USA 45 M AIRFOIL (usa45m-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 45 M AIRFOIL (usa45m-il) Reynolds number: 200,000 Max Cl/Cd: 65.88 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa45m-il-200000.txt Download as CSV file: xf-usa45m-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: USA 45 M AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3717 0.08801 0.08456 -0.0306 1.0000 0.0554
-8.500 -0.3920 0.08352 0.08017 -0.0373 1.0000 0.0562
-8.250 -0.4138 0.07967 0.07631 -0.0400 1.0000 0.0565
-8.000 -0.4327 0.07635 0.07286 -0.0408 1.0000 0.0567
-7.750 -0.4441 0.07376 0.07013 -0.0396 1.0000 0.0569
-7.500 -0.4282 0.06766 0.06434 -0.0381 1.0000 0.0582
-7.250 -0.4230 0.06570 0.06243 -0.0358 1.0000 0.0592
-7.000 -0.4227 0.06366 0.06042 -0.0337 1.0000 0.0603
-6.750 -0.4267 0.06138 0.05815 -0.0315 1.0000 0.0614
-6.500 -0.4324 0.05909 0.05583 -0.0292 1.0000 0.0626
-6.250 -0.4236 0.05565 0.05226 -0.0304 0.9972 0.0653
-6.000 -0.3952 0.04885 0.04479 -0.0375 0.9869 0.0707
-5.750 -0.3616 0.04546 0.04148 -0.0408 0.9810 0.0727
-5.500 -0.3276 0.04269 0.03859 -0.0440 0.9727 0.0773
-5.250 -0.2974 0.03880 0.03421 -0.0471 0.9622 0.0856
-5.000 -0.2593 0.03612 0.03154 -0.0504 0.9561 0.0899
-4.750 -0.2288 0.03345 0.02847 -0.0522 0.9442 0.1006
-4.500 -0.1955 0.03144 0.02644 -0.0540 0.9323 0.1072
-4.250 -0.1653 0.02931 0.02414 -0.0552 0.9175 0.1192
-4.000 -0.1366 0.02773 0.02246 -0.0559 0.8998 0.1357
-3.750 -0.1107 0.02655 0.02107 -0.0561 0.8791 0.1619
-3.250 -0.0424 0.02125 0.01420 -0.0527 0.8320 0.0812
-3.000 -0.0152 0.01930 0.01173 -0.0512 0.8035 0.0711
-2.750 0.0107 0.01846 0.01062 -0.0501 0.7714 0.0708
-2.500 0.0363 0.01805 0.00992 -0.0489 0.7369 0.0699
-2.250 0.0613 0.01768 0.00929 -0.0477 0.7010 0.0691
-2.000 0.0861 0.01678 0.00816 -0.0467 0.6669 0.0688
-1.750 0.1109 0.01623 0.00740 -0.0456 0.6361 0.0689
-1.500 0.1357 0.01581 0.00679 -0.0447 0.6095 0.0693
-1.250 0.1596 0.01501 0.00592 -0.0437 0.5864 0.0708
-1.000 0.1831 0.01457 0.00542 -0.0428 0.5671 0.0740
-0.750 0.2073 0.01431 0.00508 -0.0419 0.5506 0.0766
-0.500 0.2316 0.01410 0.00478 -0.0411 0.5366 0.0791
-0.250 0.2564 0.01397 0.00453 -0.0403 0.5240 0.0824
0.000 0.2808 0.01378 0.00423 -0.0395 0.5130 0.0891
0.250 0.3058 0.01361 0.00405 -0.0388 0.5022 0.1063
0.500 0.4403 0.01154 0.00438 -0.0593 0.4840 1.0000
0.750 0.4625 0.01164 0.00438 -0.0583 0.4754 1.0000
1.000 0.4848 0.01182 0.00438 -0.0572 0.4680 1.0000
1.250 0.5073 0.01195 0.00445 -0.0563 0.4606 1.0000
1.500 0.5300 0.01213 0.00451 -0.0553 0.4540 1.0000
1.750 0.5528 0.01232 0.00462 -0.0544 0.4474 1.0000
2.000 0.5756 0.01249 0.00473 -0.0534 0.4407 1.0000
2.250 0.5989 0.01276 0.00486 -0.0526 0.4351 1.0000
2.500 0.6217 0.01292 0.00503 -0.0516 0.4288 1.0000
2.750 0.6450 0.01313 0.00516 -0.0507 0.4230 1.0000
