NASA SC(2)-0612 AIRFOIL (sc20612-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0612 AIRFOIL (sc20612-il) Reynolds number: 500,000 Max Cl/Cd: 63.65 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20612-il-500000.txt Download as CSV file: xf-sc20612-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0612 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
------ -------- --------- --------- -------- -------- --------
-16.250 -1.0056 0.07247 0.06883 -0.0563 1.0000 0.0249
-16.000 -1.0305 0.06485 0.06099 -0.0610 1.0000 0.0249
-15.750 -1.0470 0.05925 0.05520 -0.0639 1.0000 0.0250
-15.500 -1.0591 0.05474 0.05053 -0.0658 1.0000 0.0251
-15.250 -1.0677 0.05089 0.04652 -0.0671 1.0000 0.0253
-15.000 -1.0738 0.04754 0.04302 -0.0679 1.0000 0.0254
-14.750 -1.0773 0.04461 0.03994 -0.0683 1.0000 0.0256
-14.500 -1.0786 0.04203 0.03723 -0.0684 1.0000 0.0259
-14.250 -1.0785 0.03970 0.03476 -0.0681 1.0000 0.0261
-14.000 -1.0773 0.03760 0.03252 -0.0675 1.0000 0.0264
-13.750 -1.0755 0.03571 0.03051 -0.0666 1.0000 0.0267
-13.500 -1.0737 0.03406 0.02872 -0.0651 1.0000 0.0270
-13.250 -1.0731 0.03263 0.02717 -0.0631 1.0000 0.0272
-13.000 -1.0752 0.03145 0.02589 -0.0602 1.0000 0.0274
-12.750 -1.0748 0.03040 0.02472 -0.0575 1.0000 0.0277
-12.500 -1.0709 0.02862 0.02286 -0.0555 1.0000 0.0282
-12.250 -1.0623 0.02747 0.02168 -0.0539 1.0000 0.0287
-12.000 -1.0506 0.02654 0.02073 -0.0528 1.0000 0.0291
-11.750 -1.0368 0.02565 0.01979 -0.0518 1.0000 0.0296
-11.500 -1.0215 0.02476 0.01884 -0.0510 1.0000 0.0302
-11.250 -1.0047 0.02391 0.01791 -0.0503 1.0000 0.0308
-11.000 -0.9868 0.02309 0.01700 -0.0497 1.0000 0.0315
-10.750 -0.9677 0.02237 0.01618 -0.0491 1.0000 0.0321
-10.500 -0.9492 0.02134 0.01509 -0.0485 1.0000 0.0329
-10.250 -0.9288 0.02054 0.01430 -0.0482 1.0000 0.0338
-10.000 -0.9068 0.01997 0.01373 -0.0480 1.0000 0.0347
-9.750 -0.8841 0.01945 0.01317 -0.0479 1.0000 0.0358
-9.500 -0.8607 0.01898 0.01263 -0.0477 1.0000 0.0370
-9.250 -0.8371 0.01830 0.01192 -0.0479 1.0000 0.0384
-9.000 -0.8113 0.01778 0.01142 -0.0483 0.9998 0.0399
-8.750 -0.7775 0.01735 0.01097 -0.0502 0.9987 0.0418
-8.500 -0.7436 0.01699 0.01054 -0.0519 0.9975 0.0436
-8.250 -0.7096 0.01624 0.00982 -0.0541 0.9964 0.0463
-8.000 -0.6743 0.01591 0.00949 -0.0562 0.9951 0.0492
-7.750 -0.6383 0.01536 0.00893 -0.0586 0.9941 0.0526
-7.500 -0.6024 0.01500 0.00859 -0.0608 0.9931 0.0562
