I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 960 (isa960-il) Reynolds number: 100,000 Max Cl/Cd: 55.87 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa960-il-100000.txt Download as CSV file: xf-isa960-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 960
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3410 0.09220 0.08789 -0.0287 1.0000 0.0989
-8.250 -0.3571 0.09089 0.08671 -0.0275 1.0000 0.1006
-8.000 -0.3778 0.08997 0.08589 -0.0292 1.0000 0.1022
-7.750 -0.3952 0.08875 0.08469 -0.0348 1.0000 0.1030
-7.500 -0.3961 0.08473 0.08077 -0.0311 1.0000 0.1038
-7.250 -0.3936 0.08206 0.07818 -0.0248 1.0000 0.1057
-7.000 -0.3948 0.08013 0.07631 -0.0221 1.0000 0.1085
-6.750 -0.3968 0.07795 0.07415 -0.0222 1.0000 0.1123
-6.500 -0.3907 0.07411 0.07012 -0.0326 0.9998 0.1176
-6.250 -0.3541 0.06905 0.06513 -0.0337 0.9924 0.1214
-6.000 -0.2981 0.06231 0.05805 -0.0489 0.9835 0.1329
-5.750 -0.2598 0.05829 0.05401 -0.0524 0.9741 0.1416
-5.500 -0.1983 0.04157 0.03591 -0.0701 0.9696 0.0886
-5.250 -0.1551 0.03596 0.02989 -0.0750 0.9612 0.0861
-5.000 -0.1072 0.03032 0.02318 -0.0801 0.9553 0.0898
-4.750 -0.0662 0.02814 0.02089 -0.0830 0.9470 0.0951
-4.500 -0.0209 0.02575 0.01793 -0.0863 0.9406 0.1058
-4.250 0.0235 0.02404 0.01591 -0.0890 0.9324 0.1194
-4.000 0.0698 0.02284 0.01443 -0.0920 0.9239 0.1455
-3.750 0.1152 0.02164 0.01322 -0.0949 0.9152 0.1706
-3.500 0.1534 0.02086 0.01226 -0.0962 0.9023 0.1901
-3.250 0.1887 0.02014 0.01144 -0.0970 0.8889 0.2075
-3.000 0.2206 0.01934 0.01063 -0.0972 0.8765 0.2173
-2.750 0.2524 0.01859 0.00974 -0.0973 0.8652 0.2242
-2.500 0.2827 0.01791 0.00904 -0.0971 0.8537 0.2334
-2.250 0.3094 0.01735 0.00850 -0.0964 0.8404 0.2448
-2.000 0.3362 0.01681 0.00801 -0.0957 0.8275 0.2619
-1.750 0.3629 0.01627 0.00757 -0.0950 0.8146 0.2884
-1.500 0.3894 0.01567 0.00712 -0.0942 0.8016 0.3281
-1.250 0.4236 0.01331 0.00671 -0.0944 0.7891 1.0000
-1.000 0.4519 0.01330 0.00631 -0.0938 0.7761 1.0000
-0.750 0.4794 0.01330 0.00606 -0.0932 0.7635 1.0000
-0.500 0.5062 0.01334 0.00590 -0.0926 0.7494 1.0000
-0.250 0.5328 0.01337 0.00573 -0.0918 0.7332 1.0000
0.000 0.5593 0.01344 0.00563 -0.0912 0.7175 1.0000
0.250 0.5856 0.01355 0.00559 -0.0906 0.7021 1.0000
0.500 0.6114 0.01367 0.00558 -0.0899 0.6852 1.0000
0.750 0.6369 0.01379 0.00562 -0.0893 0.6672 1.0000
1.000 0.6625 0.01392 0.00566 -0.0887 0.6498 1.0000
1.250 0.6882 0.01406 0.00573 -0.0881 0.6327 1.0000
1.500 0.7138 0.01421 0.00580 -0.0875 0.6147 1.0000
1.750 0.7394 0.01436 0.00588 -0.0869 0.5960 1.0000
2.000 0.7648 0.01453 0.00597 -0.0863 0.5759 1.0000
2.250 0.7900 0.01473 0.00607 -0.0857 0.5553 1.0000
2.500 0.8150 0.01497 0.00621 -0.0850 0.5348 1.0000
2.750 0.8397 0.01524 0.00639 -0.0844 0.5131 1.0000
3.000 0.8635 0.01556 0.00659 -0.0836 0.4881 1.0000
