I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 960 (isa960-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.52 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa960-il-1000000.txt Download as CSV file: xf-isa960-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2532 0.09849 0.09604 -0.0379 0.7270 0.0150
-11.000 -0.2579 0.09250 0.09010 -0.0405 0.7354 0.0162
-10.750 -0.6093 0.02675 0.02405 -0.0895 0.9851 0.0095
-10.500 -0.5932 0.02055 0.01716 -0.0927 0.9750 0.0101
-10.250 -0.5616 0.01952 0.01602 -0.0942 0.9634 0.0104
-10.000 -0.5295 0.01877 0.01515 -0.0955 0.9458 0.0108
-9.750 -0.5026 0.01803 0.01424 -0.0956 0.9282 0.0112
-9.250 -0.4542 0.01631 0.01209 -0.0946 0.8982 0.0120
-9.000 -0.4295 0.01558 0.01116 -0.0941 0.8831 0.0123
-8.750 -0.4039 0.01504 0.01044 -0.0936 0.8658 0.0126
-8.500 -0.3808 0.01354 0.00867 -0.0931 0.8436 0.0133
-8.250 -0.3560 0.01321 0.00812 -0.0923 0.7945 0.0138
-8.000 -0.3317 0.01311 0.00770 -0.0915 0.7309 0.0144
-7.750 -0.3056 0.01290 0.00727 -0.0911 0.6928 0.0151
-7.500 -0.2793 0.01271 0.00683 -0.0907 0.6483 0.0158
-7.250 -0.2554 0.01314 0.00667 -0.0900 0.4982 0.0163
-7.000 -0.2348 0.01337 0.00595 -0.0892 0.2218 0.0175
-6.750 -0.2073 0.01321 0.00569 -0.0891 0.2023 0.0185
-6.500 -0.1797 0.01301 0.00537 -0.0889 0.1847 0.0195
-6.250 -0.1525 0.01298 0.00513 -0.0887 0.1171 0.0205
-6.000 -0.1250 0.01258 0.00463 -0.0886 0.1133 0.0217
-5.750 -0.0974 0.01223 0.00424 -0.0885 0.1107 0.0234
-5.500 -0.0694 0.01207 0.00403 -0.0884 0.1088 0.0251
-5.250 -0.0413 0.01193 0.00384 -0.0883 0.1075 0.0264
-5.000 -0.0135 0.01162 0.00346 -0.0882 0.1068 0.0283
-4.750 0.0144 0.01138 0.00318 -0.0881 0.1062 0.0309
-4.500 0.0424 0.01124 0.00299 -0.0880 0.1060 0.0331
-4.250 0.0705 0.01113 0.00283 -0.0879 0.1059 0.0354
-4.000 0.0985 0.01097 0.00267 -0.0878 0.1058 0.0416
-3.750 0.1263 0.01084 0.00267 -0.0878 0.1058 0.0667
-3.500 0.1545 0.01090 0.00271 -0.0877 0.1057 0.0745
-3.250 0.1825 0.01091 0.00270 -0.0877 0.1056 0.0793
-3.000 0.2105 0.01090 0.00267 -0.0877 0.1054 0.0840
-2.750 0.2385 0.01092 0.00266 -0.0876 0.1052 0.0869
-2.500 0.2664 0.01096 0.00267 -0.0876 0.1052 0.0889
-2.250 0.2943 0.01096 0.00267 -0.0875 0.1051 0.0933
-2.000 0.3221 0.01099 0.00269 -0.0875 0.1051 0.0973
-1.750 0.3499 0.01103 0.00273 -0.0874 0.1051 0.1013
-1.500 0.3777 0.01107 0.00279 -0.0873 0.1051 0.1097
-1.250 0.4053 0.01111 0.00288 -0.0873 0.1052 0.1267
-1.000 0.4329 0.01118 0.00298 -0.0872 0.1052 0.1430
-0.750 0.4604 0.01126 0.00308 -0.0872 0.1052 0.1541
-0.500 0.4879 0.01137 0.00318 -0.0871 0.1052 0.1611