-7.250 -0.5689 0.01465 0.00821 -0.0624 0.9912 0.0595
-7.000 -0.5342 0.01416 0.00778 -0.0645 0.9896 0.0639
-6.750 -0.4997 0.01394 0.00753 -0.0662 0.9880 0.0676
-6.500 -0.4634 0.01345 0.00707 -0.0686 0.9867 0.0723
-6.250 -0.4275 0.01318 0.00681 -0.0707 0.9855 0.0766
-6.000 -0.3908 0.01284 0.00648 -0.0730 0.9845 0.0817
-5.750 -0.3539 0.01254 0.00622 -0.0753 0.9836 0.0879
-5.500 -0.3164 0.01222 0.00593 -0.0778 0.9829 0.0959
-5.250 -0.2785 0.01189 0.00568 -0.0803 0.9823 0.1090
-5.000 -0.2456 0.01149 0.00542 -0.0819 0.9796 0.1323
-4.750 -0.2071 0.01087 0.00511 -0.0850 0.9783 0.1936
-4.500 -0.1633 0.00995 0.00475 -0.0897 0.9783 0.3207
-4.250 -0.1152 0.00893 0.00445 -0.0955 0.9797 0.4934
-4.000 -0.0795 0.00877 0.00454 -0.0973 0.9776 0.5689
-3.750 -0.0449 0.00877 0.00458 -0.0986 0.9753 0.5968
-3.500 -0.0090 0.00878 0.00460 -0.1002 0.9734 0.6131
-3.250 0.0281 0.00878 0.00459 -0.1020 0.9719 0.6255
-3.000 0.0655 0.00879 0.00460 -0.1040 0.9708 0.6359
-2.750 0.1033 0.00880 0.00464 -0.1059 0.9698 0.6444
-2.500 0.1338 0.00884 0.00466 -0.1062 0.9644 0.6535
-2.250 0.1705 0.00882 0.00470 -0.1076 0.9616 0.6609
-2.000 0.2095 0.00879 0.00467 -0.1096 0.9589 0.6701
-1.750 0.2455 0.00866 0.00461 -0.1104 0.9533 0.6771
-1.500 0.2763 0.00859 0.00456 -0.1102 0.9441 0.6838
-1.250 0.3068 0.00851 0.00444 -0.1102 0.9336 0.6892
-1.000 0.3341 0.00836 0.00432 -0.1094 0.9204 0.6922
-0.750 0.3614 0.00831 0.00428 -0.1087 0.9075 0.6948
-0.500 0.3893 0.00828 0.00423 -0.1082 0.8935 0.6974
-0.250 0.4178 0.00828 0.00422 -0.1080 0.8802 0.7004
0.000 0.4467 0.00828 0.00419 -0.1078 0.8644 0.7036
0.250 0.4758 0.00830 0.00415 -0.1078 0.8429 0.7064
0.500 0.5041 0.00832 0.00408 -0.1075 0.8149 0.7087
0.750 0.5306 0.00841 0.00407 -0.1068 0.7745 0.7105
1.000 0.5550 0.00872 0.00409 -0.1057 0.7003 0.7122
1.250 0.5729 0.00973 0.00431 -0.1035 0.5307 0.7139
1.500 0.5930 0.01081 0.00467 -0.1022 0.3747 0.7158
1.750 0.6159 0.01165 0.00498 -0.1015 0.2593 0.7179
2.000 0.6407 0.01231 0.00527 -0.1011 0.1806 0.7204
2.250 0.6668 0.01286 0.00553 -0.1009 0.1312 0.7229
2.500 0.6941 0.01326 0.00579 -0.1009 0.1085 0.7250
2.750 0.7218 0.01359 0.00602 -0.1009 0.0956 0.7268
3.000 0.7489 0.01382 0.00623 -0.1006 0.0884 0.7285
3.250 0.7753 0.01415 0.00654 -0.1003 0.0824 0.7301
3.500 0.8022 0.01439 0.00681 -0.1000 0.0782 0.7317
3.750 0.8282 0.01480 0.00718 -0.0996 0.0733 0.7335