3.000 0.6684 0.01340 0.00537 -0.0499 0.4176 1.0000
3.250 0.6914 0.01359 0.00558 -0.0489 0.4117 1.0000
3.500 0.7150 0.01384 0.00574 -0.0481 0.4065 1.0000
3.750 0.7384 0.01411 0.00600 -0.0473 0.4011 1.0000
4.000 0.7615 0.01432 0.00623 -0.0464 0.3953 1.0000
4.250 0.7854 0.01458 0.00642 -0.0456 0.3903 1.0000
4.500 0.8085 0.01485 0.00671 -0.0448 0.3849 1.0000
4.750 0.8316 0.01506 0.00696 -0.0439 0.3790 1.0000
5.000 0.8558 0.01534 0.00715 -0.0432 0.3740 1.0000
5.250 0.8784 0.01558 0.00748 -0.0422 0.3682 1.0000
5.500 0.9016 0.01578 0.00770 -0.0413 0.3623 1.0000
5.750 0.9261 0.01612 0.00794 -0.0407 0.3574 1.0000
6.000 0.9478 0.01631 0.00828 -0.0396 0.3513 1.0000
6.250 0.9712 0.01654 0.00851 -0.0388 0.3459 1.0000
6.500 0.9951 0.01687 0.00883 -0.0381 0.3410 1.0000
6.750 1.0169 0.01710 0.00920 -0.0371 0.3349 1.0000
7.000 1.0403 0.01728 0.00934 -0.0363 0.3288 1.0000
7.250 1.0611 0.01741 0.00958 -0.0350 0.3205 1.0000
7.500 1.0833 0.01749 0.00960 -0.0340 0.3126 1.0000
7.750 1.1034 0.01758 0.00983 -0.0327 0.3034 1.0000
8.000 1.1246 0.01772 0.00995 -0.0315 0.2953 1.0000
8.250 1.1449 0.01783 0.01018 -0.0303 0.2861 1.0000
8.500 1.1647 0.01794 0.01037 -0.0289 0.2755 1.0000
8.750 1.1845 0.01814 0.01058 -0.0276 0.2663 1.0000
9.000 1.2037 0.01832 0.01084 -0.0263 0.2548 1.0000
9.250 1.2214 0.01854 0.01111 -0.0247 0.2394 1.0000
9.500 1.2388 0.01884 0.01146 -0.0231 0.2192 1.0000
9.750 1.2520 0.01944 0.01194 -0.0211 0.1896 1.0000
10.000 1.2590 0.02051 0.01277 -0.0183 0.1522 1.0000
10.250 1.2572 0.02214 0.01407 -0.0145 0.1063 1.0000
10.500 1.2375 0.02448 0.01598 -0.0086 0.0506 1.0000
10.750 1.2314 0.02621 0.01771 -0.0047 0.0419 1.0000
11.000 1.2285 0.02791 0.01951 -0.0018 0.0383 1.0000
11.250 1.2271 0.02968 0.02140 0.0005 0.0363 1.0000
11.500 1.2266 0.03156 0.02345 0.0022 0.0350 1.0000
11.750 1.2241 0.03381 0.02585 0.0035 0.0340 1.0000
12.000 1.2197 0.03648 0.02868 0.0042 0.0334 1.0000
12.250 1.2120 0.03980 0.03216 0.0043 0.0326 1.0000
12.500 1.2026 0.04364 0.03616 0.0037 0.0321 1.0000
12.750 1.1904 0.04813 0.04079 0.0026 0.0316 1.0000
13.000 1.1805 0.05254 0.04535 0.0014 0.0315 1.0000
13.250 1.1668 0.05754 0.05047 -0.0002 0.0312 1.0000
13.500 1.1532 0.06256 0.05560 -0.0018 0.0308 1.0000
13.750 1.1413 0.06733 0.06047 -0.0032 0.0306 1.0000
14.000 1.1305 0.07193 0.06513 -0.0044 0.0304 1.0000
14.250 1.1220 0.07602 0.06925 -0.0053 0.0298 1.0000
14.500 1.1212 0.07936 0.07267 -0.0061 0.0294 1.0000
14.750 1.1220 0.08242 0.07578 -0.0067 0.0288 1.0000
15.000 1.1248 0.08510 0.07851 -0.0070 0.0281 1.0000
15.250 1.1303 0.08731 0.08074 -0.0070 0.0276 1.0000
15.500 1.1391 0.08894 0.08240 -0.0065 0.0273 1.0000
15.750 1.1488 0.09042 0.08389 -0.0059 0.0267 1.0000
16.000 1.1609 0.09154 0.08505 -0.0050 0.0263 1.0000
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