I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 962 (isa962-il) Reynolds number: 200,000 Max Cl/Cd: 69.8 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa962-il-200000-n5.txt Download as CSV file: xf-isa962-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3305 0.11088 0.10704 -0.0287 1.0000 0.0394
-10.500 -0.3325 0.10777 0.10397 -0.0318 1.0000 0.0396
-10.250 -0.3322 0.10453 0.10077 -0.0341 1.0000 0.0397
-10.000 -0.3324 0.10139 0.09767 -0.0358 1.0000 0.0398
-9.750 -0.3232 0.09808 0.09440 -0.0343 1.0000 0.0401
-9.500 -0.3146 0.09552 0.09187 -0.0331 1.0000 0.0404
-9.250 -0.3112 0.09330 0.08970 -0.0321 1.0000 0.0408
-9.000 -0.3141 0.09151 0.08798 -0.0305 1.0000 0.0412
-8.750 -0.2980 0.08831 0.08479 -0.0337 0.9936 0.0423
-8.500 -0.2821 0.08477 0.08125 -0.0383 0.9838 0.0439
-8.250 -0.2617 0.07823 0.07465 -0.0550 0.9657 0.0466
-8.000 -0.2364 0.07232 0.06865 -0.0655 0.9559 0.0468
-7.750 -0.2162 0.06756 0.06385 -0.0699 0.9484 0.0471
-7.500 -0.1976 0.06462 0.06091 -0.0708 0.9419 0.0476
-7.250 -0.1760 0.06169 0.05795 -0.0730 0.9346 0.0481
-6.750 -0.1197 0.04686 0.04259 -0.0895 0.9178 0.0395
-6.500 -0.0984 0.04480 0.04049 -0.0903 0.9101 0.0390
-6.250 -0.0746 0.04147 0.03701 -0.0925 0.9025 0.0382
-6.000 -0.0498 0.03713 0.03241 -0.0951 0.8945 0.0372
-5.750 -0.0245 0.03196 0.02681 -0.0974 0.8863 0.0364
-5.500 0.0000 0.02730 0.02161 -0.0986 0.8777 0.0360
-5.250 0.0255 0.02485 0.01878 -0.0988 0.8692 0.0367
-5.000 0.0507 0.02275 0.01629 -0.0987 0.8592 0.0372
-4.750 0.0769 0.02095 0.01409 -0.0984 0.8504 0.0373
-4.500 0.1032 0.01954 0.01236 -0.0981 0.8401 0.0374
-4.250 0.1300 0.01842 0.01096 -0.0977 0.8307 0.0376
-4.000 0.1570 0.01749 0.00978 -0.0973 0.8210 0.0379
-3.750 0.1841 0.01671 0.00882 -0.0969 0.8105 0.0383
-3.500 0.2114 0.01605 0.00798 -0.0965 0.8008 0.0387
-3.250 0.2387 0.01548 0.00727 -0.0960 0.7898 0.0392
-3.000 0.2659 0.01499 0.00667 -0.0956 0.7782 0.0400
-2.750 0.2928 0.01445 0.00612 -0.0953 0.7673 0.0412
-2.500 0.3200 0.01407 0.00570 -0.0949 0.7561 0.0423
-2.250 0.3472 0.01371 0.00529 -0.0945 0.7443 0.0431
-2.000 0.3745 0.01341 0.00493 -0.0941 0.7325 0.0440
-1.750 0.4017 0.01315 0.00460 -0.0937 0.7205 0.0450
-1.500 0.4290 0.01295 0.00434 -0.0933 0.7083 0.0461
-1.250 0.4562 0.01276 0.00410 -0.0930 0.6960 0.0476
-1.000 0.4833 0.01260 0.00390 -0.0926 0.6824 0.0500
-0.750 0.5103 0.01252 0.00375 -0.0922 0.6680 0.0541
-0.500 0.5373 0.01241 0.00362 -0.0919 0.6539 0.0603
-0.250 0.5644 0.01228 0.00358 -0.0915 0.6402 0.0816
0.000 0.5913 0.01217 0.00355 -0.0912 0.6267 0.1288
0.250 0.6175 0.01194 0.00360 -0.0910 0.6123 0.2290
0.500 0.6427 0.01157 0.00368 -0.0906 0.5969 0.4059
1.000 0.7027 0.01059 0.00372 -0.0910 0.5593 1.0000
1.250 0.7285 0.01078 0.00376 -0.0905 0.5393 1.0000
1.500 0.7542 0.01099 0.00383 -0.0899 0.5174 1.0000
1.750 0.7794 0.01123 0.00391 -0.0893 0.4915 1.0000
2.000 0.8041 0.01152 0.00402 -0.0886 0.4617 1.0000
2.250 0.8279 0.01188 0.00417 -0.0879 0.4283 1.0000
2.500 0.8518 0.01225 0.00435 -0.0872 0.4011 1.0000
2.750 0.8758 0.01262 0.00456 -0.0865 0.3792 1.0000
3.000 0.8998 0.01300 0.00480 -0.0859 0.3610 1.0000
3.250 0.9241 0.01336 0.00506 -0.0853 0.3460 1.0000