4.000 0.8552 0.01507 0.00748 -0.0993 0.0699 0.7354
4.250 0.8822 0.01534 0.00775 -0.0991 0.0663 0.7375
4.500 0.9075 0.01589 0.00825 -0.0986 0.0623 0.7397
4.750 0.9351 0.01612 0.00852 -0.0985 0.0593 0.7424
5.000 0.9619 0.01648 0.00884 -0.0984 0.0558 0.7448
5.250 0.9867 0.01696 0.00934 -0.0978 0.0526 0.7467
5.500 1.0125 0.01726 0.00969 -0.0973 0.0497 0.7484
5.750 1.0367 0.01779 0.01019 -0.0966 0.0471 0.7502
6.000 1.0615 0.01827 0.01073 -0.0959 0.0449 0.7521
6.250 1.0872 0.01861 0.01110 -0.0955 0.0427 0.7542
6.500 1.1121 0.01905 0.01152 -0.0949 0.0408 0.7566
6.750 1.1356 0.01973 0.01224 -0.0942 0.0392 0.7591
7.000 1.1609 0.02019 0.01274 -0.0937 0.0378 0.7617
7.250 1.1856 0.02065 0.01323 -0.0931 0.0364 0.7637
7.500 1.2089 0.02114 0.01375 -0.0923 0.0353 0.7656
7.750 1.2292 0.02216 0.01479 -0.0910 0.0342 0.7675
8.000 1.2525 0.02270 0.01544 -0.0901 0.0334 0.7696
8.250 1.2753 0.02329 0.01612 -0.0892 0.0324 0.7719
8.500 1.2980 0.02386 0.01674 -0.0883 0.0314 0.7744
8.750 1.3202 0.02446 0.01736 -0.0874 0.0306 0.7769
9.000 1.3410 0.02532 0.01824 -0.0863 0.0299 0.7794
9.250 1.3592 0.02669 0.01968 -0.0849 0.0292 0.7816
9.500 1.3789 0.02747 0.02061 -0.0835 0.0287 0.7838
9.750 1.3978 0.02837 0.02165 -0.0820 0.0282 0.7861
10.000 1.4158 0.02934 0.02275 -0.0804 0.0277 0.7886
10.250 1.4331 0.03034 0.02387 -0.0788 0.0272 0.7912
10.500 1.4495 0.03135 0.02498 -0.0771 0.0267 0.7939
10.750 1.4651 0.03239 0.02609 -0.0754 0.0263 0.7967
11.000 1.4785 0.03343 0.02722 -0.0733 0.0259 0.7991
11.250 1.4893 0.03467 0.02855 -0.0709 0.0256 0.8014
11.500 1.4956 0.03632 0.03031 -0.0679 0.0253 0.8038
11.750 1.4951 0.03900 0.03320 -0.0643 0.0249 0.8063
12.000 1.4979 0.04041 0.03481 -0.0610 0.0248 0.8092
12.250 1.4993 0.04209 0.03668 -0.0579 0.0246 0.8120
12.500 1.4987 0.04399 0.03879 -0.0548 0.0243 0.8144
12.750 1.4957 0.04616 0.04118 -0.0519 0.0241 0.8167
13.000 1.4899 0.04874 0.04397 -0.0491 0.0239 0.8191
13.250 1.4815 0.05169 0.04715 -0.0467 0.0238 0.8215
13.500 1.4701 0.05515 0.05083 -0.0448 0.0236 0.8241
13.750 1.4556 0.05921 0.05511 -0.0436 0.0235 0.8266
14.000 1.4373 0.06408 0.06021 -0.0432 0.0234 0.8288
14.250 1.4148 0.06995 0.06633 -0.0441 0.0234 0.8307
14.500 1.3862 0.07746 0.07412 -0.0469 0.0234 0.8323
14.750 1.3465 0.08819 0.08515 -0.0530 0.0235 0.8334
15.000 1.2750 0.10883 0.10621 -0.0680 0.0238 0.8330
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