NASA SC(2)-0414 AIRFOIL (sc20414-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0414 AIRFOIL (sc20414-il) Reynolds number: 200,000 Max Cl/Cd: 35.25 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20414-il-200000.txt Download as CSV file: xf-sc20414-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7666 0.10341 0.09887 -0.0374 1.0000 0.0585
-14.000 -0.8024 0.09182 0.08720 -0.0440 1.0000 0.0577
-13.750 -0.8590 0.07899 0.07414 -0.0519 1.0000 0.0568
-13.500 -0.9071 0.06969 0.06457 -0.0566 1.0000 0.0562
-13.250 -0.9445 0.06281 0.05742 -0.0588 1.0000 0.0558
-13.000 -0.9727 0.05754 0.05188 -0.0594 1.0000 0.0558
-12.750 -0.9940 0.05333 0.04741 -0.0591 1.0000 0.0559
-12.500 -1.0104 0.04989 0.04372 -0.0580 1.0000 0.0562
-12.250 -1.0243 0.04710 0.04070 -0.0560 1.0000 0.0566
-12.000 -1.0331 0.04449 0.03782 -0.0544 1.0000 0.0572
-11.750 -1.0364 0.04206 0.03506 -0.0529 1.0000 0.0579
-11.500 -1.0370 0.04009 0.03271 -0.0512 1.0000 0.0587
-11.250 -1.0218 0.03775 0.03036 -0.0503 1.0000 0.0597
-11.000 -1.0063 0.03644 0.02904 -0.0493 1.0000 0.0608
-10.750 -0.9909 0.03518 0.02771 -0.0482 1.0000 0.0618
-10.500 -0.9761 0.03384 0.02626 -0.0470 1.0000 0.0631
-10.250 -0.9615 0.03249 0.02473 -0.0457 1.0000 0.0645
-10.000 -0.9473 0.03133 0.02330 -0.0445 1.0000 0.0660
-9.750 -0.9293 0.02982 0.02180 -0.0433 1.0000 0.0677
-9.500 -0.9110 0.02897 0.02099 -0.0422 1.0000 0.0694
-9.250 -0.8932 0.02810 0.02007 -0.0410 1.0000 0.0712
-9.000 -0.8752 0.02721 0.01907 -0.0397 1.0000 0.0732
-8.750 -0.8571 0.02643 0.01811 -0.0386 1.0000 0.0751
-8.500 -0.8388 0.02533 0.01715 -0.0371 1.0000 0.0774
-8.250 -0.8202 0.02470 0.01655 -0.0360 1.0000 0.0800
-8.000 -0.8012 0.02408 0.01585 -0.0349 1.0000 0.0828
-7.750 -0.7820 0.02335 0.01504 -0.0337 1.0000 0.0853
-7.500 -0.7635 0.02257 0.01439 -0.0325 1.0000 0.0883
-7.250 -0.7436 0.02205 0.01388 -0.0317 1.0000 0.0918
-7.000 -0.7226 0.02162 0.01335 -0.0309 1.0000 0.0954
-6.750 -0.7032 0.02079 0.01267 -0.0300 1.0000 0.0994
-6.500 -0.6813 0.02032 0.01223 -0.0296 1.0000 0.1042
-6.250 -0.6588 0.01977 0.01167 -0.0292 1.0000 0.1094
-6.000 -0.6354 0.01922 0.01122 -0.0293 1.0000 0.1156
-5.750 -0.6108 0.01874 0.01076 -0.0294 1.0000 0.1228
-5.500 -0.5852 0.01824 0.01035 -0.0300 1.0000 0.1321
-5.250 -0.5577 0.01764 0.00986 -0.0310 1.0000 0.1440
-5.000 -0.5285 0.01705 0.00941 -0.0324 1.0000 0.1616
-4.750 -0.4914 0.01625 0.00887 -0.0356 0.9991 0.1963
-4.500 -0.4421 0.01457 0.00802 -0.0426 0.9989 0.3284
-4.250 -0.3985 0.01378 0.00847 -0.0467 0.9979 0.5487
-4.000 -0.3607 0.01428 0.00903 -0.0483 0.9941 0.5969
-3.750 -0.3258 0.01485 0.00957 -0.0493 0.9899 0.6211
-3.500 -0.2929 0.01548 0.01018 -0.0497 0.9851 0.6366
-3.250 -0.2568 0.01610 0.01078 -0.0508 0.9816 0.6495
-3.000 -0.2263 0.01662 0.01127 -0.0508 0.9759 0.6600
-2.750 -0.1961 0.01723 0.01189 -0.0505 0.9711 0.6674
-2.500 -0.1632 0.01794 0.01262 -0.0504 0.9679 0.6752
-2.250 -0.1370 0.01833 0.01300 -0.0497 0.9610 0.6840
-2.000 -0.1095 0.01902 0.01373 -0.0483 0.9564 0.6889
-1.750 -0.0671 0.01926 0.01392 -0.0513 0.9540 0.7005
-1.500 -0.0529 0.01994 0.01468 -0.0469 0.9453 0.7044
-1.250 -0.0254 0.02065 0.01543 -0.0450 0.9410 0.7120
