NASA SC(2)-0412 AIRFOIL (sc20412-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0412 AIRFOIL (sc20412-il) Reynolds number: 500,000 Max Cl/Cd: 56.73 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20412-il-500000.txt Download as CSV file: xf-sc20412-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0412 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0060 0.09794 0.09468 -0.0259 1.0000 0.0244
-16.250 -1.0501 0.08477 0.08125 -0.0346 1.0000 0.0243
-16.000 -1.0801 0.07537 0.07162 -0.0406 1.0000 0.0243
-15.750 -1.1026 0.06814 0.06419 -0.0449 1.0000 0.0243
-15.500 -1.1202 0.06233 0.05817 -0.0478 1.0000 0.0244
-15.250 -1.1341 0.05756 0.05319 -0.0498 1.0000 0.0245
-15.000 -1.1443 0.05353 0.04897 -0.0512 1.0000 0.0246
-14.750 -1.1545 0.04965 0.04489 -0.0520 1.0000 0.0248
-14.500 -1.1626 0.04594 0.04101 -0.0521 1.0000 0.0250
-14.250 -1.1620 0.04333 0.03832 -0.0521 1.0000 0.0253
-14.000 -1.1583 0.04118 0.03609 -0.0519 1.0000 0.0255
-13.750 -1.1527 0.03928 0.03411 -0.0516 1.0000 0.0258
-13.500 -1.1463 0.03750 0.03226 -0.0513 1.0000 0.0261
-13.250 -1.1391 0.03583 0.03049 -0.0508 1.0000 0.0264
-13.000 -1.1312 0.03423 0.02879 -0.0503 1.0000 0.0268
-12.750 -1.1227 0.03271 0.02716 -0.0495 1.0000 0.0272
-12.500 -1.1136 0.03130 0.02563 -0.0486 1.0000 0.0276
-12.250 -1.1043 0.02999 0.02421 -0.0475 1.0000 0.0281
-12.000 -1.0950 0.02882 0.02291 -0.0462 1.0000 0.0285
-11.750 -1.0818 0.02776 0.02171 -0.0455 1.0000 0.0289
-11.500 -1.0688 0.02615 0.02004 -0.0444 1.0000 0.0296
-11.250 -1.0528 0.02514 0.01903 -0.0438 1.0000 0.0302
-11.000 -1.0353 0.02432 0.01818 -0.0433 1.0000 0.0309
-10.750 -1.0170 0.02355 0.01736 -0.0428 1.0000 0.0317
-10.500 -0.9980 0.02283 0.01657 -0.0422 1.0000 0.0326
-10.250 -0.9781 0.02220 0.01585 -0.0416 1.0000 0.0335
-10.000 -0.9603 0.02116 0.01476 -0.0407 1.0000 0.0345
-9.750 -0.9406 0.02043 0.01405 -0.0401 1.0000 0.0356
-9.500 -0.9196 0.01987 0.01348 -0.0395 1.0000 0.0366
-9.250 -0.8983 0.01932 0.01289 -0.0389 1.0000 0.0379
-9.000 -0.8763 0.01884 0.01234 -0.0384 1.0000 0.0390
-8.750 -0.8561 0.01795 0.01144 -0.0378 1.0000 0.0405
-8.500 -0.8339 0.01743 0.01094 -0.0374 1.0000 0.0419
-8.250 -0.8110 0.01703 0.01053 -0.0369 1.0000 0.0435
-8.000 -0.7878 0.01670 0.01014 -0.0365 1.0000 0.0452
-7.750 -0.7650 0.01599 0.00944 -0.0363 1.0000 0.0471
-7.500 -0.7413 0.01557 0.00905 -0.0360 1.0000 0.0490
-7.250 -0.7173 0.01523 0.00870 -0.0358 1.0000 0.0510
