I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 962 (isa962-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.84 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa962-il-1000000.txt Download as CSV file: xf-isa962-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3172 0.09673 0.09504 -0.0295 1.0000 0.0222
-9.750 -0.3140 0.09353 0.09186 -0.0309 1.0000 0.0231
-9.500 -0.3158 0.08726 0.08561 -0.0384 0.9945 0.0238
-9.250 -0.3020 0.08226 0.08060 -0.0446 0.9782 0.0238
-9.000 -0.1994 0.06668 0.06492 -0.0499 0.9161 0.0244
-8.750 -0.1942 0.06390 0.06210 -0.0506 0.9061 0.0246
-8.500 -0.1898 0.06103 0.05920 -0.0515 0.8974 0.0248
-8.250 -0.1861 0.05796 0.05611 -0.0530 0.8892 0.0251
-8.000 -0.1808 0.05447 0.05259 -0.0557 0.8818 0.0254
-7.750 -0.1717 0.05042 0.04852 -0.0596 0.8751 0.0259
-7.500 -0.1605 0.04579 0.04385 -0.0645 0.8682 0.0267
-7.250 -0.1777 0.05423 0.05211 -0.0743 0.8802 0.0270
-7.000 -0.1333 0.02726 0.02499 -0.0839 0.8568 0.0285
-6.750 -0.1137 0.02508 0.02274 -0.0849 0.8495 0.0288
-6.500 -0.0927 0.02288 0.02046 -0.0861 0.8420 0.0291
-6.250 -0.0711 0.02027 0.01773 -0.0875 0.8335 0.0296
-6.000 -0.0475 0.01319 0.00997 -0.0915 0.8284 0.0328
-5.750 -0.0315 0.00872 0.00509 -0.0926 0.8214 0.0336
-5.500 -0.0071 0.00794 0.00422 -0.0926 0.8131 0.0339
-5.250 0.0180 0.00720 0.00339 -0.0926 0.8034 0.0344
-5.000 0.0432 0.00650 0.00254 -0.0925 0.7931 0.0350
-4.750 0.0688 0.01324 0.00827 -0.0950 0.8014 0.0301
-4.500 0.0960 0.01216 0.00695 -0.0947 0.7895 0.0299
-4.250 0.1235 0.01148 0.00610 -0.0944 0.7768 0.0299
-4.000 0.1511 0.01093 0.00541 -0.0941 0.7637 0.0300
-3.750 0.1788 0.01046 0.00483 -0.0939 0.7500 0.0301
-3.500 0.2065 0.01007 0.00434 -0.0936 0.7354 0.0303
-3.250 0.2342 0.00974 0.00392 -0.0934 0.7210 0.0306
-3.000 0.2620 0.00949 0.00359 -0.0932 0.7072 0.0311
-2.750 0.2898 0.00929 0.00333 -0.0930 0.6943 0.0317
-2.500 0.3176 0.00910 0.00305 -0.0927 0.6803 0.0321
-2.250 0.3456 0.00894 0.00283 -0.0926 0.6670 0.0325
-2.000 0.3738 0.00883 0.00268 -0.0924 0.6553 0.0328
-1.750 0.4014 0.00847 0.00227 -0.0923 0.6448 0.0336
-1.500 0.4294 0.00832 0.00208 -0.0922 0.6332 0.0343
-1.250 0.4576 0.00822 0.00196 -0.0921 0.6216 0.0352
-1.000 0.4857 0.00816 0.00186 -0.0920 0.6097 0.0361
-0.750 0.5136 0.00812 0.00178 -0.0918 0.5966 0.0372
-0.500 0.5415 0.00813 0.00173 -0.0917 0.5812 0.0384
-0.250 0.5693 0.00808 0.00163 -0.0916 0.5648 0.0413
0.000 0.5971 0.00810 0.00160 -0.0915 0.5488 0.0440
0.250 0.6249 0.00810 0.00157 -0.0913 0.5310 0.0526
0.500 0.6521 0.00801 0.00162 -0.0912 0.5101 0.1251
0.750 0.6787 0.00796 0.00171 -0.0911 0.4834 0.2213
1.000 0.7045 0.00792 0.00185 -0.0909 0.4466 0.3657
1.250 0.7324 0.00688 0.00209 -0.0913 0.3978 1.0000
1.500 0.7580 0.00721 0.00223 -0.0909 0.3648 1.0000
1.750 0.7845 0.00745 0.00234 -0.0906 0.3465 1.0000
2.000 0.8112 0.00765 0.00246 -0.0904 0.3334 1.0000
2.500 0.8650 0.00801 0.00268 -0.0900 0.3126 1.0000
2.750 0.8917 0.00820 0.00281 -0.0898 0.3031 1.0000
3.000 0.9189 0.00834 0.00292 -0.0897 0.2951 1.0000
3.250 0.9456 0.00853 0.00305 -0.0895 0.2853 1.0000
3.500 0.9722 0.00873 0.00318 -0.0893 0.2728 1.0000
