USA 45 AIRFOIL (usa45-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 45 AIRFOIL (usa45-il) Reynolds number: 100,000 Max Cl/Cd: 32.99 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa45-il-100000.txt Download as CSV file: xf-usa45-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: USA 45 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2849 0.10398 0.09935 -0.0312 1.0000 0.1222
-9.500 -0.2956 0.10144 0.09689 -0.0332 1.0000 0.1271
-9.250 -0.3392 0.09936 0.09501 -0.0387 1.0000 0.1289
-9.000 -0.2982 0.09477 0.09038 -0.0334 1.0000 0.1327
-8.750 -0.2917 0.09224 0.08790 -0.0323 1.0000 0.1368
-8.500 -0.3089 0.08978 0.08556 -0.0334 1.0000 0.1421
-8.250 -0.3632 0.08802 0.08404 -0.0352 1.0000 0.1438
-8.000 -0.4099 0.08685 0.08299 -0.0328 1.0000 0.1442
-7.750 -0.3385 0.08217 0.07831 -0.0293 1.0000 0.1502
-7.500 -0.3634 0.08090 0.07718 -0.0259 1.0000 0.1520
-7.250 -0.3954 0.07999 0.07640 -0.0218 1.0000 0.1528
-7.000 -0.4193 0.07455 0.07087 -0.0313 0.9880 0.1616
-6.750 -0.3744 0.07113 0.06748 -0.0335 0.9807 0.1724
-6.500 -0.3418 0.06631 0.06261 -0.0393 0.9693 0.1852
-6.250 -0.3135 0.06157 0.05778 -0.0451 0.9554 0.1998
-6.000 -0.2841 0.05727 0.05337 -0.0499 0.9410 0.2160
-5.750 -0.2527 0.05346 0.04946 -0.0538 0.9266 0.2350
-5.500 -0.2545 0.03562 0.02872 -0.0586 0.9085 0.0988
-5.250 -0.2196 0.03212 0.02490 -0.0599 0.8933 0.0973
-5.000 -0.1840 0.02937 0.02174 -0.0608 0.8765 0.0967
-4.750 -0.1495 0.02754 0.01942 -0.0610 0.8570 0.0986
-4.500 -0.1195 0.02568 0.01723 -0.0605 0.8324 0.1002
-4.250 -0.0861 0.02384 0.01520 -0.0606 0.8083 0.1023
-4.000 -0.0573 0.02265 0.01384 -0.0599 0.7792 0.1052
-3.750 -0.0298 0.02179 0.01275 -0.0589 0.7497 0.1103
-3.500 -0.0027 0.02092 0.01164 -0.0579 0.7218 0.1158
-3.250 0.0231 0.02014 0.01079 -0.0569 0.6965 0.1230
-3.000 0.0470 0.01946 0.01003 -0.0556 0.6727 0.1328
-2.750 0.0694 0.01889 0.00947 -0.0542 0.6523 0.1522
-2.500 0.0896 0.01806 0.00886 -0.0523 0.6351 0.2071
-2.250 0.0972 0.01607 0.00850 -0.0486 0.6211 0.5163
-2.000 0.1520 0.01602 0.00928 -0.0498 0.6029 0.8657
-1.750 0.2633 0.01735 0.00997 -0.0621 0.5815 0.9500
-1.500 0.3804 0.01757 0.00963 -0.0786 0.5606 0.9945
-1.250 0.4143 0.01752 0.00931 -0.0805 0.5498 1.0000
-1.000 0.4328 0.01762 0.00929 -0.0794 0.5405 1.0000
-0.750 0.4527 0.01776 0.00920 -0.0783 0.5331 1.0000
-0.500 0.4718 0.01792 0.00928 -0.0772 0.5250 1.0000
-0.250 0.4922 0.01809 0.00927 -0.0762 0.5182 1.0000
0.000 0.5119 0.01831 0.00940 -0.0751 0.5110 1.0000
0.250 0.5320 0.01852 0.00949 -0.0740 0.5041 1.0000
0.500 0.5532 0.01880 0.00960 -0.0730 0.4986 1.0000
0.750 0.5722 0.01911 0.00991 -0.0717 0.4921 1.0000
1.000 0.5930 0.01941 0.01010 -0.0706 0.4869 1.0000
1.250 0.6140 0.01978 0.01035 -0.0696 0.4820 1.0000
1.500 0.6325 0.02017 0.01077 -0.0682 0.4759 1.0000
1.750 0.6534 0.02052 0.01102 -0.0671 0.4708 1.0000
2.000 0.6750 0.02096 0.01134 -0.0661 0.4665 1.0000
2.250 0.6924 0.02148 0.01194 -0.0646 0.4614 1.0000
2.500 0.7123 0.02194 0.01239 -0.0633 0.4567 1.0000
2.750 0.7344 0.02237 0.01270 -0.0624 0.4527 1.0000
3.000 0.7524 0.02299 0.01336 -0.0609 0.4482 1.0000
3.250 0.7699 0.02359 0.01402 -0.0594 0.4433 1.0000
3.500 0.7904 0.02411 0.01451 -0.0582 0.4392 1.0000
3.750 0.8133 0.02465 0.01495 -0.0574 0.4359 1.0000
4.000 0.8284 0.02549 0.01590 -0.0556 0.4316 1.0000
4.250 0.8444 0.02624 0.01675 -0.0539 0.4269 1.0000
4.500 0.8651 0.02681 0.01730 -0.0528 0.4230 1.0000
4.750 0.8888 0.02737 0.01777 -0.0522 0.4197 1.0000
5.000 0.9012 0.02845 0.01900 -0.0501 0.4158 1.0000
5.250 0.9135 0.02949 0.02019 -0.0480 0.4112 1.0000
5.500 0.9337 0.03012 0.02082 -0.0469 0.4072 1.0000
5.750 0.9584 0.03065 0.02127 -0.0464 0.4039 1.0000
6.000 0.9693 0.03194 0.02272 -0.0443 0.4002 1.0000
6.250 0.9738 0.03345 0.02444 -0.0414 0.3954 1.0000
6.500 0.9916 0.03425 0.02527 -0.0401 0.3913 1.0000
6.750 1.0203 0.03456 0.02550 -0.0401 0.3881 1.0000
7.000 1.0265 0.03617 0.02728 -0.0376 0.3840 1.0000
7.250 1.0182 0.03848 0.02984 -0.0337 0.3788 1.0000
7.500 1.0370 0.03921 0.03060 -0.0326 0.3747 1.0000
7.750 1.0761 0.03891 0.03018 -0.0336 0.3716 1.0000
8.000 1.0487 0.04247 0.03405 -0.0281 0.3663 1.0000
8.250 1.0182 0.04616 0.03796 -0.0229 0.3607 1.0000
8.500 1.0706 0.04472 0.03645 -0.0246 0.3573 1.0000
8.750 1.1249 0.04360 0.03519 -0.0268 0.3542 1.0000
9.000 0.8185 0.07217 0.06417 -0.0155 0.3394 1.0000
9.250 0.8944 0.06533 0.05738 -0.0122 0.3392 1.0000
9.500 1.0950 0.05053 0.04254 -0.0165 0.3398 1.0000
9.750 0.6867 0.09868 0.09077 -0.0223 0.3188 1.0000
10.000 0.6738 0.10390 0.09602 -0.0237 0.3154 1.0000
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Polar data table (+)
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