-7.000 -0.6931 0.01501 0.00842 -0.0354 1.0000 0.0528
-6.750 -0.6676 0.01432 0.00779 -0.0358 1.0000 0.0558
-6.500 -0.6425 0.01402 0.00749 -0.0358 1.0000 0.0585
-6.250 -0.6120 0.01378 0.00721 -0.0368 0.9993 0.0611
-6.000 -0.5755 0.01315 0.00665 -0.0392 0.9980 0.0659
-5.750 -0.5390 0.01285 0.00635 -0.0414 0.9963 0.0700
-5.500 -0.5016 0.01239 0.00594 -0.0439 0.9949 0.0762
-5.250 -0.4639 0.01212 0.00567 -0.0463 0.9936 0.0825
-5.000 -0.4274 0.01170 0.00532 -0.0485 0.9916 0.0924
-4.750 -0.3904 0.01129 0.00500 -0.0508 0.9893 0.1064
-4.500 -0.3523 0.01081 0.00468 -0.0535 0.9874 0.1320
-4.250 -0.3132 0.01022 0.00436 -0.0566 0.9859 0.1875
-4.000 -0.2726 0.00941 0.00399 -0.0603 0.9850 0.2822
-3.750 -0.2289 0.00824 0.00353 -0.0652 0.9849 0.4473
-3.500 -0.1884 0.00774 0.00354 -0.0683 0.9841 0.5746
-3.250 -0.1499 0.00773 0.00357 -0.0705 0.9827 0.6084
-3.000 -0.1153 0.00774 0.00359 -0.0718 0.9790 0.6263
-2.750 -0.0790 0.00777 0.00364 -0.0734 0.9758 0.6394
-2.500 -0.0410 0.00779 0.00368 -0.0753 0.9735 0.6499
-2.250 -0.0011 0.00778 0.00362 -0.0777 0.9711 0.6593
-2.000 0.0329 0.00776 0.00364 -0.0786 0.9654 0.6650
-1.750 0.0670 0.00780 0.00370 -0.0795 0.9595 0.6732
-1.500 0.0987 0.00789 0.00381 -0.0798 0.9533 0.6813
-1.250 0.1276 0.00796 0.00391 -0.0794 0.9431 0.6878
-1.000 0.1562 0.00801 0.00389 -0.0789 0.9282 0.6941
-0.750 0.1816 0.00803 0.00394 -0.0777 0.9124 0.6986
-0.500 0.2084 0.00810 0.00402 -0.0770 0.8992 0.7023
-0.250 0.2357 0.00816 0.00404 -0.0764 0.8829 0.7063
0.000 0.2641 0.00824 0.00407 -0.0761 0.8662 0.7111
0.250 0.2919 0.00826 0.00405 -0.0757 0.8475 0.7145
0.500 0.3191 0.00830 0.00404 -0.0751 0.8263 0.7167
0.750 0.3470 0.00835 0.00403 -0.0748 0.8043 0.7184
1.000 0.3751 0.00841 0.00403 -0.0746 0.7784 0.7203
1.250 0.4031 0.00852 0.00403 -0.0743 0.7446 0.7223
1.500 0.4305 0.00869 0.00401 -0.0740 0.6949 0.7242
1.750 0.4560 0.00913 0.00403 -0.0734 0.5944 0.7262
2.000 0.4788 0.01009 0.00424 -0.0727 0.4319 0.7282
2.250 0.5043 0.01084 0.00447 -0.0726 0.3173 0.7300
2.500 0.5303 0.01148 0.00468 -0.0725 0.2248 0.7317
2.750 0.5566 0.01193 0.00488 -0.0724 0.1687 0.7332
3.000 0.5836 0.01229 0.00510 -0.0723 0.1386 0.7347
3.250 0.6108 0.01263 0.00532 -0.0721 0.1171 0.7363
3.500 0.6382 0.01295 0.00557 -0.0720 0.1026 0.7381
3.750 0.6658 0.01323 0.00582 -0.0719 0.0928 0.7403
4.000 0.6933 0.01356 0.00610 -0.0719 0.0851 0.7427
4.250 0.7213 0.01383 0.00635 -0.0719 0.0796 0.7449
