I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 962 (isa962-il) Reynolds number: 200,000 Max Cl/Cd: 77.06 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa962-il-200000.txt Download as CSV file: xf-isa962-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 962
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3315 0.09817 0.09467 -0.0332 1.0000 0.0524
-9.000 -0.3556 0.09771 0.09433 -0.0303 1.0000 0.0525
-8.750 -0.3747 0.09662 0.09330 -0.0294 1.0000 0.0526
-8.500 -0.3826 0.09379 0.09054 -0.0272 1.0000 0.0529
-8.250 -0.3776 0.09096 0.08775 -0.0232 0.9996 0.0533
-8.000 -0.3555 0.08751 0.08429 -0.0237 0.9969 0.0542
-7.750 -0.3296 0.08374 0.08051 -0.0282 0.9932 0.0555
-7.500 -0.3030 0.07965 0.07639 -0.0348 0.9874 0.0579
-7.250 -0.2596 0.07145 0.06801 -0.0568 0.9781 0.0621
-7.000 -0.2378 0.06843 0.06502 -0.0567 0.9744 0.0630
-6.750 -0.2080 0.06524 0.06182 -0.0599 0.9713 0.0646
-6.500 -0.1793 0.06179 0.05831 -0.0648 0.9642 0.0673
-6.250 -0.1297 0.05472 0.05095 -0.0796 0.9591 0.0729
-6.000 -0.1012 0.05219 0.04845 -0.0813 0.9552 0.0744
-5.750 -0.0520 0.04763 0.04335 -0.0919 0.9479 0.0837
-5.500 -0.0232 0.04429 0.04018 -0.0935 0.9447 0.0852
-5.250 0.0050 0.04225 0.03815 -0.0948 0.9377 0.0878
-5.000 0.0469 0.03840 0.03382 -0.1006 0.9309 0.0976
-4.750 0.0742 0.03610 0.03159 -0.1015 0.9238 0.0996
-4.500 0.1022 0.03430 0.02973 -0.1022 0.9154 0.1035
-4.250 0.1331 0.03173 0.02680 -0.1039 0.9067 0.1132
-4.000 0.1588 0.03007 0.02513 -0.1039 0.8981 0.1164
-3.750 0.1864 0.02846 0.02316 -0.1043 0.8881 0.1282
-3.500 0.2227 0.02146 0.01495 -0.1042 0.8810 0.0741
-3.250 0.2494 0.01973 0.01290 -0.1033 0.8706 0.0684
-3.000 0.2779 0.01807 0.01086 -0.1027 0.8630 0.0655
-2.750 0.3040 0.01698 0.00951 -0.1017 0.8515 0.0644
-2.500 0.3311 0.01617 0.00856 -0.1010 0.8423 0.0646
-2.250 0.3580 0.01552 0.00783 -0.1002 0.8324 0.0656
-2.000 0.3845 0.01506 0.00733 -0.0995 0.8216 0.0681
-1.750 0.4122 0.01453 0.00671 -0.0989 0.8133 0.0701
-1.500 0.4387 0.01409 0.00626 -0.0982 0.8022 0.0716
-1.250 0.4655 0.01353 0.00575 -0.0976 0.7925 0.0746
-1.000 0.4926 0.01319 0.00540 -0.0970 0.7818 0.0794
-0.750 0.5192 0.01288 0.00512 -0.0963 0.7690 0.0877
-0.500 0.5462 0.01255 0.00484 -0.0957 0.7568 0.1122
-0.250 0.5705 0.01141 0.00468 -0.0951 0.7459 0.4111
0.000 0.6072 0.01011 0.00454 -0.0963 0.7336 1.0000
0.250 0.6338 0.01019 0.00447 -0.0957 0.7204 1.0000
0.500 0.6605 0.01028 0.00442 -0.0951 0.7068 1.0000
0.750 0.6870 0.01038 0.00437 -0.0945 0.6923 1.0000
1.000 0.7134 0.01049 0.00436 -0.0939 0.6777 1.0000
1.250 0.7398 0.01061 0.00436 -0.0934 0.6629 1.0000
1.500 0.7659 0.01074 0.00438 -0.0928 0.6467 1.0000
1.750 0.7918 0.01088 0.00443 -0.0921 0.6287 1.0000
2.000 0.8173 0.01102 0.00448 -0.0915 0.6082 1.0000
2.250 0.8426 0.01119 0.00453 -0.0908 0.5866 1.0000
2.500 0.8676 0.01140 0.00461 -0.0900 0.5638 1.0000
2.750 0.8922 0.01162 0.00472 -0.0893 0.5371 1.0000
3.000 0.9163 0.01189 0.00485 -0.0885 0.5087 1.0000
3.250 0.9400 0.01221 0.00502 -0.0876 0.4797 1.0000