3.750 0.9987 0.00893 0.00332 -0.0891 0.2580 1.0000
4.000 1.0241 0.00924 0.00349 -0.0888 0.2322 1.0000
4.250 1.0470 0.00980 0.00379 -0.0881 0.1889 1.0000
4.500 1.0715 0.01018 0.00406 -0.0876 0.1734 1.0000
4.750 1.0967 0.01049 0.00432 -0.0873 0.1644 1.0000
5.000 1.1224 0.01073 0.00454 -0.0870 0.1593 1.0000
5.250 1.1475 0.01103 0.00480 -0.0866 0.1539 1.0000
5.500 1.1728 0.01129 0.00505 -0.0863 0.1496 1.0000
5.750 1.1987 0.01148 0.00526 -0.0861 0.1470 1.0000
6.000 1.2241 0.01173 0.00550 -0.0858 0.1434 1.0000
6.250 1.2484 0.01206 0.00579 -0.0853 0.1377 1.0000
6.500 1.2736 0.01229 0.00603 -0.0850 0.1342 1.0000
6.750 1.2989 0.01249 0.00625 -0.0847 0.1311 1.0000
7.000 1.3235 0.01276 0.00650 -0.0844 0.1269 1.0000
7.250 1.3470 0.01312 0.00683 -0.0838 0.1214 1.0000
7.500 1.3721 0.01331 0.00705 -0.0836 0.1190 1.0000
7.750 1.3962 0.01358 0.00731 -0.0831 0.1150 1.0000
8.000 1.4192 0.01394 0.00764 -0.0826 0.1095 1.0000
8.250 1.4430 0.01421 0.00793 -0.0821 0.1061 1.0000
8.500 1.4659 0.01453 0.00824 -0.0815 0.1017 1.0000
8.750 1.4876 0.01494 0.00862 -0.0808 0.0962 1.0000
9.000 1.5102 0.01525 0.00895 -0.0802 0.0926 1.0000
9.250 1.5311 0.01567 0.00934 -0.0793 0.0878 1.0000
9.500 1.5518 0.01608 0.00976 -0.0785 0.0837 1.0000
9.750 1.5722 0.01649 0.01018 -0.0775 0.0798 1.0000
10.000 1.5904 0.01701 0.01067 -0.0763 0.0751 1.0000
10.250 1.6095 0.01742 0.01111 -0.0752 0.0719 1.0000
10.500 1.6248 0.01796 0.01163 -0.0734 0.0674 1.0000
10.750 1.6392 0.01852 0.01220 -0.0715 0.0624 1.0000
11.000 1.6509 0.01927 0.01290 -0.0694 0.0557 1.0000
11.250 1.6606 0.02018 0.01376 -0.0671 0.0464 1.0000
11.500 1.6549 0.02215 0.01554 -0.0630 0.0237 1.0000
11.750 1.6567 0.02374 0.01713 -0.0602 0.0175 1.0000
12.000 1.6642 0.02501 0.01845 -0.0582 0.0161 1.0000
12.250 1.6719 0.02630 0.01981 -0.0564 0.0151 1.0000
12.500 1.6812 0.02751 0.02109 -0.0549 0.0145 1.0000
12.750 1.6888 0.02888 0.02254 -0.0534 0.0140 1.0000
13.000 1.6947 0.03045 0.02419 -0.0519 0.0136 1.0000
13.250 1.6986 0.03225 0.02606 -0.0504 0.0131 1.0000
13.500 1.6996 0.03437 0.02829 -0.0490 0.0126 1.0000
13.750 1.7030 0.03637 0.03037 -0.0478 0.0124 1.0000
14.000 1.7073 0.03834 0.03244 -0.0470 0.0122 1.0000
14.250 1.7097 0.04055 0.03474 -0.0462 0.0119 1.0000
14.500 1.7109 0.04298 0.03726 -0.0455 0.0117 1.0000
14.750 1.7106 0.04565 0.04003 -0.0450 0.0114 1.0000
15.000 1.7084 0.04861 0.04310 -0.0447 0.0112 1.0000
15.250 1.7047 0.05187 0.04645 -0.0446 0.0110 1.0000
15.500 1.6987 0.05558 0.05027 -0.0447 0.0108 1.0000
15.750 1.6903 0.05971 0.05452 -0.0451 0.0107 1.0000
16.000 1.6787 0.06445 0.05938 -0.0458 0.0106 1.0000
16.250 1.6645 0.06973 0.06479 -0.0469 0.0104 1.0000
16.500 1.6470 0.07567 0.07087 -0.0483 0.0103 1.0000
16.750 1.6283 0.08200 0.07735 -0.0501 0.0103 1.0000
17.000 1.6057 0.08922 0.08472 -0.0525 0.0102 1.0000
17.250 1.5831 0.09661 0.09226 -0.0550 0.0102 1.0000
17.500 1.5594 0.10439 0.10019 -0.0579 0.0102 1.0000
17.750 1.5358 0.11230 0.10824 -0.0611 0.0101 1.0000
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Polar data table (+)
Polar graphs
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