I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 960 (isa960-il) Reynolds number: 50,000 Max Cl/Cd: 38.04 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa960-il-50000-n5.txt Download as CSV file: xf-isa960-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3322 0.09744 0.09111 -0.0340 1.0000 0.0603
-8.750 -0.3388 0.09489 0.08868 -0.0332 1.0000 0.0590
-8.500 -0.3474 0.09231 0.08624 -0.0326 1.0000 0.0577
-8.250 -0.3559 0.08942 0.08347 -0.0328 1.0000 0.0565
-7.750 -0.3749 0.08178 0.07598 -0.0368 1.0000 0.0533
-7.500 -0.3765 0.07871 0.07294 -0.0368 1.0000 0.0531
-7.250 -0.3767 0.07513 0.06938 -0.0379 1.0000 0.0531
-7.000 -0.3741 0.07079 0.06500 -0.0401 1.0000 0.0534
-6.750 -0.3701 0.06972 0.06401 -0.0378 1.0000 0.0555
-6.500 -0.3612 0.06656 0.06080 -0.0391 0.9994 0.0570
-6.250 -0.3273 0.06037 0.05437 -0.0471 0.9927 0.0582
-6.000 -0.2905 0.05367 0.04730 -0.0551 0.9863 0.0592
-5.750 -0.2500 0.04555 0.03837 -0.0637 0.9799 0.0634
-5.500 -0.2149 0.04298 0.03557 -0.0672 0.9736 0.0676
-5.250 -0.1764 0.03862 0.03055 -0.0715 0.9670 0.0727
-5.000 -0.1371 0.03588 0.02731 -0.0751 0.9592 0.0808
-4.750 -0.0917 0.03231 0.02284 -0.0791 0.9517 0.0896
-4.500 -0.0523 0.03111 0.02138 -0.0816 0.9407 0.1024
-4.250 -0.0090 0.02940 0.01924 -0.0844 0.9310 0.1164
-4.000 0.0359 0.02845 0.01813 -0.0875 0.9211 0.1354
-3.750 0.0735 0.02793 0.01736 -0.0895 0.9094 0.1608
-3.500 0.1136 0.02707 0.01636 -0.0915 0.8976 0.1794
-3.250 0.1537 0.02603 0.01499 -0.0930 0.8840 0.1905
-3.000 0.1906 0.02512 0.01392 -0.0939 0.8689 0.1989
-2.750 0.2248 0.02439 0.01301 -0.0943 0.8538 0.2095
-2.500 0.2560 0.02384 0.01236 -0.0944 0.8405 0.2236
-2.250 0.2863 0.02333 0.01176 -0.0943 0.8281 0.2387
-2.000 0.3162 0.02280 0.01122 -0.0942 0.8157 0.2558
-1.750 0.3435 0.02235 0.01080 -0.0938 0.8023 0.2781
-1.500 0.3704 0.02188 0.01044 -0.0934 0.7892 0.3144
-1.000 0.4268 0.01952 0.00975 -0.0921 0.7641 1.0000
-0.750 0.4553 0.01952 0.00943 -0.0916 0.7499 1.0000
-0.500 0.4831 0.01953 0.00916 -0.0911 0.7348 1.0000
-0.250 0.5105 0.01957 0.00896 -0.0905 0.7197 1.0000
0.000 0.5374 0.01966 0.00884 -0.0900 0.7053 1.0000
0.250 0.5633 0.01978 0.00879 -0.0893 0.6897 1.0000
0.500 0.5883 0.01993 0.00881 -0.0885 0.6729 1.0000
0.750 0.6127 0.02010 0.00886 -0.0877 0.6546 1.0000
1.000 0.6370 0.02026 0.00890 -0.0868 0.6343 1.0000
1.250 0.6608 0.02044 0.00898 -0.0859 0.6117 1.0000
1.500 0.6849 0.02063 0.00903 -0.0850 0.5882 1.0000
1.750 0.7095 0.02083 0.00910 -0.0842 0.5663 1.0000
2.000 0.7341 0.02106 0.00922 -0.0834 0.5457 1.0000
