USA-35B AIRFOIL (usa35b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA-35B AIRFOIL (usa35b-il) Reynolds number: 200,000 Max Cl/Cd: 76.76 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa35b-il-200000.txt Download as CSV file: xf-usa35b-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: USA-35B 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3212 0.08954 0.08599 -0.0362 1.0000 0.0669
-9.500 -0.3347 0.08762 0.08416 -0.0349 1.0000 0.0683
-9.250 -0.3622 0.08669 0.08334 -0.0315 1.0000 0.0690
-9.000 -0.3990 0.08479 0.08155 -0.0329 0.9993 0.0701
-8.750 -0.3767 0.07574 0.07242 -0.0472 0.9927 0.0715
-8.500 -0.3529 0.07358 0.07028 -0.0462 0.9890 0.0726
-8.250 -0.3245 0.07063 0.06731 -0.0492 0.9848 0.0746
-8.000 -0.2905 0.05931 0.05548 -0.0722 0.9730 0.0826
-7.750 -0.2598 0.05604 0.05232 -0.0740 0.9703 0.0837
-7.500 -0.2326 0.05357 0.04987 -0.0757 0.9633 0.0853
-7.250 -0.1914 0.04770 0.04325 -0.0872 0.9568 0.0954
-7.000 -0.1639 0.04395 0.03968 -0.0888 0.9506 0.0969
-6.750 -0.1320 0.04167 0.03743 -0.0909 0.9443 0.0993
-6.500 -0.0990 0.03825 0.03353 -0.0951 0.9360 0.1108
-6.250 -0.0703 0.03590 0.03125 -0.0961 0.9274 0.1132
-6.000 -0.0399 0.02532 0.01909 -0.0975 0.9172 0.0684
-5.750 -0.0092 0.02270 0.01609 -0.0980 0.9086 0.0659
-5.500 0.0175 0.02101 0.01409 -0.0974 0.8958 0.0656
-5.250 0.0452 0.01978 0.01264 -0.0970 0.8833 0.0665
-5.000 0.0730 0.01858 0.01118 -0.0964 0.8708 0.0668
-4.750 0.1005 0.01755 0.00993 -0.0956 0.8574 0.0673
-4.500 0.1271 0.01673 0.00894 -0.0949 0.8420 0.0682
-4.250 0.1539 0.01606 0.00812 -0.0941 0.8266 0.0695
-4.000 0.1806 0.01540 0.00734 -0.0934 0.8113 0.0713
-3.750 0.2070 0.01477 0.00673 -0.0929 0.7965 0.0748
-3.500 0.2339 0.01438 0.00628 -0.0924 0.7823 0.0788
-3.250 0.2608 0.01393 0.00574 -0.0918 0.7684 0.0829
-3.000 0.2873 0.01346 0.00527 -0.0912 0.7545 0.0902
-2.750 0.3139 0.01303 0.00483 -0.0907 0.7406 0.1046
-2.500 0.3404 0.01244 0.00446 -0.0904 0.7273 0.1540
-2.250 0.3655 0.01161 0.00433 -0.0902 0.7162 0.3448
-2.000 0.3848 0.01057 0.00439 -0.0883 0.7067 0.6733
-1.750 0.4305 0.00999 0.00434 -0.0906 0.6955 1.0000
-1.500 0.4572 0.01014 0.00428 -0.0902 0.6862 1.0000
-1.250 0.4839 0.01027 0.00426 -0.0898 0.6766 1.0000
-1.000 0.5108 0.01043 0.00428 -0.0895 0.6677 1.0000
-0.750 0.5378 0.01059 0.00430 -0.0891 0.6589 1.0000
-0.500 0.5648 0.01076 0.00436 -0.0888 0.6502 1.0000
-0.250 0.5920 0.01094 0.00442 -0.0885 0.6420 1.0000
0.000 0.6190 0.01113 0.00453 -0.0882 0.6335 1.0000
0.250 0.6461 0.01131 0.00460 -0.0879 0.6251 1.0000
0.500 0.6731 0.01150 0.00474 -0.0877 0.6168 1.0000
0.750 0.7003 0.01169 0.00485 -0.0874 0.6086 1.0000
1.000 0.7273 0.01190 0.00500 -0.0871 0.6002 1.0000
1.250 0.7543 0.01208 0.00512 -0.0868 0.5915 1.0000
1.500 0.7811 0.01229 0.00530 -0.0865 0.5829 1.0000
1.750 0.8080 0.01247 0.00541 -0.0861 0.5737 1.0000
2.000 0.8340 0.01262 0.00555 -0.0856 0.5622 1.0000
