I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 960 (isa960-il) Reynolds number: 200,000 Max Cl/Cd: 53.68 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa960-il-200000-n5.txt Download as CSV file: xf-isa960-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3406 0.09873 0.09536 -0.0340 1.0000 0.0167
-10.000 -0.3403 0.09518 0.09185 -0.0350 1.0000 0.0166
-9.750 -0.3418 0.09168 0.08841 -0.0357 1.0000 0.0165
-9.500 -0.3387 0.08737 0.08414 -0.0386 0.9931 0.0164
-9.250 -0.3324 0.08224 0.07902 -0.0432 0.9755 0.0164
-9.000 -0.3269 0.07681 0.07361 -0.0487 0.9540 0.0164
-8.750 -0.3163 0.06993 0.06671 -0.0574 0.9384 0.0165
-8.500 -0.3052 0.06091 0.05762 -0.0688 0.9259 0.0167
-8.250 -0.3116 0.02946 0.02480 -0.0964 0.9205 0.0169
-8.000 -0.2867 0.02543 0.02001 -0.0984 0.9096 0.0180
-7.750 -0.2608 0.02338 0.01771 -0.0992 0.8980 0.0190
-7.500 -0.2344 0.02185 0.01590 -0.0995 0.8853 0.0200
-7.250 -0.2086 0.02042 0.01412 -0.0994 0.8697 0.0213
-7.000 -0.1829 0.01926 0.01262 -0.0991 0.8505 0.0231
-6.750 -0.1566 0.01850 0.01153 -0.0986 0.8289 0.0248
-6.500 -0.1321 0.01704 0.00983 -0.0981 0.7993 0.0271
-6.250 -0.1072 0.01634 0.00879 -0.0973 0.7594 0.0294
-6.000 -0.0823 0.01585 0.00790 -0.0964 0.7221 0.0325
-5.750 -0.0571 0.01527 0.00701 -0.0958 0.6900 0.0354
-5.500 -0.0312 0.01482 0.00636 -0.0953 0.6575 0.0394
-5.250 -0.0054 0.01452 0.00579 -0.0947 0.6138 0.0440
-5.000 0.0188 0.01449 0.00545 -0.0939 0.5412 0.0501
-4.750 0.0436 0.01462 0.00526 -0.0933 0.4801 0.0608
-4.500 0.0627 0.01559 0.00525 -0.0920 0.2593 0.0711
-4.250 0.0886 0.01566 0.00506 -0.0916 0.2233 0.0804
-4.000 0.1158 0.01561 0.00485 -0.0915 0.2141 0.0894
-3.750 0.1429 0.01553 0.00472 -0.0913 0.2066 0.0968
-3.500 0.1702 0.01547 0.00455 -0.0912 0.2007 0.1024
-3.250 0.1975 0.01540 0.00443 -0.0910 0.1940 0.1072
-3.000 0.2248 0.01537 0.00432 -0.0909 0.1871 0.1132
-2.500 0.2781 0.01550 0.00418 -0.0904 0.1297 0.1262
-2.250 0.3051 0.01551 0.00413 -0.0903 0.1265 0.1344
-2.000 0.3322 0.01553 0.00409 -0.0901 0.1246 0.1434
-1.750 0.3591 0.01549 0.00405 -0.0899 0.1233 0.1516
-1.250 0.4129 0.01549 0.00400 -0.0896 0.1217 0.1715
-1.000 0.4398 0.01549 0.00402 -0.0894 0.1212 0.1827
-0.750 0.4665 0.01551 0.00406 -0.0893 0.1209 0.1964
-0.500 0.4931 0.01553 0.00414 -0.0891 0.1205 0.2172
-0.250 0.5196 0.01552 0.00424 -0.0890 0.1202 0.2595
0.000 0.5457 0.01542 0.00435 -0.0888 0.1200 0.3334
0.500 0.5978 0.01421 0.00462 -0.0879 0.1196 1.0000
0.750 0.6240 0.01442 0.00475 -0.0876 0.1195 1.0000
1.000 0.6500 0.01463 0.00490 -0.0873 0.1194 1.0000
1.250 0.6759 0.01486 0.00507 -0.0870 0.1192 1.0000
1.500 0.7016 0.01509 0.00526 -0.0867 0.1190 1.0000
1.750 0.7273 0.01533 0.00547 -0.0864 0.1188 1.0000
