I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 962 (isa962-il) Reynolds number: 500,000 Max Cl/Cd: 98.66 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa962-il-500000.txt Download as CSV file: xf-isa962-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3071 0.09316 0.09084 -0.0310 1.0000 0.0295
-9.250 -0.3069 0.09091 0.08864 -0.0308 1.0000 0.0299
-9.000 -0.3121 0.08910 0.08688 -0.0297 0.9992 0.0303
-8.750 -0.2944 0.08482 0.08260 -0.0357 0.9941 0.0316
-8.500 -0.2669 0.07458 0.07229 -0.0596 0.9808 0.0329
-8.250 -0.2531 0.07089 0.06861 -0.0603 0.9750 0.0332
-8.000 -0.2310 0.06800 0.06570 -0.0630 0.9697 0.0335
-7.750 -0.2095 0.06508 0.06276 -0.0662 0.9609 0.0339
-7.500 -0.1870 0.06189 0.05954 -0.0701 0.9518 0.0345
-7.250 -0.1643 0.05839 0.05598 -0.0745 0.9418 0.0353
-7.000 -0.1298 0.04689 0.04411 -0.0906 0.9291 0.0387
-6.750 -0.1130 0.04501 0.04219 -0.0904 0.9189 0.0391
-6.500 -0.0933 0.04327 0.04038 -0.0907 0.9102 0.0395
-6.250 -0.0724 0.04135 0.03839 -0.0913 0.9009 0.0401
-6.000 -0.0494 0.03902 0.03595 -0.0925 0.8929 0.0411
-5.750 -0.0205 0.03093 0.02722 -0.0973 0.8843 0.0457
-5.500 0.0022 0.02960 0.02586 -0.0973 0.8765 0.0462
-5.250 0.0259 0.02838 0.02458 -0.0972 0.8675 0.0470
-5.000 0.0505 0.02696 0.02304 -0.0972 0.8592 0.0483
-4.750 0.0770 0.02357 0.01912 -0.0977 0.8505 0.0539
-4.500 0.1021 0.02254 0.01808 -0.0976 0.8418 0.0549
-4.250 0.1280 0.02156 0.01701 -0.0974 0.8325 0.0565
-4.000 0.1562 0.01598 0.01035 -0.0968 0.8240 0.0463
-3.750 0.1836 0.01437 0.00851 -0.0963 0.8146 0.0419
-3.500 0.2115 0.01302 0.00683 -0.0958 0.8040 0.0402
-3.250 0.2390 0.01244 0.00614 -0.0955 0.7933 0.0406
-3.000 0.2665 0.01193 0.00553 -0.0951 0.7816 0.0411
-2.750 0.2941 0.01140 0.00490 -0.0947 0.7688 0.0412
-2.500 0.3215 0.01098 0.00439 -0.0943 0.7550 0.0416
-2.250 0.3489 0.01063 0.00396 -0.0940 0.7413 0.0421
-2.000 0.3764 0.01036 0.00361 -0.0936 0.7284 0.0428
-1.750 0.4039 0.01014 0.00332 -0.0933 0.7160 0.0435
-1.500 0.4315 0.00995 0.00309 -0.0930 0.7033 0.0443
-1.250 0.4592 0.00978 0.00287 -0.0928 0.6914 0.0452
-1.000 0.4865 0.00954 0.00260 -0.0925 0.6799 0.0477
-0.750 0.5144 0.00943 0.00248 -0.0923 0.6684 0.0500
-0.500 0.5422 0.00936 0.00236 -0.0921 0.6569 0.0524
-0.250 0.5698 0.00926 0.00225 -0.0919 0.6450 0.0582
0.000 0.5971 0.00912 0.00223 -0.0917 0.6311 0.1093
0.250 0.6238 0.00879 0.00229 -0.0916 0.6163 0.2574
0.500 0.6473 0.00788 0.00241 -0.0911 0.6020 0.6513
0.750 0.6829 0.00727 0.00243 -0.0924 0.5861 1.0000
1.000 0.7098 0.00740 0.00246 -0.0921 0.5695 1.0000
1.250 0.7364 0.00756 0.00251 -0.0917 0.5511 1.0000
1.500 0.7628 0.00774 0.00256 -0.0914 0.5289 1.0000
1.750 0.7883 0.00799 0.00264 -0.0908 0.4975 1.0000
2.000 0.8134 0.00829 0.00275 -0.0903 0.4606 1.0000
2.250 0.8380 0.00864 0.00290 -0.0897 0.4234 1.0000
2.500 0.8626 0.00902 0.00308 -0.0891 0.3910 1.0000
2.750 0.8875 0.00937 0.00328 -0.0887 0.3688 1.0000
3.000 0.9129 0.00968 0.00348 -0.0882 0.3525 1.0000
3.250 0.9385 0.00996 0.00368 -0.0879 0.3390 1.0000