3.500 0.9485 0.01371 0.00533 -0.0847 0.3332 1.0000
3.750 0.9727 0.01407 0.00561 -0.0841 0.3212 1.0000
4.000 0.9969 0.01442 0.00591 -0.0836 0.3085 1.0000
4.250 1.0213 0.01476 0.00621 -0.0831 0.2955 1.0000
4.500 1.0453 0.01511 0.00652 -0.0825 0.2816 1.0000
4.750 1.0691 0.01547 0.00683 -0.0819 0.2653 1.0000
5.000 1.0923 0.01586 0.00716 -0.0812 0.2458 1.0000
5.250 1.1147 0.01631 0.00751 -0.0805 0.2240 1.0000
5.500 1.1362 0.01683 0.00791 -0.0796 0.2029 1.0000
5.750 1.1572 0.01740 0.00838 -0.0787 0.1888 1.0000
6.000 1.1781 0.01795 0.00887 -0.0778 0.1796 1.0000
6.250 1.1989 0.01850 0.00939 -0.0768 0.1725 1.0000
6.500 1.2189 0.01909 0.00995 -0.0758 0.1666 1.0000
6.750 1.2398 0.01959 0.01050 -0.0749 0.1613 1.0000
7.000 1.2593 0.02018 0.01109 -0.0737 0.1565 1.0000
7.250 1.2769 0.02089 0.01176 -0.0724 0.1523 1.0000
7.500 1.2976 0.02135 0.01233 -0.0715 0.1485 1.0000
7.750 1.3169 0.02190 0.01294 -0.0703 0.1443 1.0000
8.000 1.3343 0.02254 0.01360 -0.0690 0.1404 1.0000
8.250 1.3490 0.02333 0.01437 -0.0673 0.1370 1.0000
8.500 1.3665 0.02385 0.01501 -0.0658 0.1340 1.0000
8.750 1.3831 0.02442 0.01567 -0.0644 0.1303 1.0000
9.000 1.3980 0.02509 0.01638 -0.0628 0.1263 1.0000
9.250 1.4103 0.02593 0.01721 -0.0609 0.1225 1.0000
9.500 1.4268 0.02654 0.01794 -0.0597 0.1186 1.0000
9.750 1.4419 0.02724 0.01874 -0.0583 0.1144 1.0000
10.000 1.4546 0.02809 0.01962 -0.0568 0.1107 1.0000
10.250 1.4674 0.02899 0.02057 -0.0554 0.1071 1.0000
10.500 1.4816 0.02982 0.02151 -0.0542 0.1032 1.0000
10.750 1.4938 0.03080 0.02257 -0.0529 0.0998 1.0000
11.000 1.5038 0.03196 0.02377 -0.0516 0.0970 1.0000
11.250 1.5157 0.03304 0.02496 -0.0504 0.0941 1.0000
11.500 1.5271 0.03417 0.02620 -0.0493 0.0909 1.0000
11.750 1.5367 0.03547 0.02757 -0.0482 0.0879 1.0000
12.000 1.5436 0.03701 0.02917 -0.0470 0.0849 1.0000
12.250 1.5538 0.03834 0.03064 -0.0461 0.0819 1.0000
12.500 1.5621 0.03987 0.03228 -0.0452 0.0787 1.0000
12.750 1.5677 0.04168 0.03416 -0.0444 0.0756 1.0000
13.000 1.5734 0.04354 0.03612 -0.0436 0.0727 1.0000
13.250 1.5798 0.04539 0.03811 -0.0430 0.0691 1.0000
13.500 1.5821 0.04771 0.04049 -0.0424 0.0650 1.0000
13.750 1.5856 0.04995 0.04286 -0.0420 0.0607 1.0000
14.000 1.5857 0.05265 0.04564 -0.0417 0.0561 1.0000
14.250 1.5854 0.05548 0.04857 -0.0415 0.0509 1.0000
14.500 1.5810 0.05888 0.05204 -0.0416 0.0442 1.0000
14.750 1.5715 0.06308 0.05628 -0.0419 0.0351 1.0000
15.000 1.5555 0.06835 0.06156 -0.0428 0.0273 1.0000
15.250 1.5398 0.07381 0.06711 -0.0439 0.0242 1.0000
15.500 1.5241 0.07952 0.07294 -0.0454 0.0227 1.0000
15.750 1.5075 0.08560 0.07917 -0.0473 0.0217 1.0000
16.000 1.4899 0.09207 0.08580 -0.0495 0.0211 1.0000
16.250 1.4722 0.09882 0.09272 -0.0521 0.0206 1.0000
16.500 1.4532 0.10602 0.10010 -0.0550 0.0203 1.0000
16.750 1.4328 0.11365 0.10790 -0.0584 0.0201 1.0000
17.000 1.4113 0.12167 0.11610 -0.0620 0.0201 1.0000
17.250 1.3885 0.13016 0.12478 -0.0661 0.0200 1.0000
17.500 1.3647 0.13910 0.13390 -0.0707 0.0201 1.0000
17.750 1.3397 0.14859 0.14356 -0.0757 0.0203 1.0000
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Polar data table (+)
Polar graphs
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