I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 961 (isa961-il) Reynolds number: 200,000 Max Cl/Cd: 63.01 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa961-il-200000-n5.txt Download as CSV file: xf-isa961-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 961
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3397 0.08958 0.08630 -0.0336 1.0000 0.0147
-9.000 -0.3485 0.08745 0.08425 -0.0322 1.0000 0.0149
-8.750 -0.3557 0.08463 0.08150 -0.0322 0.9977 0.0149
-8.500 -0.3410 0.07881 0.07569 -0.0397 0.9897 0.0149
-8.250 -0.3277 0.06906 0.06592 -0.0521 0.9800 0.0142
-8.000 -0.3106 0.05695 0.05371 -0.0668 0.9698 0.0137
-7.750 -0.2932 0.03291 0.02868 -0.0889 0.9583 0.0132
-7.500 -0.2655 0.02693 0.02187 -0.0930 0.9536 0.0133
-7.250 -0.2382 0.02392 0.01834 -0.0944 0.9482 0.0136
-7.000 -0.2107 0.02125 0.01520 -0.0955 0.9427 0.0141
-6.750 -0.1793 0.01956 0.01322 -0.0967 0.9389 0.0149
-6.500 -0.1497 0.01847 0.01193 -0.0974 0.9336 0.0163
-6.250 -0.1198 0.01746 0.01071 -0.0979 0.9281 0.0178
-6.000 -0.0875 0.01650 0.00951 -0.0987 0.9238 0.0189
-5.750 -0.0576 0.01571 0.00853 -0.0990 0.9180 0.0201
-5.500 -0.0279 0.01489 0.00755 -0.0993 0.9120 0.0230
-5.250 0.0039 0.01419 0.00676 -0.0999 0.9073 0.0288
-5.000 0.0317 0.01374 0.00645 -0.0997 0.8990 0.0464
-4.750 0.0628 0.01375 0.00628 -0.0999 0.8896 0.0657
-4.500 0.0915 0.01363 0.00605 -0.0997 0.8770 0.0747
-4.250 0.1186 0.01345 0.00574 -0.0992 0.8632 0.0827
-4.000 0.1455 0.01327 0.00549 -0.0988 0.8502 0.0896
-3.750 0.1725 0.01303 0.00516 -0.0984 0.8387 0.0949
-3.500 0.1997 0.01277 0.00485 -0.0981 0.8280 0.0981
-3.250 0.2272 0.01254 0.00454 -0.0977 0.8174 0.1007
-3.000 0.2541 0.01235 0.00427 -0.0973 0.8049 0.1042
-2.750 0.2810 0.01216 0.00403 -0.0968 0.7908 0.1079
-2.500 0.3079 0.01200 0.00382 -0.0964 0.7750 0.1122
-2.250 0.3348 0.01187 0.00360 -0.0959 0.7574 0.1177
-2.000 0.3613 0.01177 0.00344 -0.0954 0.7370 0.1255
-1.750 0.3879 0.01170 0.00329 -0.0949 0.7154 0.1376
-1.500 0.4144 0.01166 0.00316 -0.0944 0.6950 0.1527
-1.250 0.4408 0.01163 0.00307 -0.0940 0.6736 0.1700
-1.000 0.4668 0.01163 0.00299 -0.0935 0.6498 0.1878
-0.750 0.4927 0.01164 0.00294 -0.0930 0.6249 0.2066
-0.500 0.5184 0.01167 0.00292 -0.0925 0.6007 0.2308
-0.250 0.5438 0.01170 0.00293 -0.0920 0.5749 0.2653
0.000 0.5686 0.01166 0.00297 -0.0915 0.5476 0.3341
0.500 0.6272 0.01063 0.00311 -0.0920 0.4892 1.0000
0.750 0.6517 0.01091 0.00319 -0.0913 0.4628 1.0000
1.000 0.6756 0.01124 0.00330 -0.0906 0.4337 1.0000
1.250 0.6992 0.01161 0.00345 -0.0899 0.4023 1.0000
1.500 0.7226 0.01200 0.00361 -0.0891 0.3693 1.0000
1.750 0.7462 0.01239 0.00378 -0.0885 0.3371 1.0000
