NASA SC(2)-0414 AIRFOIL (sc20414-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0414 AIRFOIL (sc20414-il) Reynolds number: 200,000 Max Cl/Cd: 43.33 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20414-il-200000-n5.txt Download as CSV file: xf-sc20414-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0414 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9831 0.09737 0.09210 -0.0367 1.0000 0.0343
-16.500 -1.0212 0.08626 0.08067 -0.0436 1.0000 0.0344
-16.250 -1.0457 0.07838 0.07253 -0.0481 1.0000 0.0346
-16.000 -1.0639 0.07208 0.06597 -0.0513 1.0000 0.0348
-15.750 -1.0779 0.06678 0.06042 -0.0537 1.0000 0.0350
-15.500 -1.0841 0.06285 0.05633 -0.0550 1.0000 0.0353
-15.250 -1.0832 0.06003 0.05345 -0.0557 1.0000 0.0356
-15.000 -1.0820 0.05737 0.05071 -0.0563 1.0000 0.0359
-14.750 -1.0804 0.05484 0.04811 -0.0567 1.0000 0.0363
-14.500 -1.0783 0.05243 0.04560 -0.0571 1.0000 0.0367
-14.250 -1.0755 0.05012 0.04319 -0.0573 1.0000 0.0372
-14.000 -1.0722 0.04791 0.04086 -0.0573 1.0000 0.0378
-13.750 -1.0680 0.04579 0.03861 -0.0572 1.0000 0.0385
-13.500 -1.0629 0.04378 0.03644 -0.0569 1.0000 0.0391
-13.250 -1.0568 0.04187 0.03434 -0.0565 1.0000 0.0398
-13.000 -1.0482 0.04023 0.03259 -0.0560 1.0000 0.0404
-12.750 -1.0380 0.03883 0.03118 -0.0554 1.0000 0.0410
-12.500 -1.0274 0.03751 0.02983 -0.0549 1.0000 0.0416
-12.250 -1.0165 0.03624 0.02851 -0.0542 1.0000 0.0423
-12.000 -1.0052 0.03502 0.02721 -0.0534 1.0000 0.0431
-11.750 -0.9934 0.03385 0.02596 -0.0525 1.0000 0.0440
-11.500 -0.9815 0.03275 0.02474 -0.0515 1.0000 0.0451
-11.250 -0.9696 0.03170 0.02363 -0.0503 1.0000 0.0461
-11.000 -0.9590 0.03074 0.02269 -0.0490 1.0000 0.0469
-10.750 -0.9492 0.02988 0.02181 -0.0473 1.0000 0.0478
-10.500 -0.9409 0.02907 0.02098 -0.0453 1.0000 0.0489
-10.250 -0.9331 0.02829 0.02016 -0.0430 1.0000 0.0499
-10.000 -0.9219 0.02751 0.01931 -0.0412 1.0000 0.0511
-9.750 -0.9105 0.02672 0.01848 -0.0394 1.0000 0.0522
-9.500 -0.8991 0.02595 0.01774 -0.0379 1.0000 0.0534
-9.250 -0.8861 0.02526 0.01705 -0.0364 1.0000 0.0548
-9.000 -0.8720 0.02461 0.01636 -0.0351 1.0000 0.0565
-8.750 -0.8567 0.02398 0.01566 -0.0338 1.0000 0.0582
-8.500 -0.8415 0.02327 0.01497 -0.0327 1.0000 0.0598
-8.250 -0.8250 0.02264 0.01435 -0.0318 1.0000 0.0615
-8.000 -0.8058 0.02207 0.01377 -0.0312 0.9998 0.0636
-7.750 -0.7729 0.02146 0.01310 -0.0330 0.9970 0.0665
-7.500 -0.7398 0.02075 0.01244 -0.0352 0.9942 0.0696
-7.250 -0.7066 0.02019 0.01186 -0.0371 0.9914 0.0732
