NASA SC(2)-0606 AIRFOIL (sc20606-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0606 AIRFOIL (sc20606-il) Reynolds number: 200,000 Max Cl/Cd: 51.78 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20606-il-200000.txt Download as CSV file: xf-sc20606-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6052 0.09409 0.09045 -0.0125 1.0000 0.0426
-9.250 -0.6095 0.08900 0.08542 -0.0185 1.0000 0.0432
-9.000 -0.6134 0.08265 0.07908 -0.0272 1.0000 0.0434
-8.750 -0.6140 0.07742 0.07373 -0.0334 1.0000 0.0436
-8.500 -0.6126 0.07283 0.06895 -0.0372 1.0000 0.0438
-8.250 -0.6149 0.06452 0.06070 -0.0392 1.0000 0.0449
-8.000 -0.6051 0.06150 0.05776 -0.0381 1.0000 0.0464
-7.750 -0.5941 0.05888 0.05513 -0.0382 1.0000 0.0496
-7.500 -0.5739 0.05544 0.05094 -0.0445 1.0000 0.0565
-7.250 -0.5637 0.04763 0.04311 -0.0468 1.0000 0.0585
-7.000 -0.5461 0.04437 0.03987 -0.0472 1.0000 0.0608
-6.750 -0.5186 0.04214 0.03709 -0.0493 1.0000 0.0691
-6.500 -0.4972 0.03668 0.03149 -0.0516 1.0000 0.0732
-6.250 -0.4568 0.02837 0.02209 -0.0541 1.0000 0.0465
-6.000 -0.4228 0.02315 0.01616 -0.0550 1.0000 0.0357
-5.750 -0.3936 0.02100 0.01368 -0.0554 1.0000 0.0370
-5.500 -0.3650 0.01928 0.01169 -0.0556 1.0000 0.0389
-5.250 -0.3362 0.01743 0.00958 -0.0555 1.0000 0.0395
-5.000 -0.3078 0.01602 0.00803 -0.0554 1.0000 0.0415
-4.750 -0.2786 0.01465 0.00657 -0.0556 1.0000 0.0449
-4.500 -0.2491 0.01372 0.00564 -0.0563 1.0000 0.0554
-4.250 -0.2157 0.01244 0.00443 -0.0579 1.0000 0.0736
-4.000 -0.1793 0.01110 0.00354 -0.0606 1.0000 0.1598
-3.750 -0.1388 0.00917 0.00349 -0.0647 1.0000 0.6206
-3.500 -0.1136 0.00920 0.00357 -0.0637 1.0000 0.6823
-3.250 -0.0887 0.00925 0.00364 -0.0627 1.0000 0.7143
-3.000 -0.0653 0.00937 0.00377 -0.0613 1.0000 0.7435
-2.750 -0.0422 0.00951 0.00391 -0.0598 1.0000 0.7693
-2.500 -0.0218 0.00965 0.00408 -0.0575 1.0000 0.7917
-2.250 -0.0005 0.00976 0.00421 -0.0556 1.0000 0.8116
-2.000 0.0203 0.00983 0.00430 -0.0537 1.0000 0.8273
-1.750 0.0417 0.00986 0.00435 -0.0520 1.0000 0.8419
-1.500 0.0648 0.00986 0.00437 -0.0508 1.0000 0.8547
-1.250 0.0892 0.00984 0.00437 -0.0500 1.0000 0.8666
-1.000 0.1132 0.00981 0.00436 -0.0492 1.0000 0.8773
-0.750 0.1364 0.00975 0.00436 -0.0481 1.0000 0.8876
-0.500 0.1603 0.00970 0.00436 -0.0473 1.0000 0.8981
-0.250 0.1846 0.00966 0.00438 -0.0467 1.0000 0.9091
0.000 0.2083 0.00961 0.00440 -0.0460 1.0000 0.9209
0.250 0.2308 0.00953 0.00441 -0.0449 1.0000 0.9340
0.500 0.2516 0.00941 0.00440 -0.0436 1.0000 0.9499
0.750 0.2712 0.00929 0.00440 -0.0421 1.0000 0.9749
1.000 0.2969 0.00941 0.00466 -0.0424 1.0000 1.0000
1.250 0.3643 0.00902 0.00448 -0.0504 0.9739 1.0000
1.500 0.4246 0.00820 0.00387 -0.0556 0.9152 1.0000
2.000 0.4852 0.01275 0.00468 -0.0561 0.0734 1.0000
2.250 0.5148 0.01388 0.00572 -0.0567 0.0540 1.0000
2.500 0.5446 0.01517 0.00704 -0.0571 0.0467 1.0000
2.750 0.5735 0.01702 0.00881 -0.0576 0.0395 1.0000
3.000 0.6049 0.01824 0.01023 -0.0581 0.0377 1.0000
3.250 0.6361 0.02010 0.01231 -0.0583 0.0366 1.0000
3.500 0.6668 0.02256 0.01509 -0.0583 0.0370 1.0000
3.750 0.6953 0.02617 0.01909 -0.0581 0.0386 1.0000
4.000 0.7210 0.03087 0.02415 -0.0578 0.0396 1.0000
4.500 0.7790 0.03957 0.03432 -0.0540 0.0677 1.0000
4.750 0.7986 0.04337 0.03868 -0.0532 0.0599 1.0000
5.000 0.8188 0.04655 0.04209 -0.0528 0.0560 1.0000
5.250 0.8370 0.05013 0.04568 -0.0527 0.0539 1.0000
5.500 0.8444 0.05904 0.05459 -0.0532 0.0520 1.0000
5.750 0.8633 0.06028 0.05671 -0.0521 0.0472 1.0000
6.000 0.8753 0.06477 0.06141 -0.0524 0.0447 1.0000
6.250 0.8856 0.06867 0.06542 -0.0525 0.0426 1.0000
6.500 0.8962 0.07184 0.06845 -0.0516 0.0405 1.0000
6.750 0.8022 0.07013 0.06746 -0.0435 0.0433 1.0000
7.000 0.7965 0.07506 0.07244 -0.0439 0.0425 1.0000
7.250 0.7790 0.08040 0.07784 -0.0450 0.0425 1.0000
7.500 0.7562 0.08744 0.08489 -0.0505 0.0431 1.0000
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Polar data table (+)
Polar graphs
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