I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 961 (isa961-il) Reynolds number: 100,000 Max Cl/Cd: 55.53 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa961-il-100000.txt Download as CSV file: xf-isa961-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3456 0.09443 0.08995 -0.0283 1.0000 0.0910
-8.250 -0.3653 0.09349 0.08916 -0.0290 1.0000 0.0921
-8.000 -0.3826 0.09233 0.08808 -0.0323 1.0000 0.0927
-7.750 -0.3903 0.08957 0.08536 -0.0342 1.0000 0.0932
-7.500 -0.3861 0.08543 0.08130 -0.0280 1.0000 0.0943
-7.250 -0.3847 0.08278 0.07870 -0.0246 1.0000 0.0956
-7.000 -0.3850 0.08040 0.07636 -0.0228 1.0000 0.0974
-6.750 -0.3851 0.07793 0.07391 -0.0224 1.0000 0.0996
-6.500 -0.3829 0.07511 0.07108 -0.0241 1.0000 0.1032
-6.250 -0.3733 0.07074 0.06656 -0.0323 1.0000 0.1074
-6.000 -0.3694 0.06795 0.06383 -0.0291 1.0000 0.1089
-5.750 -0.3620 0.06546 0.06136 -0.0278 1.0000 0.1117
-5.500 -0.3405 0.06144 0.05707 -0.0345 1.0000 0.1214
-5.250 -0.3352 0.05935 0.05510 -0.0310 1.0000 0.1251
-5.000 -0.2812 0.04416 0.03879 -0.0448 1.0000 0.0780
-4.750 -0.2514 0.03920 0.03350 -0.0475 0.9989 0.0753
-4.500 -0.2023 0.03212 0.02533 -0.0531 0.9961 0.0773
-4.250 -0.1572 0.02970 0.02252 -0.0571 0.9905 0.0886
-4.000 -0.1089 0.02767 0.02001 -0.0613 0.9848 0.1106
-3.750 -0.0657 0.02728 0.01937 -0.0646 0.9762 0.1368
-3.500 -0.0232 0.02728 0.01941 -0.0680 0.9682 0.1594
-3.250 0.0203 0.02603 0.01776 -0.0711 0.9608 0.1675
-3.000 0.0615 0.02529 0.01682 -0.0738 0.9529 0.1755
-2.750 0.1065 0.02437 0.01557 -0.0770 0.9457 0.1803
-2.500 0.1446 0.02371 0.01488 -0.0791 0.9367 0.1876
-2.250 0.1919 0.02295 0.01400 -0.0827 0.9302 0.1970
-2.000 0.2281 0.02241 0.01343 -0.0842 0.9198 0.2060
-1.750 0.2794 0.02155 0.01261 -0.0883 0.9145 0.2226
-1.500 0.3162 0.02085 0.01210 -0.0897 0.9031 0.2488
-1.250 0.3603 0.01978 0.01131 -0.0920 0.8925 0.3052
-1.000 0.4228 0.01673 0.01015 -0.0970 0.8855 1.0000
-0.750 0.4606 0.01635 0.00946 -0.0976 0.8712 1.0000
-0.500 0.4941 0.01604 0.00897 -0.0976 0.8567 1.0000
-0.250 0.5253 0.01578 0.00856 -0.0972 0.8419 1.0000
0.000 0.5549 0.01554 0.00820 -0.0966 0.8267 1.0000
0.250 0.5835 0.01532 0.00787 -0.0958 0.8111 1.0000
0.500 0.6115 0.01514 0.00758 -0.0949 0.7952 1.0000
0.750 0.6381 0.01501 0.00737 -0.0939 0.7779 1.0000
1.000 0.6635 0.01495 0.00722 -0.0927 0.7585 1.0000
1.250 0.6901 0.01485 0.00703 -0.0917 0.7388 1.0000
1.500 0.7166 0.01479 0.00685 -0.0907 0.7178 1.0000
1.750 0.7418 0.01481 0.00678 -0.0896 0.6937 1.0000
2.000 0.7670 0.01488 0.00673 -0.0885 0.6689 1.0000
2.250 0.7925 0.01500 0.00670 -0.0875 0.6445 1.0000
2.500 0.8169 0.01520 0.00682 -0.0865 0.6183 1.0000
2.750 0.8411 0.01545 0.00693 -0.0855 0.5918 1.0000
3.000 0.8650 0.01574 0.00707 -0.0845 0.5652 1.0000
3.250 0.8887 0.01606 0.00722 -0.0835 0.5392 1.0000
3.500 0.9116 0.01643 0.00747 -0.0824 0.5130 1.0000
3.750 0.9345 0.01683 0.00775 -0.0814 0.4883 1.0000