-7.000 -0.6744 0.01957 0.01125 -0.0389 0.9880 0.0770
-6.750 -0.6409 0.01902 0.01072 -0.0409 0.9849 0.0815
-6.500 -0.6065 0.01848 0.01019 -0.0430 0.9824 0.0865
-6.250 -0.5721 0.01796 0.00970 -0.0451 0.9798 0.0926
-6.000 -0.5400 0.01744 0.00921 -0.0467 0.9755 0.0990
-5.750 -0.5054 0.01697 0.00875 -0.0488 0.9722 0.1075
-5.500 -0.4692 0.01643 0.00830 -0.0512 0.9697 0.1183
-5.250 -0.4319 0.01593 0.00787 -0.0538 0.9678 0.1333
-5.000 -0.4002 0.01544 0.00747 -0.0553 0.9627 0.1506
-4.750 -0.3645 0.01486 0.00706 -0.0578 0.9595 0.1788
-4.500 -0.3267 0.01417 0.00662 -0.0608 0.9572 0.2235
-4.000 -0.2438 0.01218 0.00565 -0.0693 0.9539 0.4193
-3.750 -0.2120 0.01192 0.00593 -0.0702 0.9489 0.5233
-3.500 -0.1797 0.01201 0.00613 -0.0708 0.9445 0.5643
-3.250 -0.1450 0.01208 0.00620 -0.0720 0.9411 0.5870
-3.000 -0.1092 0.01215 0.00626 -0.0734 0.9384 0.6045
-2.750 -0.0805 0.01230 0.00642 -0.0733 0.9316 0.6172
-2.500 -0.0466 0.01237 0.00645 -0.0743 0.9273 0.6290
-2.250 -0.0146 0.01256 0.00666 -0.0747 0.9236 0.6378
-2.000 0.0156 0.01275 0.00685 -0.0748 0.9178 0.6485
-1.750 0.0439 0.01307 0.00720 -0.0742 0.9119 0.6583
-1.500 0.0751 0.01325 0.00738 -0.0745 0.9076 0.6660
-1.250 0.1027 0.01343 0.00761 -0.0738 0.9011 0.6701
-1.000 0.1321 0.01349 0.00766 -0.0737 0.8931 0.6747
-0.750 0.1668 0.01332 0.00744 -0.0751 0.8851 0.6799
-0.500 0.1972 0.01319 0.00728 -0.0752 0.8725 0.6826
-0.250 0.2249 0.01312 0.00720 -0.0746 0.8561 0.6842
0.000 0.2527 0.01304 0.00707 -0.0738 0.8351 0.6862
0.250 0.2803 0.01300 0.00696 -0.0731 0.8114 0.6884
0.500 0.3093 0.01295 0.00687 -0.0730 0.7908 0.6905
0.750 0.3390 0.01291 0.00678 -0.0731 0.7712 0.6927
1.000 0.3692 0.01287 0.00667 -0.0734 0.7485 0.6953
1.250 0.4003 0.01284 0.00653 -0.0740 0.7214 0.6985
1.500 0.4297 0.01287 0.00644 -0.0741 0.6828 0.7008
1.750 0.4551 0.01307 0.00641 -0.0732 0.6213 0.7021
2.000 0.4761 0.01368 0.00646 -0.0716 0.5053 0.7035
2.250 0.4965 0.01450 0.00672 -0.0702 0.3921 0.7050
2.500 0.5194 0.01519 0.00700 -0.0695 0.3108 0.7066
2.750 0.5440 0.01576 0.00727 -0.0692 0.2483 0.7084
3.000 0.5698 0.01625 0.00752 -0.0690 0.2042 0.7104
3.500 0.6243 0.01703 0.00801 -0.0692 0.1526 0.7155
3.750 0.6530 0.01736 0.00825 -0.0696 0.1361 0.7182
4.000 0.6799 0.01772 0.00853 -0.0695 0.1241 0.7201
4.250 0.7053 0.01807 0.00886 -0.0691 0.1146 0.7217
4.500 0.7310 0.01841 0.00921 -0.0686 0.1068 0.7233
4.750 0.7565 0.01881 0.00957 -0.0682 0.1000 0.7250
5.000 0.7828 0.01916 0.00994 -0.0680 0.0942 0.7268