2.000 0.7703 0.01273 0.00397 -0.0879 0.3121 1.0000
2.250 0.7950 0.01303 0.00416 -0.0874 0.2947 1.0000
2.500 0.8196 0.01334 0.00436 -0.0869 0.2786 1.0000
2.750 0.8438 0.01368 0.00459 -0.0864 0.2618 1.0000
3.000 0.8683 0.01399 0.00483 -0.0859 0.2482 1.0000
3.250 0.8927 0.01431 0.00507 -0.0854 0.2361 1.0000
3.500 0.9169 0.01464 0.00535 -0.0849 0.2239 1.0000
3.750 0.9409 0.01499 0.00563 -0.0844 0.2112 1.0000
4.000 0.9650 0.01532 0.00592 -0.0839 0.1973 1.0000
4.250 0.9886 0.01569 0.00625 -0.0834 0.1761 1.0000
4.500 1.0085 0.01643 0.00670 -0.0823 0.1360 1.0000
4.750 1.0312 0.01687 0.00710 -0.0817 0.1287 1.0000
5.000 1.0546 0.01724 0.00748 -0.0811 0.1257 1.0000
5.250 1.0779 0.01760 0.00789 -0.0805 0.1230 1.0000
5.500 1.1008 0.01799 0.00832 -0.0798 0.1203 1.0000
5.750 1.1229 0.01844 0.00880 -0.0791 0.1167 1.0000
6.000 1.1453 0.01885 0.00926 -0.0784 0.1144 1.0000
6.250 1.1681 0.01920 0.00972 -0.0777 0.1130 1.0000
6.500 1.1905 0.01957 0.01019 -0.0770 0.1108 1.0000
6.750 1.2113 0.02007 0.01074 -0.0761 0.1053 1.0000
7.000 1.2313 0.02062 0.01131 -0.0751 0.0967 1.0000
7.250 1.2514 0.02115 0.01183 -0.0742 0.0683 1.0000
7.500 1.2664 0.02207 0.01261 -0.0726 0.0598 1.0000
7.750 1.2816 0.02291 0.01349 -0.0709 0.0555 1.0000
8.000 1.2952 0.02378 0.01443 -0.0690 0.0518 1.0000
8.250 1.3106 0.02439 0.01516 -0.0673 0.0481 1.0000
8.500 1.3239 0.02517 0.01603 -0.0654 0.0436 1.0000
8.750 1.3395 0.02580 0.01676 -0.0638 0.0385 1.0000
9.000 1.3482 0.02695 0.01779 -0.0615 0.0180 1.0000
9.250 1.3549 0.02830 0.01920 -0.0591 0.0153 1.0000
9.500 1.3622 0.02964 0.02070 -0.0568 0.0138 1.0000
9.750 1.3692 0.03104 0.02226 -0.0547 0.0128 1.0000
10.000 1.3766 0.03245 0.02383 -0.0528 0.0123 1.0000
10.250 1.3827 0.03401 0.02555 -0.0510 0.0117 1.0000
10.500 1.3871 0.03577 0.02748 -0.0493 0.0111 1.0000
10.750 1.3895 0.03777 0.02965 -0.0476 0.0105 1.0000
11.000 1.3898 0.04006 0.03210 -0.0461 0.0100 1.0000
11.250 1.3878 0.04269 0.03490 -0.0449 0.0096 1.0000
11.500 1.3835 0.04571 0.03809 -0.0439 0.0094 1.0000
11.750 1.3772 0.04911 0.04166 -0.0432 0.0092 1.0000
12.000 1.3681 0.05305 0.04577 -0.0429 0.0090 1.0000
12.250 1.3573 0.05739 0.05029 -0.0431 0.0088 1.0000
12.500 1.3453 0.06213 0.05519 -0.0436 0.0087 1.0000
12.750 1.3379 0.06648 0.05968 -0.0444 0.0087 1.0000
13.000 1.3303 0.07101 0.06435 -0.0453 0.0086 1.0000
13.250 1.3222 0.07577 0.06926 -0.0465 0.0085 1.0000
13.500 1.3139 0.08071 0.07437 -0.0479 0.0084 1.0000
13.750 1.3054 0.08574 0.07954 -0.0493 0.0083 1.0000
14.000 1.2971 0.09082 0.08476 -0.0509 0.0083 1.0000
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Polar data table (+)
Polar graphs
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