Place a Hold |