5.250 0.8085 0.01958 0.01032 -0.0677 0.0891 0.7287
5.500 0.8348 0.01998 0.01073 -0.0675 0.0846 0.7307
5.750 0.8610 0.02040 0.01115 -0.0674 0.0804 0.7330
6.000 0.8870 0.02089 0.01161 -0.0672 0.0767 0.7354
6.250 0.9142 0.02132 0.01206 -0.0673 0.0731 0.7381
6.500 0.9377 0.02179 0.01255 -0.0666 0.0701 0.7396
6.750 0.9614 0.02230 0.01310 -0.0658 0.0674 0.7413
7.000 0.9854 0.02278 0.01364 -0.0652 0.0647 0.7430
7.250 1.0092 0.02329 0.01416 -0.0646 0.0624 0.7449
7.500 1.0326 0.02388 0.01478 -0.0640 0.0603 0.7469
7.750 1.0567 0.02443 0.01540 -0.0634 0.0580 0.7491
8.000 1.0805 0.02499 0.01599 -0.0629 0.0561 0.7515
8.250 1.1036 0.02564 0.01663 -0.0624 0.0545 0.7539
8.500 1.1267 0.02636 0.01741 -0.0618 0.0529 0.7562
8.750 1.1478 0.02703 0.01818 -0.0608 0.0513 0.7579
9.000 1.1684 0.02769 0.01891 -0.0597 0.0498 0.7599
9.250 1.1884 0.02838 0.01964 -0.0586 0.0485 0.7621
9.500 1.2078 0.02921 0.02051 -0.0575 0.0474 0.7644
9.750 1.2280 0.03004 0.02149 -0.0564 0.0461 0.7668
10.000 1.2475 0.03092 0.02247 -0.0554 0.0449 0.7693
10.250 1.2663 0.03181 0.02342 -0.0543 0.0439 0.7718
10.500 1.2834 0.03267 0.02434 -0.0530 0.0431 0.7739
10.750 1.2980 0.03360 0.02531 -0.0513 0.0423 0.7758
11.000 1.3104 0.03465 0.02650 -0.0492 0.0415 0.7778
11.250 1.3216 0.03574 0.02779 -0.0470 0.0406 0.7801
11.500 1.3335 0.03691 0.02910 -0.0451 0.0398 0.7826
11.750 1.3449 0.03811 0.03043 -0.0433 0.0390 0.7853
12.000 1.3559 0.03937 0.03179 -0.0417 0.0384 0.7883
12.250 1.3656 0.04069 0.03320 -0.0400 0.0379 0.7910
12.500 1.3737 0.04207 0.03467 -0.0381 0.0374 0.7932
12.750 1.3811 0.04363 0.03629 -0.0365 0.0370 0.7957
13.000 1.3854 0.04558 0.03844 -0.0347 0.0366 0.7983
13.250 1.3873 0.04781 0.04093 -0.0331 0.0361 0.8012
13.500 1.3876 0.05026 0.04361 -0.0316 0.0356 0.8041
13.750 1.3864 0.05294 0.04650 -0.0306 0.0351 0.8070
14.000 1.3829 0.05578 0.04956 -0.0295 0.0347 0.8090
14.250 1.3781 0.05888 0.05286 -0.0289 0.0343 0.8111
14.500 1.3720 0.06229 0.05647 -0.0288 0.0340 0.8133
14.750 1.3649 0.06600 0.06035 -0.0291 0.0337 0.8157
15.000 1.3565 0.07010 0.06462 -0.0299 0.0334 0.8181
15.250 1.3459 0.07475 0.06944 -0.0314 0.0332 0.8205
15.500 1.3327 0.08014 0.07500 -0.0336 0.0330 0.8227
15.750 1.3179 0.08613 0.08117 -0.0366 0.0328 0.8246
16.000 1.2954 0.09398 0.08925 -0.0410 0.0327 0.8260
16.250 1.2580 0.10573 0.10132 -0.0488 0.0327 0.8268
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Polar data table (+)
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