4.500 0.7488 0.01423 0.00670 -0.0719 0.0745 0.7469
4.750 0.7772 0.01447 0.00695 -0.0720 0.0706 0.7486
5.000 0.8038 0.01482 0.00727 -0.0718 0.0666 0.7503
5.250 0.8302 0.01517 0.00766 -0.0714 0.0635 0.7519
5.500 0.8572 0.01543 0.00794 -0.0712 0.0603 0.7536
5.750 0.8826 0.01594 0.00843 -0.0708 0.0569 0.7554
6.000 0.9094 0.01626 0.00880 -0.0706 0.0544 0.7573
6.250 0.9364 0.01655 0.00910 -0.0704 0.0517 0.7595
6.500 0.9609 0.01724 0.00974 -0.0700 0.0487 0.7616
6.750 0.9883 0.01751 0.01008 -0.0698 0.0468 0.7639
7.000 1.0149 0.01789 0.01046 -0.0697 0.0447 0.7660
7.250 1.0390 0.01845 0.01102 -0.0691 0.0427 0.7680
7.500 1.0633 0.01902 0.01167 -0.0684 0.0411 0.7700
7.750 1.0887 0.01942 0.01213 -0.0679 0.0394 0.7720
8.000 1.1137 0.01983 0.01256 -0.0675 0.0379 0.7743
8.250 1.1356 0.02079 0.01350 -0.0666 0.0363 0.7769
8.500 1.1610 0.02122 0.01403 -0.0662 0.0352 0.7795
8.750 1.1855 0.02178 0.01465 -0.0657 0.0341 0.7818
9.000 1.2092 0.02231 0.01524 -0.0650 0.0330 0.7839
9.250 1.2318 0.02290 0.01586 -0.0642 0.0321 0.7860
9.500 1.2510 0.02420 0.01718 -0.0630 0.0311 0.7881
9.750 1.2734 0.02484 0.01796 -0.0621 0.0306 0.7906
10.000 1.2948 0.02563 0.01888 -0.0612 0.0298 0.7934
10.250 1.3158 0.02646 0.01982 -0.0602 0.0292 0.7962
10.500 1.3365 0.02728 0.02070 -0.0592 0.0285 0.7988
10.750 1.3561 0.02800 0.02149 -0.0581 0.0279 0.8012
11.000 1.3743 0.02887 0.02241 -0.0568 0.0274 0.8036
11.250 1.3878 0.03070 0.02433 -0.0550 0.0267 0.8061
11.500 1.4035 0.03179 0.02560 -0.0534 0.0264 0.8090
11.750 1.4178 0.03300 0.02698 -0.0516 0.0260 0.8121
12.000 1.4301 0.03434 0.02849 -0.0497 0.0256 0.8150
12.250 1.4392 0.03574 0.03006 -0.0473 0.0253 0.8177
12.500 1.4430 0.03712 0.03162 -0.0441 0.0250 0.8206
12.750 1.4452 0.03865 0.03331 -0.0410 0.0248 0.8239
13.000 1.4470 0.04038 0.03521 -0.0382 0.0245 0.8273
13.250 1.4479 0.04226 0.03723 -0.0358 0.0243 0.8308
13.500 1.4469 0.04430 0.03943 -0.0334 0.0241 0.8340
13.750 1.4442 0.04661 0.04191 -0.0314 0.0239 0.8374
14.000 1.4405 0.04914 0.04460 -0.0298 0.0237 0.8411
14.250 1.4352 0.05206 0.04767 -0.0287 0.0236 0.8449
14.500 1.4270 0.05547 0.05124 -0.0280 0.0234 0.8483
14.750 1.4159 0.05945 0.05541 -0.0280 0.0233 0.8514
15.000 1.4016 0.06419 0.06033 -0.0288 0.0233 0.8547
15.250 1.3820 0.07017 0.06653 -0.0309 0.0232 0.8580
15.500 1.3557 0.07797 0.07457 -0.0349 0.0232 0.8609
15.750 1.3088 0.09105 0.08803 -0.0436 0.0234 0.8624
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