3.500 0.9643 0.01020 0.00387 -0.0876 0.3270 1.0000
3.750 0.9900 0.01046 0.00407 -0.0872 0.3161 1.0000
4.000 1.0152 0.01076 0.00430 -0.0868 0.3038 1.0000
4.250 1.0410 0.01099 0.00449 -0.0865 0.2903 1.0000
4.500 1.0664 0.01126 0.00470 -0.0862 0.2742 1.0000
4.750 1.0912 0.01158 0.00493 -0.0857 0.2519 1.0000
5.000 1.1145 0.01203 0.00520 -0.0851 0.2182 1.0000
5.250 1.1367 0.01257 0.00555 -0.0843 0.1933 1.0000
5.750 1.1829 0.01346 0.00632 -0.0830 0.1733 1.0000
6.000 1.2050 0.01397 0.00676 -0.0822 0.1662 1.0000
6.250 1.2289 0.01429 0.00712 -0.0817 0.1619 1.0000
6.500 1.2520 0.01468 0.00752 -0.0810 0.1573 1.0000
6.750 1.2732 0.01521 0.00801 -0.0801 0.1524 1.0000
7.000 1.2959 0.01559 0.00842 -0.0795 0.1482 1.0000
7.250 1.3194 0.01589 0.00877 -0.0789 0.1436 1.0000
7.500 1.3405 0.01637 0.00922 -0.0780 0.1386 1.0000
7.750 1.3614 0.01684 0.00970 -0.0771 0.1343 1.0000
8.000 1.3848 0.01710 0.01001 -0.0766 0.1303 1.0000
8.250 1.4060 0.01750 0.01042 -0.0758 0.1259 1.0000
8.500 1.4241 0.01811 0.01101 -0.0745 0.1214 1.0000
8.750 1.4465 0.01838 0.01136 -0.0738 0.1184 1.0000
9.000 1.4669 0.01875 0.01177 -0.0729 0.1145 1.0000
9.250 1.4843 0.01927 0.01227 -0.0715 0.1104 1.0000
9.500 1.5012 0.01974 0.01278 -0.0699 0.1067 1.0000
9.750 1.5193 0.02014 0.01323 -0.0687 0.1030 1.0000
10.000 1.5351 0.02068 0.01378 -0.0671 0.0994 1.0000
10.250 1.5486 0.02139 0.01450 -0.0653 0.0959 1.0000
10.500 1.5660 0.02188 0.01506 -0.0641 0.0930 1.0000
10.750 1.5814 0.02250 0.01572 -0.0627 0.0895 1.0000
11.000 1.5940 0.02333 0.01655 -0.0611 0.0859 1.0000
11.250 1.6093 0.02400 0.01730 -0.0599 0.0826 1.0000
11.500 1.6235 0.02476 0.01811 -0.0587 0.0790 1.0000
11.750 1.6345 0.02579 0.01913 -0.0572 0.0751 1.0000
12.000 1.6485 0.02661 0.02004 -0.0561 0.0716 1.0000
12.250 1.6595 0.02769 0.02113 -0.0548 0.0665 1.0000
12.500 1.6700 0.02884 0.02230 -0.0535 0.0602 1.0000
12.750 1.6765 0.03035 0.02379 -0.0520 0.0518 1.0000
13.000 1.6756 0.03254 0.02590 -0.0502 0.0380 1.0000
13.250 1.6657 0.03565 0.02891 -0.0481 0.0249 1.0000
13.500 1.6614 0.03842 0.03172 -0.0466 0.0216 1.0000
13.750 1.6602 0.04099 0.03439 -0.0456 0.0203 1.0000
14.000 1.6577 0.04381 0.03732 -0.0447 0.0194 1.0000
14.250 1.6530 0.04699 0.04061 -0.0441 0.0186 1.0000
14.500 1.6481 0.05030 0.04404 -0.0437 0.0181 1.0000
14.750 1.6442 0.05363 0.04750 -0.0436 0.0177 1.0000
15.000 1.6380 0.05738 0.05139 -0.0438 0.0174 1.0000
15.250 1.6301 0.06150 0.05565 -0.0442 0.0171 1.0000
15.500 1.6202 0.06605 0.06034 -0.0449 0.0168 1.0000
15.750 1.6082 0.07108 0.06550 -0.0459 0.0166 1.0000
16.000 1.5940 0.07657 0.07114 -0.0473 0.0164 1.0000
16.250 1.5781 0.08252 0.07724 -0.0490 0.0163 1.0000
16.500 1.5601 0.08902 0.08389 -0.0512 0.0162 1.0000
16.750 1.5413 0.09581 0.09083 -0.0535 0.0161 1.0000
17.000 1.5208 0.10308 0.09825 -0.0563 0.0160 1.0000
17.250 1.5005 0.11045 0.10577 -0.0592 0.0159 1.0000
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Polar data table (+)
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