YS-915 (ys915-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: YS-915 (ys915-il) Reynolds number: 50,000 Max Cl/Cd: 21.9 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ys915-il-50000-n5.txt Download as CSV file: xf-ys915-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: YS-915
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5179 0.09576 0.08902 -0.0441 1.0000 0.0323
-9.250 -0.5357 0.08927 0.08260 -0.0485 1.0000 0.0309
-8.750 -0.5641 0.08251 0.07584 -0.0496 1.0000 0.0301
-8.500 -0.5790 0.07988 0.07325 -0.0480 1.0000 0.0298
-8.250 -0.5969 0.07692 0.07030 -0.0459 1.0000 0.0296
-8.000 -0.6104 0.07375 0.06710 -0.0442 1.0000 0.0294
-7.750 -0.6220 0.07050 0.06377 -0.0425 1.0000 0.0291
-7.500 -0.6308 0.06721 0.06036 -0.0408 1.0000 0.0288
-7.250 -0.6379 0.06363 0.05662 -0.0390 1.0000 0.0285
-7.000 -0.6417 0.06004 0.05280 -0.0373 1.0000 0.0282
-6.750 -0.6417 0.05659 0.04908 -0.0356 1.0000 0.0279
-6.500 -0.6392 0.05291 0.04506 -0.0337 1.0000 0.0276
-6.250 -0.6327 0.04961 0.04138 -0.0320 1.0000 0.0273
-6.000 -0.6236 0.04616 0.03748 -0.0301 1.0000 0.0272
-5.750 -0.6110 0.04294 0.03378 -0.0283 1.0000 0.0272
-5.500 -0.5955 0.04002 0.03039 -0.0266 1.0000 0.0273
-5.250 -0.5774 0.03739 0.02728 -0.0249 1.0000 0.0276
-5.000 -0.5571 0.03494 0.02438 -0.0231 1.0000 0.0284
-4.750 -0.5356 0.03289 0.02195 -0.0214 1.0000 0.0294
-4.500 -0.5149 0.03095 0.01976 -0.0196 1.0000 0.0309
-4.250 -0.4968 0.02914 0.01785 -0.0179 1.0000 0.0346
-4.000 -0.4777 0.02775 0.01625 -0.0164 1.0000 0.0450
-3.750 -0.4578 0.02630 0.01438 -0.0148 1.0000 0.0539
-3.500 -0.4350 0.02441 0.01250 -0.0142 1.0000 0.0829
-3.250 -0.4197 0.02163 0.01171 -0.0128 1.0000 0.4290
-3.000 -0.4143 0.02130 0.01212 -0.0072 1.0000 0.5855
-2.750 -0.3949 0.02104 0.01170 -0.0051 1.0000 0.6270
-2.500 -0.3717 0.02074 0.01114 -0.0041 1.0000 0.6534
-2.250 -0.3489 0.02046 0.01071 -0.0030 1.0000 0.6831
-2.000 -0.3259 0.02019 0.01034 -0.0020 1.0000 0.7200
-1.750 -0.3010 0.01994 0.01008 -0.0012 1.0000 0.7711
-1.500 -0.2590 0.01983 0.00981 -0.0038 1.0000 0.8555
-1.250 -0.1907 0.01999 0.00966 -0.0127 1.0000 1.0000
-1.000 -0.1725 0.01997 0.00935 -0.0118 1.0000 1.0000
-0.750 -0.1532 0.02002 0.00914 -0.0110 1.0000 1.0000
-0.500 -0.1335 0.02011 0.00902 -0.0101 1.0000 1.0000
-0.250 -0.1135 0.02023 0.00895 -0.0093 1.0000 1.0000
0.000 -0.0932 0.02039 0.00887 -0.0085 1.0000 1.0000
0.250 -0.0729 0.02057 0.00891 -0.0077 1.0000 1.0000
0.500 -0.0526 0.02077 0.00900 -0.0070 1.0000 1.0000
0.750 -0.0323 0.02100 0.00914 -0.0062 1.0000 1.0000
1.000 -0.0119 0.02125 0.00933 -0.0055 1.0000 1.0000
1.250 0.0083 0.02153 0.00957 -0.0048 1.0000 1.0000
1.500 0.0392 0.02205 0.01008 -0.0063 0.9955 1.0000
1.750 0.0721 0.02260 0.01064 -0.0082 0.9895 1.0000
2.000 0.1062 0.02324 0.01132 -0.0103 0.9834 1.0000
2.250 0.1386 0.02377 0.01193 -0.0121 0.9763 1.0000
2.500 0.1740 0.02445 0.01272 -0.0144 0.9696 1.0000
2.750 0.2052 0.02493 0.01335 -0.0159 0.9611 1.0000
3.000 0.2394 0.02552 0.01425 -0.0179 0.9528 1.0000
3.250 0.2758 0.02613 0.01509 -0.0203 0.9440 1.0000
3.500 0.3086 0.02660 0.01581 -0.0219 0.9331 1.0000
3.750 0.3433 0.02708 0.01660 -0.0237 0.9214 1.0000
4.000 0.3798 0.02750 0.01741 -0.0257 0.9084 1.0000
4.250 0.4202 0.02781 0.01838 -0.0280 0.8933 1.0000
4.500 0.4962 0.02415 0.01562 -0.0303 0.7951 1.0000
4.750 0.5546 0.02532 0.01289 -0.0283 0.0769 1.0000
5.000 0.5758 0.02709 0.01469 -0.0269 0.0615 1.0000
5.250 0.6038 0.02868 0.01648 -0.0266 0.0447 1.0000
5.500 0.6510 0.03127 0.01929 -0.0291 0.0382 1.0000
5.750 0.6992 0.03470 0.02304 -0.0313 0.0356 1.0000
6.000 0.7297 0.03735 0.02623 -0.0307 0.0321 1.0000
6.250 0.7518 0.03980 0.02925 -0.0294 0.0287 1.0000
6.500 0.7682 0.04266 0.03234 -0.0280 0.0258 1.0000
6.750 0.7832 0.04622 0.03628 -0.0260 0.0253 1.0000
7.000 0.7949 0.04965 0.04012 -0.0235 0.0252 1.0000
7.250 0.8040 0.05285 0.04373 -0.0207 0.0252 1.0000
7.500 0.8104 0.05607 0.04735 -0.0177 0.0254 1.0000
7.750 0.8142 0.05929 0.05094 -0.0146 0.0256 1.0000
8.000 0.8152 0.06254 0.05455 -0.0114 0.0259 1.0000
8.250 0.8106 0.06587 0.05827 -0.0078 0.0265 1.0000
8.500 0.8025 0.06940 0.06210 -0.0046 0.0272 1.0000
8.750 0.7914 0.07294 0.06586 -0.0016 0.0277 1.0000
9.000 0.7764 0.07629 0.06936 0.0013 0.0282 1.0000
9.250 0.7603 0.07997 0.07316 0.0031 0.0286 1.0000
9.500 0.7453 0.08390 0.07718 0.0037 0.0291 1.0000
9.750 0.7300 0.08851 0.08184 0.0030 0.0296 1.0000
10.000 0.7164 0.09375 0.08711 0.0009 0.0301 1.0000
10.250 0.7061 0.09951 0.09287 -0.0024 0.0308 1.0000
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Polar data table (+)
Polar graphs
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