-1.000 0.0156 0.02087 0.01565 -0.0468 0.9384 0.7219
-0.750 0.0337 0.02112 0.01594 -0.0438 0.9286 0.7260
-0.500 0.0782 0.02095 0.01578 -0.0463 0.9249 0.7308
-0.250 0.1413 0.02024 0.01502 -0.0541 0.9224 0.7382
0.000 0.1638 0.02004 0.01486 -0.0517 0.9108 0.7404
0.250 0.2005 0.01952 0.01436 -0.0516 0.9006 0.7431
0.500 0.2354 0.01896 0.01380 -0.0517 0.8892 0.7462
0.750 0.2659 0.01854 0.01339 -0.0520 0.8765 0.7492
1.000 0.3036 0.01806 0.01289 -0.0540 0.8662 0.7532
1.250 0.3390 0.01759 0.01242 -0.0557 0.8534 0.7567
1.500 0.3631 0.01733 0.01218 -0.0542 0.8387 0.7584
1.750 0.3885 0.01709 0.01195 -0.0529 0.8227 0.7606
2.000 0.4147 0.01685 0.01173 -0.0519 0.8035 0.7634
2.250 0.4438 0.01660 0.01144 -0.0517 0.7799 0.7663
2.500 0.4746 0.01634 0.01112 -0.0522 0.7483 0.7688
2.750 0.5075 0.01616 0.01079 -0.0533 0.7012 0.7716
3.000 0.5351 0.01619 0.01047 -0.0531 0.6116 0.7738
3.250 0.5468 0.01701 0.01046 -0.0495 0.4523 0.7755
3.500 0.5599 0.01807 0.01081 -0.0470 0.3192 0.7776
3.750 0.5791 0.01894 0.01117 -0.0459 0.2327 0.7798
4.000 0.6025 0.01961 0.01152 -0.0456 0.1907 0.7819
4.250 0.6291 0.02010 0.01187 -0.0458 0.1669 0.7841
4.500 0.6575 0.02060 0.01225 -0.0465 0.1508 0.7865
4.750 0.6878 0.02116 0.01269 -0.0477 0.1384 0.7889
5.000 0.7157 0.02156 0.01303 -0.0481 0.1286 0.7909
5.250 0.7377 0.02202 0.01350 -0.0469 0.1212 0.7927
5.500 0.7609 0.02248 0.01391 -0.0461 0.1146 0.7948
5.750 0.7856 0.02309 0.01451 -0.0456 0.1087 0.7971
6.000 0.8125 0.02354 0.01495 -0.0457 0.1031 0.7993
6.250 0.8399 0.02438 0.01572 -0.0460 0.0984 0.8020
6.500 0.8700 0.02489 0.01628 -0.0468 0.0937 0.8050
6.750 0.9002 0.02560 0.01690 -0.0479 0.0897 0.8073
7.000 0.9247 0.02644 0.01779 -0.0473 0.0864 0.8089
7.250 0.9489 0.02698 0.01844 -0.0467 0.0830 0.8107
7.500 0.9740 0.02763 0.01904 -0.0464 0.0800 0.8128
7.750 1.0008 0.02887 0.02029 -0.0465 0.0773 0.8149
8.000 1.0270 0.02966 0.02126 -0.0464 0.0748 0.8174
8.250 1.0539 0.03049 0.02216 -0.0466 0.0722 0.8203
8.500 1.0835 0.03151 0.02309 -0.0476 0.0700 0.8233
8.750 1.1067 0.03280 0.02455 -0.0471 0.0680 0.8253
9.000 1.1278 0.03389 0.02588 -0.0460 0.0661 0.8274
9.250 1.1497 0.03503 0.02716 -0.0453 0.0645 0.8296
9.500 1.1723 0.03608 0.02830 -0.0448 0.0630 0.8320
9.750 1.1970 0.03746 0.02963 -0.0449 0.0616 0.8346
10.000 1.2150 0.03946 0.03195 -0.0440 0.0603 0.8373
10.250 1.2307 0.04144 0.03431 -0.0429 0.0589 0.8399
10.500 1.2429 0.04334 0.03651 -0.0411 0.0578 0.8423
10.750 1.2539 0.04522 0.03862 -0.0391 0.0569 0.8449
11.000 1.2665 0.04694 0.04049 -0.0376 0.0560 0.8478
11.250 1.2820 0.04855 0.04218 -0.0366 0.0553 0.8508
11.500 1.2966 0.05063 0.04433 -0.0358 0.0546 0.8535
11.750 1.2995 0.05415 0.04807 -0.0342 0.0540 0.8561
12.000 1.2828 0.05728 0.05164 -0.0299 0.0537 0.8583
12.250 1.2585 0.06037 0.05509 -0.0250 0.0535 0.8607
12.500 1.2323 0.06441 0.05947 -0.0216 0.0534 0.8632
12.750 1.2037 0.06919 0.06457 -0.0197 0.0534 0.8655
13.000 1.1720 0.07495 0.07062 -0.0196 0.0535 0.8676
13.250 1.1398 0.08167 0.07758 -0.0212 0.0536 0.8694
13.500 1.1072 0.08952 0.08564 -0.0247 0.0538 0.8710
13.750 1.0774 0.09825 0.09453 -0.0295 0.0541 0.8724
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