2.250 0.8600 0.01275 0.00561 -0.0851 0.5500 1.0000
2.500 0.8861 0.01288 0.00565 -0.0845 0.5379 1.0000
2.750 0.9118 0.01301 0.00582 -0.0840 0.5259 1.0000
3.000 0.9379 0.01319 0.00597 -0.0836 0.5152 1.0000
3.250 0.9640 0.01337 0.00609 -0.0831 0.5049 1.0000
3.500 0.9895 0.01353 0.00631 -0.0826 0.4928 1.0000
3.750 1.0151 0.01372 0.00649 -0.0820 0.4810 1.0000
4.000 1.0404 0.01392 0.00664 -0.0815 0.4692 1.0000
4.250 1.0654 0.01412 0.00684 -0.0809 0.4562 1.0000
4.500 1.0902 0.01433 0.00707 -0.0802 0.4428 1.0000
4.750 1.1148 0.01458 0.00732 -0.0796 0.4296 1.0000
5.000 1.1391 0.01485 0.00758 -0.0789 0.4166 1.0000
5.250 1.1629 0.01515 0.00786 -0.0781 0.4029 1.0000
5.500 1.1858 0.01546 0.00814 -0.0773 0.3873 1.0000
5.750 1.2080 0.01582 0.00846 -0.0763 0.3704 1.0000
6.000 1.2297 0.01622 0.00884 -0.0752 0.3536 1.0000
6.250 1.2510 0.01667 0.00925 -0.0742 0.3376 1.0000
6.500 1.2717 0.01716 0.00971 -0.0731 0.3215 1.0000
6.750 1.2919 0.01768 0.01021 -0.0719 0.3056 1.0000
7.000 1.3114 0.01822 0.01073 -0.0706 0.2898 1.0000
7.250 1.3302 0.01878 0.01128 -0.0693 0.2742 1.0000
7.500 1.3483 0.01936 0.01185 -0.0678 0.2587 1.0000
7.750 1.3656 0.01996 0.01246 -0.0663 0.2440 1.0000
8.000 1.3819 0.02062 0.01310 -0.0647 0.2310 1.0000
8.250 1.3970 0.02132 0.01378 -0.0629 0.2188 1.0000
8.500 1.4112 0.02198 0.01447 -0.0609 0.2064 1.0000
8.750 1.4232 0.02271 0.01523 -0.0587 0.1945 1.0000
9.000 1.4342 0.02355 0.01609 -0.0565 0.1832 1.0000
9.250 1.4434 0.02452 0.01706 -0.0543 0.1715 1.0000
9.500 1.4511 0.02564 0.01818 -0.0520 0.1583 1.0000
9.750 1.4576 0.02692 0.01947 -0.0498 0.1418 1.0000
10.000 1.4596 0.02860 0.02110 -0.0475 0.1216 1.0000
10.250 1.4594 0.03060 0.02302 -0.0453 0.0998 1.0000
10.500 1.4572 0.03291 0.02524 -0.0433 0.0846 1.0000
10.750 1.4559 0.03528 0.02758 -0.0417 0.0760 1.0000
11.000 1.4540 0.03783 0.03016 -0.0403 0.0710 1.0000
11.250 1.4509 0.04062 0.03299 -0.0392 0.0674 1.0000
11.500 1.4444 0.04388 0.03626 -0.0382 0.0647 1.0000
11.750 1.4435 0.04669 0.03920 -0.0376 0.0623 1.0000
12.000 1.4405 0.04978 0.04238 -0.0371 0.0602 1.0000
12.250 1.4352 0.05315 0.04579 -0.0367 0.0584 1.0000
12.500 1.4282 0.05666 0.04930 -0.0361 0.0568 1.0000
12.750 1.4280 0.05954 0.05228 -0.0356 0.0553 1.0000
13.000 1.4280 0.06244 0.05530 -0.0353 0.0538 1.0000
13.250 1.4278 0.06536 0.05829 -0.0350 0.0522 1.0000
13.500 1.4281 0.06819 0.06115 -0.0346 0.0508 1.0000
13.750 1.4322 0.07016 0.06302 -0.0332 0.0491 1.0000
14.000 1.4355 0.07268 0.06566 -0.0326 0.0479 1.0000
14.250 1.4378 0.07546 0.06858 -0.0325 0.0468 1.0000
14.500 1.4401 0.07824 0.07147 -0.0323 0.0456 1.0000
14.750 1.4433 0.08083 0.07413 -0.0321 0.0444 1.0000
15.000 1.4495 0.08291 0.07621 -0.0315 0.0432 1.0000
15.250 1.4643 0.08369 0.07692 -0.0291 0.0416 1.0000
15.500 1.4593 0.08766 0.08111 -0.0301 0.0410 1.0000
15.750 1.4553 0.09155 0.08520 -0.0310 0.0404 1.0000
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