4.000 0.9575 0.01726 0.00802 -0.0805 0.4663 1.0000
4.250 0.9805 0.01771 0.00840 -0.0796 0.4458 1.0000
4.500 1.0040 0.01819 0.00884 -0.0789 0.4288 1.0000
4.750 1.0278 0.01869 0.00930 -0.0783 0.4142 1.0000
5.000 1.0516 0.01919 0.00978 -0.0777 0.4008 1.0000
5.250 1.0751 0.01969 0.01028 -0.0770 0.3875 1.0000
5.500 1.0983 0.02019 0.01076 -0.0763 0.3745 1.0000
5.750 1.1215 0.02068 0.01131 -0.0756 0.3624 1.0000
6.000 1.1444 0.02118 0.01189 -0.0749 0.3505 1.0000
6.250 1.1671 0.02170 0.01250 -0.0742 0.3392 1.0000
6.500 1.1896 0.02225 0.01308 -0.0734 0.3281 1.0000
6.750 1.2116 0.02280 0.01367 -0.0726 0.3166 1.0000
7.000 1.2323 0.02335 0.01432 -0.0716 0.3036 1.0000
7.250 1.2521 0.02392 0.01500 -0.0704 0.2898 1.0000
7.500 1.2714 0.02456 0.01572 -0.0692 0.2761 1.0000
7.750 1.2892 0.02521 0.01642 -0.0678 0.2612 1.0000
8.000 1.3049 0.02583 0.01707 -0.0661 0.2452 1.0000
8.250 1.3193 0.02646 0.01773 -0.0643 0.2293 1.0000
8.500 1.3336 0.02715 0.01853 -0.0625 0.2148 1.0000
8.750 1.3482 0.02788 0.01939 -0.0608 0.2016 1.0000
9.000 1.3625 0.02864 0.02030 -0.0590 0.1894 1.0000
9.250 1.3746 0.02939 0.02116 -0.0570 0.1761 1.0000
9.500 1.3834 0.03018 0.02203 -0.0546 0.1625 1.0000
9.750 1.3904 0.03118 0.02306 -0.0520 0.1508 1.0000
10.000 1.3957 0.03243 0.02433 -0.0494 0.1407 1.0000
10.250 1.3975 0.03402 0.02590 -0.0467 0.1322 1.0000
10.500 1.3991 0.03579 0.02778 -0.0443 0.1220 1.0000
10.750 1.3982 0.03783 0.02993 -0.0419 0.1106 1.0000
11.000 1.3964 0.04004 0.03231 -0.0398 0.0975 1.0000
11.250 1.3979 0.04214 0.03461 -0.0384 0.0769 1.0000
11.500 1.3893 0.04528 0.03758 -0.0370 0.0666 1.0000
11.750 1.3731 0.04939 0.04159 -0.0357 0.0618 1.0000
12.000 1.3598 0.05351 0.04584 -0.0346 0.0576 1.0000
12.250 1.3467 0.05778 0.05019 -0.0340 0.0545 1.0000
12.500 1.3359 0.06169 0.05397 -0.0325 0.0513 1.0000
12.750 1.3331 0.06514 0.05765 -0.0320 0.0489 1.0000
13.000 1.3315 0.06847 0.06113 -0.0313 0.0464 1.0000
13.250 1.3309 0.07166 0.06439 -0.0306 0.0441 1.0000
13.500 1.3409 0.07384 0.06642 -0.0283 0.0411 1.0000
13.750 1.3333 0.07801 0.07090 -0.0290 0.0402 1.0000
14.000 1.3265 0.08229 0.07544 -0.0297 0.0391 1.0000
14.250 1.3199 0.08674 0.08013 -0.0306 0.0381 1.0000
14.500 1.3123 0.09148 0.08510 -0.0317 0.0374 1.0000
14.750 1.3033 0.09657 0.09041 -0.0331 0.0369 1.0000
15.000 1.2921 0.10221 0.09628 -0.0351 0.0366 1.0000
15.250 1.2782 0.10851 0.10281 -0.0378 0.0365 1.0000
15.500 1.2613 0.11569 0.11022 -0.0414 0.0365 1.0000
15.750 1.2407 0.12395 0.11872 -0.0460 0.0368 1.0000
16.000 1.2163 0.13358 0.12858 -0.0519 0.0373 1.0000
16.250 1.1883 0.14481 0.14002 -0.0591 0.0381 1.0000
16.500 1.1571 0.15783 0.15317 -0.0675 0.0393 1.0000
16.750 1.1303 0.17063 0.16602 -0.0752 0.0405 1.0000
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Polar data table (+)
Polar graphs
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