2.000 0.7528 0.01559 0.00569 -0.0861 0.1186 1.0000
2.250 0.7781 0.01585 0.00593 -0.0857 0.1184 1.0000
2.500 0.8033 0.01613 0.00619 -0.0854 0.1183 1.0000
2.750 0.8283 0.01641 0.00647 -0.0850 0.1182 1.0000
3.000 0.8532 0.01670 0.00675 -0.0846 0.1181 1.0000
3.250 0.8779 0.01700 0.00705 -0.0842 0.1182 1.0000
3.500 0.9023 0.01731 0.00738 -0.0838 0.1183 1.0000
3.750 0.9266 0.01763 0.00771 -0.0833 0.1183 1.0000
4.000 0.9506 0.01797 0.00806 -0.0828 0.1185 1.0000
4.250 0.9743 0.01832 0.00845 -0.0823 0.1186 1.0000
4.500 0.9977 0.01868 0.00883 -0.0817 0.1187 1.0000
4.750 1.0208 0.01906 0.00924 -0.0811 0.1189 1.0000
5.000 1.0436 0.01945 0.00967 -0.0805 0.1190 1.0000
5.250 1.0660 0.01986 0.01013 -0.0798 0.1192 1.0000
5.500 1.0882 0.02029 0.01059 -0.0791 0.1193 1.0000
5.750 1.1099 0.02074 0.01108 -0.0783 0.1195 1.0000
6.000 1.1313 0.02121 0.01160 -0.0775 0.1194 1.0000
6.250 1.1519 0.02173 0.01219 -0.0766 0.1188 1.0000
6.500 1.1718 0.02232 0.01283 -0.0756 0.1177 1.0000
6.750 1.1896 0.02312 0.01363 -0.0744 0.1152 1.0000
7.000 1.2057 0.02458 0.01494 -0.0732 0.1115 1.0000
7.250 1.2243 0.02496 0.01549 -0.0720 0.1082 1.0000
7.500 1.2425 0.02565 0.01627 -0.0709 0.1053 1.0000
7.750 1.2614 0.02674 0.01729 -0.0700 0.1023 1.0000
8.000 1.2766 0.02724 0.01795 -0.0684 0.0999 1.0000
8.250 1.2902 0.02762 0.01854 -0.0664 0.0965 1.0000
8.500 1.3031 0.02838 0.01935 -0.0647 0.0925 1.0000
8.750 1.3210 0.02825 0.01960 -0.0635 0.0858 1.0000
9.000 1.3495 0.02771 0.01909 -0.0639 0.0423 1.0000
9.250 1.3515 0.02957 0.02074 -0.0612 0.0220 1.0000
9.500 1.3597 0.03100 0.02216 -0.0592 0.0182 1.0000
9.750 1.3698 0.03227 0.02356 -0.0576 0.0167 1.0000
10.000 1.3783 0.03369 0.02511 -0.0560 0.0153 1.0000
10.250 1.3848 0.03533 0.02688 -0.0544 0.0141 1.0000
10.500 1.3885 0.03725 0.02897 -0.0527 0.0132 1.0000
10.750 1.3900 0.03944 0.03133 -0.0511 0.0126 1.0000
11.000 1.3936 0.04148 0.03355 -0.0499 0.0123 1.0000
11.250 1.3952 0.04380 0.03605 -0.0489 0.0120 1.0000
11.500 1.3948 0.04644 0.03890 -0.0480 0.0117 1.0000
11.750 1.3928 0.04935 0.04199 -0.0473 0.0114 1.0000
12.000 1.3893 0.05256 0.04536 -0.0470 0.0111 1.0000
12.250 1.3843 0.05605 0.04901 -0.0468 0.0108 1.0000
12.500 1.3780 0.05983 0.05295 -0.0469 0.0105 1.0000
12.750 1.3707 0.06390 0.05717 -0.0473 0.0102 1.0000
13.000 1.3624 0.06830 0.06171 -0.0480 0.0100 1.0000
13.250 1.3532 0.07303 0.06659 -0.0490 0.0098 1.0000
13.500 1.3434 0.07803 0.07172 -0.0503 0.0096 1.0000
13.750 1.3330 0.08328 0.07708 -0.0518 0.0094 1.0000
14.000 1.3223 0.08865 0.08258 -0.0534 0.0093 1.0000
14.250 1.3119 0.09405 0.08809 -0.0551 0.0092 1.0000
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Polar data table (+)
Polar graphs
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