3.500 0.9635 0.01258 0.00523 -0.0868 0.4522 1.0000
3.750 0.9869 0.01297 0.00548 -0.0860 0.4269 1.0000
4.000 1.0099 0.01340 0.00576 -0.0852 0.4044 1.0000
4.250 1.0329 0.01385 0.00608 -0.0844 0.3843 1.0000
4.500 1.0558 0.01430 0.00643 -0.0836 0.3652 1.0000
4.750 1.0784 0.01478 0.00683 -0.0828 0.3464 1.0000
5.000 1.1006 0.01529 0.00724 -0.0819 0.3272 1.0000
5.250 1.1220 0.01584 0.00768 -0.0809 0.3066 1.0000
5.500 1.1433 0.01636 0.00813 -0.0800 0.2841 1.0000
5.750 1.1645 0.01687 0.00858 -0.0790 0.2610 1.0000
6.000 1.1850 0.01743 0.00904 -0.0779 0.2418 1.0000
6.250 1.2055 0.01801 0.00952 -0.0769 0.2263 1.0000
6.500 1.2261 0.01859 0.01004 -0.0759 0.2139 1.0000
6.750 1.2461 0.01922 0.01065 -0.0748 0.2045 1.0000
7.000 1.2648 0.01995 0.01128 -0.0736 0.1963 1.0000
7.250 1.2849 0.02060 0.01195 -0.0725 0.1889 1.0000
7.500 1.3032 0.02141 0.01269 -0.0713 0.1822 1.0000
7.750 1.3228 0.02218 0.01348 -0.0702 0.1764 1.0000
8.000 1.3421 0.02292 0.01425 -0.0691 0.1708 1.0000
8.250 1.3622 0.02408 0.01525 -0.0683 0.1653 1.0000
8.500 1.3811 0.02471 0.01605 -0.0671 0.1608 1.0000
8.750 1.3996 0.02547 0.01686 -0.0660 0.1558 1.0000
9.000 1.4213 0.02673 0.01797 -0.0656 0.1502 1.0000
9.250 1.4358 0.02728 0.01873 -0.0638 0.1461 1.0000
9.500 1.4509 0.02796 0.01951 -0.0622 0.1415 1.0000
9.750 1.4671 0.02885 0.02036 -0.0609 0.1374 1.0000
10.000 1.4836 0.02984 0.02143 -0.0597 0.1337 1.0000
10.250 1.4952 0.03057 0.02232 -0.0576 0.1304 1.0000
10.500 1.5072 0.03133 0.02318 -0.0558 0.1270 1.0000
10.750 1.5196 0.03218 0.02404 -0.0541 0.1238 1.0000
11.000 1.5346 0.03330 0.02519 -0.0530 0.1206 1.0000
11.250 1.5425 0.03421 0.02632 -0.0509 0.1180 1.0000
11.500 1.5516 0.03518 0.02742 -0.0491 0.1151 1.0000
11.750 1.5606 0.03616 0.02849 -0.0476 0.1124 1.0000
12.000 1.5698 0.03726 0.02959 -0.0462 0.1097 1.0000
12.250 1.5771 0.03857 0.03105 -0.0447 0.1070 1.0000
12.500 1.5824 0.03992 0.03260 -0.0432 0.1044 1.0000
12.750 1.5882 0.04129 0.03411 -0.0419 0.1018 1.0000
13.000 1.5937 0.04273 0.03565 -0.0408 0.0994 1.0000
13.250 1.5991 0.04431 0.03722 -0.0398 0.0968 1.0000
13.500 1.6009 0.04625 0.03940 -0.0390 0.0941 1.0000
13.750 1.6026 0.04827 0.04162 -0.0384 0.0909 1.0000
14.000 1.6033 0.05047 0.04392 -0.0381 0.0876 1.0000
14.250 1.6025 0.05300 0.04650 -0.0379 0.0843 1.0000
14.500 1.6028 0.05566 0.04944 -0.0380 0.0803 1.0000
14.750 1.6001 0.05876 0.05263 -0.0385 0.0761 1.0000
15.000 1.5971 0.06213 0.05617 -0.0390 0.0713 1.0000
15.250 1.5910 0.06610 0.06025 -0.0400 0.0659 1.0000
15.500 1.5838 0.07037 0.06467 -0.0410 0.0595 1.0000
15.750 1.5710 0.07556 0.06995 -0.0424 0.0543 1.0000
16.000 1.5562 0.08125 0.07574 -0.0441 0.0495 1.0000
16.250 1.5397 0.08733 0.08194 -0.0460 0.0458 1.0000
16.500 1.5211 0.09398 0.08870 -0.0484 0.0431 1.0000
16.750 1.5004 0.10119 0.09601 -0.0513 0.0416 1.0000
17.000 1.4821 0.10817 0.10313 -0.0542 0.0398 1.0000
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Polar data table (+)
Polar graphs
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