NASA SC(2)-0606 AIRFOIL (sc20606-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0606 AIRFOIL (sc20606-il) Reynolds number: 50,000 Max Cl/Cd: 25.35 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20606-il-50000-n5.txt Download as CSV file: xf-sc20606-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0606 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6150 0.10777 0.10043 -0.0073 1.0000 0.0620
-9.750 -0.6104 0.10355 0.09624 -0.0079 1.0000 0.0603
-9.250 -0.6243 0.09048 0.08332 -0.0217 1.0000 0.0500
-9.000 -0.6210 0.08575 0.07861 -0.0239 1.0000 0.0496
-8.750 -0.6180 0.08096 0.07383 -0.0265 1.0000 0.0491
-8.500 -0.6147 0.07614 0.06898 -0.0290 1.0000 0.0484
-8.250 -0.6106 0.07117 0.06394 -0.0319 1.0000 0.0476
-8.000 -0.6048 0.06602 0.05866 -0.0350 1.0000 0.0467
-7.750 -0.5960 0.06078 0.05321 -0.0381 1.0000 0.0458
-7.500 -0.5834 0.05555 0.04765 -0.0411 1.0000 0.0451
-7.250 -0.5664 0.05044 0.04212 -0.0439 1.0000 0.0445
-7.000 -0.5454 0.04566 0.03683 -0.0462 1.0000 0.0443
-6.750 -0.5210 0.04133 0.03194 -0.0481 1.0000 0.0444
-6.500 -0.4945 0.03750 0.02744 -0.0495 1.0000 0.0449
-6.250 -0.4668 0.03432 0.02365 -0.0504 1.0000 0.0471
-6.000 -0.4387 0.03166 0.02040 -0.0509 1.0000 0.0510
-5.750 -0.4133 0.02940 0.01796 -0.0509 1.0000 0.0547
-5.500 -0.3875 0.02737 0.01566 -0.0502 1.0000 0.0577
-5.250 -0.3626 0.02567 0.01365 -0.0490 1.0000 0.0620
-5.000 -0.3385 0.02425 0.01221 -0.0483 1.0000 0.0727
-4.750 -0.3138 0.02283 0.01064 -0.0475 1.0000 0.0838
-4.500 -0.2882 0.02155 0.00928 -0.0472 1.0000 0.1047
-4.250 -0.2588 0.01994 0.00788 -0.0483 1.0000 0.1449
-4.000 -0.2299 0.01708 0.00715 -0.0502 1.0000 0.4861
-3.750 -0.2172 0.01702 0.00751 -0.0451 1.0000 0.6595
-3.500 -0.2052 0.01721 0.00765 -0.0400 1.0000 0.7388
-3.250 -0.1999 0.01734 0.00782 -0.0330 1.0000 0.7993
-3.000 -0.1941 0.01721 0.00764 -0.0266 1.0000 0.8461
-2.750 -0.1826 0.01683 0.00716 -0.0222 1.0000 0.8819
-2.500 -0.1657 0.01634 0.00653 -0.0193 1.0000 0.9125
-2.250 -0.1415 0.01586 0.00590 -0.0185 1.0000 0.9389
-2.000 -0.1098 0.01547 0.00531 -0.0196 1.0000 0.9623
-1.750 -0.0765 0.01516 0.00488 -0.0213 1.0000 0.9887
-1.500 -0.0506 0.01498 0.00462 -0.0218 1.0000 1.0000
-1.250 -0.0212 0.01495 0.00448 -0.0231 1.0000 1.0000
-1.000 0.0089 0.01496 0.00440 -0.0245 1.0000 1.0000
-0.750 0.0395 0.01500 0.00439 -0.0258 1.0000 1.0000
-0.500 0.0700 0.01507 0.00443 -0.0272 1.0000 1.0000
-0.250 0.1006 0.01516 0.00453 -0.0284 1.0000 1.0000
0.000 0.1309 0.01528 0.00470 -0.0296 1.0000 1.0000
0.250 0.1610 0.01542 0.00491 -0.0307 1.0000 1.0000
0.500 0.1909 0.01559 0.00517 -0.0317 1.0000 1.0000
0.750 0.2204 0.01577 0.00549 -0.0327 1.0000 1.0000
1.000 0.2496 0.01598 0.00591 -0.0335 1.0000 1.0000
1.250 0.2785 0.01622 0.00635 -0.0343 1.0000 1.0000
1.500 0.3071 0.01649 0.00686 -0.0350 1.0000 1.0000
1.750 0.3353 0.01679 0.00745 -0.0357 1.0000 1.0000
2.000 0.3632 0.01713 0.00814 -0.0363 1.0000 1.0000
2.250 0.4758 0.01877 0.00751 -0.0471 0.2288 1.0000
2.500 0.5000 0.02097 0.00892 -0.0470 0.1215 1.0000
2.750 0.5285 0.02251 0.01030 -0.0474 0.0894 1.0000
3.000 0.5587 0.02415 0.01202 -0.0476 0.0759 1.0000
3.250 0.5885 0.02574 0.01378 -0.0478 0.0628 1.0000
3.500 0.6200 0.02760 0.01597 -0.0477 0.0572 1.0000
3.750 0.6504 0.02981 0.01845 -0.0476 0.0537 1.0000
4.000 0.6781 0.03227 0.02107 -0.0477 0.0500 1.0000
4.250 0.7061 0.03476 0.02415 -0.0472 0.0461 1.0000
4.500 0.7324 0.03770 0.02767 -0.0467 0.0439 1.0000
4.750 0.7566 0.04113 0.03175 -0.0460 0.0433 1.0000
5.000 0.7784 0.04490 0.03609 -0.0453 0.0431 1.0000
5.250 0.7978 0.04901 0.04075 -0.0446 0.0432 1.0000
5.500 0.8145 0.05347 0.04572 -0.0440 0.0436 1.0000
5.750 0.8286 0.05819 0.05090 -0.0436 0.0443 1.0000
6.000 0.8402 0.06309 0.05619 -0.0435 0.0451 1.0000
6.250 0.8493 0.06811 0.06152 -0.0437 0.0459 1.0000
6.500 0.8558 0.07319 0.06686 -0.0442 0.0463 1.0000
6.750 0.8597 0.07836 0.07225 -0.0451 0.0465 1.0000
7.000 0.8611 0.08359 0.07764 -0.0465 0.0467 1.0000
7.250 0.8605 0.08886 0.08303 -0.0482 0.0470 1.0000
7.500 0.8586 0.09411 0.08835 -0.0503 0.0473 1.0000
7.750 0.8551 0.09915 0.09342 -0.0523 0.0478 1.0000
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Polar data table (+)
Polar graphs
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