NASA SC(2)-0610 AIRFOIL (sc20610-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0610 AIRFOIL (sc20610-il) Reynolds number: 200,000 Max Cl/Cd: 41.91 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20610-il-200000.txt Download as CSV file: xf-sc20610-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0610 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4752 0.09058 0.08682 -0.0339 1.0000 0.0773
-10.500 -0.4782 0.08642 0.08268 -0.0346 1.0000 0.0787
-10.250 -0.4864 0.08139 0.07769 -0.0359 1.0000 0.0803
-10.000 -0.5028 0.07493 0.07126 -0.0385 1.0000 0.0819
-9.750 -0.5389 0.06533 0.06169 -0.0441 1.0000 0.0826
-9.500 -0.7726 0.05017 0.04511 -0.0516 1.0000 0.0519
-9.250 -0.7558 0.04890 0.04401 -0.0506 1.0000 0.0533
-9.000 -0.7592 0.03921 0.03347 -0.0514 1.0000 0.0451
-8.750 -0.7457 0.03288 0.02624 -0.0524 1.0000 0.0436
-8.500 -0.7250 0.03052 0.02364 -0.0524 1.0000 0.0442
-8.250 -0.7031 0.02883 0.02178 -0.0523 1.0000 0.0453
-8.000 -0.6800 0.02735 0.02012 -0.0522 1.0000 0.0471
-7.750 -0.6557 0.02572 0.01820 -0.0521 1.0000 0.0489
-7.500 -0.6306 0.02431 0.01649 -0.0520 1.0000 0.0503
-7.250 -0.6066 0.02222 0.01427 -0.0518 1.0000 0.0524
-7.000 -0.5822 0.02121 0.01327 -0.0516 1.0000 0.0550
-6.750 -0.5568 0.02046 0.01244 -0.0514 1.0000 0.0588
-6.500 -0.5311 0.01936 0.01126 -0.0513 1.0000 0.0632
-6.250 -0.5052 0.01860 0.01055 -0.0514 1.0000 0.0680
-6.000 -0.4785 0.01818 0.01001 -0.0514 1.0000 0.0732
-5.750 -0.4508 0.01715 0.00912 -0.0520 1.0000 0.0805
-5.500 -0.4221 0.01656 0.00851 -0.0525 1.0000 0.0881
-5.250 -0.3923 0.01595 0.00796 -0.0535 1.0000 0.0976
-5.000 -0.3605 0.01527 0.00736 -0.0549 1.0000 0.1098
-4.750 -0.3273 0.01464 0.00683 -0.0567 1.0000 0.1280
-4.500 -0.2876 0.01366 0.00621 -0.0602 1.0000 0.1815
-4.250 -0.2290 0.01160 0.00613 -0.0686 1.0000 0.5755
-4.000 -0.2057 0.01196 0.00655 -0.0673 1.0000 0.6324
-3.750 -0.1834 0.01239 0.00696 -0.0657 1.0000 0.6604
-3.500 -0.1631 0.01287 0.00743 -0.0637 1.0000 0.6783
-3.250 -0.1430 0.01334 0.00790 -0.0616 1.0000 0.6928
-3.000 -0.1207 0.01376 0.00827 -0.0602 1.0000 0.7062
-2.750 -0.1050 0.01426 0.00882 -0.0571 1.0000 0.7141
-2.500 -0.0842 0.01466 0.00921 -0.0554 1.0000 0.7250
-2.250 -0.0674 0.01521 0.00978 -0.0526 1.0000 0.7373
-2.000 -0.0559 0.01575 0.01038 -0.0484 1.0000 0.7462
-1.750 -0.0365 0.01616 0.01079 -0.0465 1.0000 0.7578
-1.500 -0.0221 0.01656 0.01123 -0.0433 1.0000 0.7667
-1.250 -0.0036 0.01686 0.01155 -0.0412 1.0000 0.7757
-1.000 0.0178 0.01712 0.01183 -0.0400 1.0000 0.7844
-0.750 0.0400 0.01728 0.01201 -0.0391 1.0000 0.7902
-0.500 0.0632 0.01744 0.01220 -0.0384 0.9995 0.7951
-0.250 0.1141 0.01758 0.01233 -0.0435 0.9941 0.8003
0.000 0.1618 0.01752 0.01230 -0.0476 0.9857 0.8041
0.250 0.2127 0.01729 0.01213 -0.0518 0.9743 0.8071
0.500 0.2661 0.01684 0.01173 -0.0565 0.9614 0.8095
0.750 0.3260 0.01604 0.01101 -0.0620 0.9460 0.8116
1.000 0.3779 0.01537 0.01041 -0.0661 0.9330 0.8143
1.250 0.4299 0.01465 0.00979 -0.0703 0.9194 0.8168
1.500 0.4739 0.01385 0.00907 -0.0723 0.8993 0.8187
1.750 0.5044 0.01332 0.00860 -0.0716 0.8644 0.8209
2.000 0.5398 0.01288 0.00800 -0.0716 0.7723 0.8231
2.250 0.5532 0.01432 0.00787 -0.0677 0.4591 0.8257
2.500 0.5667 0.01619 0.00844 -0.0658 0.2113 0.8288
2.750 0.5924 0.01726 0.00900 -0.0661 0.1377 0.8317
3.000 0.6179 0.01789 0.00949 -0.0658 0.1158 0.8341
3.250 0.6411 0.01839 0.00997 -0.0649 0.1031 0.8364
3.500 0.6657 0.01901 0.01055 -0.0643 0.0931 0.8389
3.750 0.6917 0.01971 0.01118 -0.0642 0.0845 0.8413
4.000 0.7199 0.02030 0.01182 -0.0643 0.0772 0.8440
4.250 0.7479 0.02148 0.01287 -0.0648 0.0701 0.8470
4.500 0.7757 0.02195 0.01347 -0.0648 0.0650 0.8494
4.750 0.8005 0.02269 0.01420 -0.0642 0.0607 0.8518
5.000 0.8262 0.02399 0.01557 -0.0638 0.0567 0.8546
5.250 0.8536 0.02474 0.01644 -0.0637 0.0529 0.8575
5.500 0.8819 0.02582 0.01755 -0.0640 0.0503 0.8601
5.750 0.9110 0.02835 0.02018 -0.0646 0.0482 0.8626
6.000 0.9359 0.02969 0.02185 -0.0638 0.0470 0.8649
6.250 0.9591 0.03150 0.02401 -0.0627 0.0459 0.8674
6.500 0.9814 0.03338 0.02625 -0.0617 0.0444 0.8703
6.750 1.0037 0.03525 0.02837 -0.0609 0.0431 0.8736
7.000 1.0232 0.03848 0.03205 -0.0598 0.0429 0.8767
7.250 1.0325 0.04366 0.03792 -0.0571 0.0441 0.8792
7.500 1.0374 0.04889 0.04366 -0.0543 0.0460 0.8817
7.750 1.0437 0.05395 0.04894 -0.0526 0.0476 0.8845
8.000 1.0043 0.07098 0.06732 -0.0465 0.0724 0.8864
8.250 1.0203 0.07494 0.07119 -0.0466 0.0713 0.8893
8.500 1.0101 0.08415 0.08049 -0.0466 0.0701 0.8916
8.750 0.9878 0.08723 0.08393 -0.0443 0.0697 0.8944
9.000 0.9489 0.09128 0.08826 -0.0424 0.0693 0.8977
9.250 0.9125 0.09813 0.09529 -0.0458 0.0690 0.9008
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Polar data table (+)
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