3.250 0.8873 0.01592 0.00685 -0.0828 0.4623 1.0000
3.500 0.9106 0.01630 0.00716 -0.0820 0.4348 1.0000
3.750 0.9334 0.01674 0.00748 -0.0812 0.4062 1.0000
4.000 0.9559 0.01720 0.00783 -0.0803 0.3797 1.0000
4.250 0.9781 0.01770 0.00823 -0.0795 0.3561 1.0000
4.500 1.0002 0.01823 0.00869 -0.0786 0.3373 1.0000
4.750 1.0221 0.01879 0.00916 -0.0777 0.3205 1.0000
5.000 1.0437 0.01938 0.00968 -0.0768 0.3059 1.0000
5.250 1.0649 0.02003 0.01026 -0.0759 0.2940 1.0000
5.500 1.0866 0.02066 0.01089 -0.0751 0.2828 1.0000
5.750 1.1080 0.02135 0.01156 -0.0742 0.2724 1.0000
6.000 1.1289 0.02216 0.01229 -0.0733 0.2629 1.0000
6.250 1.1508 0.02291 0.01310 -0.0725 0.2534 1.0000
6.500 1.1733 0.02381 0.01396 -0.0718 0.2454 1.0000
6.750 1.1966 0.02468 0.01486 -0.0713 0.2381 1.0000
7.000 1.2217 0.02570 0.01582 -0.0711 0.2327 1.0000
7.250 1.2463 0.02660 0.01690 -0.0708 0.2278 1.0000
7.500 1.2710 0.02751 0.01789 -0.0706 0.2230 1.0000
7.750 1.2939 0.02839 0.01877 -0.0702 0.2168 1.0000
8.000 1.3106 0.02891 0.01952 -0.0687 0.2082 1.0000
8.250 1.3268 0.02942 0.02014 -0.0673 0.1999 1.0000
8.500 1.3430 0.02992 0.02087 -0.0658 0.1924 1.0000
8.750 1.3593 0.03047 0.02157 -0.0644 0.1862 1.0000
9.000 1.3717 0.03084 0.02219 -0.0624 0.1777 1.0000
9.250 1.3826 0.03122 0.02281 -0.0602 0.1684 1.0000
9.500 1.3878 0.03163 0.02332 -0.0572 0.1577 1.0000
9.750 1.3914 0.03253 0.02424 -0.0544 0.1481 1.0000
10.000 1.3902 0.03426 0.02581 -0.0515 0.1369 1.0000
10.250 1.3880 0.03695 0.02832 -0.0488 0.1225 1.0000
10.500 1.3850 0.04031 0.03160 -0.0463 0.1034 1.0000
10.750 1.3720 0.04261 0.03440 -0.0432 0.0899 1.0000
11.000 1.3758 0.04396 0.03627 -0.0421 0.0651 1.0000
11.250 1.3779 0.04600 0.03810 -0.0416 0.0587 1.0000
11.500 1.3725 0.04912 0.04123 -0.0404 0.0551 1.0000
11.750 1.3657 0.05252 0.04473 -0.0394 0.0524 1.0000
12.000 1.3569 0.05625 0.04852 -0.0387 0.0502 1.0000
12.250 1.3474 0.06013 0.05241 -0.0380 0.0483 1.0000
12.500 1.3448 0.06340 0.05585 -0.0373 0.0465 1.0000
12.750 1.3427 0.06670 0.05932 -0.0368 0.0447 1.0000
13.000 1.3415 0.06992 0.06270 -0.0362 0.0434 1.0000
13.250 1.3414 0.07308 0.06598 -0.0356 0.0423 1.0000
13.500 1.3415 0.07632 0.06932 -0.0351 0.0412 1.0000
13.750 1.3417 0.07964 0.07275 -0.0345 0.0404 1.0000
14.000 1.3424 0.08306 0.07628 -0.0340 0.0396 1.0000
14.250 1.3407 0.08700 0.08038 -0.0337 0.0391 1.0000
14.500 1.3349 0.09170 0.08526 -0.0339 0.0386 1.0000
14.750 1.3235 0.09712 0.09089 -0.0351 0.0384 1.0000
15.000 1.3093 0.10301 0.09703 -0.0373 0.0384 1.0000
15.250 1.2936 0.10945 0.10371 -0.0402 0.0383 1.0000
15.500 1.2764 0.11644 0.11092 -0.0436 0.0384 1.0000
15.750 1.2583 0.12397 0.11869 -0.0477 0.0385 1.0000
16.000 1.2353 0.13323 0.12823 -0.0542 0.0391 1.0000
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Polar data table (+)
Polar graphs
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