2.250 0.7585 0.02131 0.00934 -0.0826 0.5247 1.0000
2.500 0.7823 0.02163 0.00953 -0.0818 0.5029 1.0000
2.750 0.8057 0.02198 0.00981 -0.0810 0.4819 1.0000
3.000 0.8290 0.02236 0.01012 -0.0803 0.4628 1.0000
3.250 0.8519 0.02277 0.01048 -0.0795 0.4440 1.0000
3.500 0.8746 0.02320 0.01089 -0.0787 0.4247 1.0000
3.750 0.8968 0.02367 0.01136 -0.0779 0.4055 1.0000
4.000 0.9186 0.02417 0.01184 -0.0770 0.3869 1.0000
4.250 0.9400 0.02471 0.01235 -0.0761 0.3694 1.0000
4.500 0.9610 0.02528 0.01293 -0.0752 0.3536 1.0000
4.750 0.9815 0.02588 0.01353 -0.0742 0.3390 1.0000
5.000 1.0011 0.02655 0.01417 -0.0732 0.3240 1.0000
5.250 1.0201 0.02727 0.01486 -0.0721 0.3102 1.0000
5.500 1.0393 0.02799 0.01564 -0.0710 0.2992 1.0000
5.750 1.0585 0.02873 0.01642 -0.0699 0.2907 1.0000
6.000 1.0776 0.02950 0.01725 -0.0689 0.2830 1.0000
6.250 1.0958 0.03033 0.01813 -0.0678 0.2745 1.0000
6.500 1.1130 0.03123 0.01910 -0.0665 0.2656 1.0000
6.750 1.1315 0.03210 0.02008 -0.0655 0.2584 1.0000
7.000 1.1496 0.03301 0.02110 -0.0644 0.2515 1.0000
7.250 1.1681 0.03395 0.02215 -0.0633 0.2451 1.0000
7.500 1.1871 0.03491 0.02327 -0.0624 0.2385 1.0000
7.750 1.2067 0.03590 0.02438 -0.0615 0.2330 1.0000
8.000 1.2271 0.03691 0.02565 -0.0607 0.2269 1.0000
8.250 1.2483 0.03795 0.02685 -0.0601 0.2217 1.0000
8.500 1.2705 0.03903 0.02810 -0.0596 0.2171 1.0000
8.750 1.2910 0.04022 0.02960 -0.0589 0.2122 1.0000
9.000 1.3120 0.04143 0.03105 -0.0583 0.2081 1.0000
9.250 1.3272 0.04256 0.03238 -0.0570 0.2027 1.0000
9.500 1.3297 0.04397 0.03416 -0.0545 0.1948 1.0000
9.750 1.3305 0.04530 0.03566 -0.0520 0.1866 1.0000
10.000 1.3297 0.04694 0.03761 -0.0497 0.1777 1.0000
10.250 1.3281 0.04877 0.03972 -0.0479 0.1684 1.0000
10.500 1.3235 0.05078 0.04188 -0.0463 0.1583 1.0000
10.750 1.3171 0.05312 0.04418 -0.0451 0.1490 1.0000
11.000 1.3098 0.05589 0.04677 -0.0442 0.1411 1.0000
11.250 1.3035 0.05899 0.04971 -0.0434 0.1334 1.0000
11.500 1.2971 0.06237 0.05299 -0.0426 0.1243 1.0000
11.750 1.2912 0.06594 0.05661 -0.0419 0.1152 1.0000
12.000 1.2847 0.06974 0.06059 -0.0415 0.1071 1.0000
12.250 1.2736 0.07422 0.06534 -0.0419 0.0992 1.0000
12.500 1.2595 0.07948 0.07099 -0.0432 0.0918 1.0000
12.750 1.2447 0.08655 0.07920 -0.0460 0.0742 1.0000
13.000 1.2346 0.09166 0.08438 -0.0479 0.0627 1.0000
13.250 1.2238 0.09704 0.08968 -0.0503 0.0580 1.0000
13.500 1.2121 0.10288 0.09551 -0.0527 0.0548 1.0000
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Polar data table (+)
Polar graphs
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