-0.250 0.5153 0.01146 0.00329 -0.0870 0.1053 0.1704
0.000 0.5425 0.01157 0.00341 -0.0869 0.1053 0.1798
0.250 0.5697 0.01167 0.00355 -0.0868 0.1054 0.1947
0.500 0.5966 0.01172 0.00372 -0.0868 0.1054 0.2408
0.750 0.6234 0.01172 0.00391 -0.0867 0.1055 0.3186
1.000 0.6408 0.01042 0.00420 -0.0849 0.1055 0.9082
1.250 0.6735 0.01055 0.00438 -0.0860 0.1056 1.0000
1.500 0.6999 0.01079 0.00458 -0.0858 0.1056 1.0000
1.750 0.7262 0.01103 0.00480 -0.0855 0.1057 1.0000
2.000 0.7523 0.01129 0.00503 -0.0853 0.1057 1.0000
2.250 0.7782 0.01156 0.00528 -0.0850 0.1058 1.0000
2.500 0.8040 0.01184 0.00555 -0.0847 0.1058 1.0000
2.750 0.8296 0.01214 0.00583 -0.0845 0.1059 1.0000
3.000 0.8551 0.01245 0.00612 -0.0841 0.1059 1.0000
3.250 0.8817 0.01261 0.00627 -0.0840 0.1056 1.0000
3.500 0.9083 0.01276 0.00642 -0.0839 0.1051 1.0000
3.750 0.9341 0.01301 0.00666 -0.0837 0.1049 1.0000
4.000 0.9594 0.01330 0.00695 -0.0834 0.1048 1.0000
4.250 0.9846 0.01361 0.00727 -0.0831 0.1048 1.0000
4.500 1.0097 0.01391 0.00757 -0.0827 0.1047 1.0000
4.750 1.0357 0.01408 0.00775 -0.0826 0.1035 1.0000
5.000 1.0613 0.01429 0.00796 -0.0824 0.1016 1.0000
5.250 1.0861 0.01458 0.00826 -0.0821 0.1003 1.0000
5.500 1.1105 0.01490 0.00858 -0.0817 0.0990 1.0000
5.750 1.1341 0.01531 0.00899 -0.0812 0.0980 1.0000
6.000 1.1546 0.01613 0.00977 -0.0803 0.0963 1.0000
6.250 1.1785 0.01645 0.01014 -0.0799 0.0948 1.0000
6.500 1.2064 0.01620 0.00994 -0.0801 0.0935 1.0000
6.750 1.2339 0.01609 0.00987 -0.0802 0.0915 1.0000
7.000 1.2632 0.01583 0.00964 -0.0807 0.0884 1.0000
7.250 1.2943 0.01549 0.00925 -0.0815 0.0844 1.0000
7.500 1.3307 0.01470 0.00810 -0.0831 0.0446 1.0000
7.750 1.3439 0.01593 0.00915 -0.0811 0.0174 1.0000
8.000 1.3632 0.01659 0.00982 -0.0799 0.0144 1.0000
8.250 1.3835 0.01712 0.01040 -0.0789 0.0134 1.0000
8.500 1.4031 0.01767 0.01101 -0.0778 0.0125 1.0000
8.750 1.4209 0.01834 0.01172 -0.0765 0.0115 1.0000
9.000 1.4353 0.01924 0.01269 -0.0746 0.0106 1.0000
9.250 1.4517 0.01987 0.01339 -0.0731 0.0103 1.0000
9.500 1.4660 0.02048 0.01406 -0.0711 0.0099 1.0000
9.750 1.4789 0.02119 0.01483 -0.0690 0.0095 1.0000
10.000 1.4910 0.02198 0.01568 -0.0669 0.0091 1.0000
10.250 1.5023 0.02284 0.01661 -0.0649 0.0088 1.0000
10.500 1.5121 0.02384 0.01768 -0.0628 0.0085 1.0000
10.750 1.5189 0.02510 0.01902 -0.0605 0.0082 1.0000
11.000 1.5176 0.02703 0.02108 -0.0576 0.0078 1.0000
11.250 1.5210 0.02870 0.02286 -0.0555 0.0076 1.0000
11.500 1.5310 0.02990 0.02412 -0.0542 0.0075 1.0000
11.750 1.5391 0.03130 0.02560 -0.0529 0.0073 1.0000
12.000 1.5443 0.03301 0.02740 -0.0515 0.0071 1.0000
12.250 1.5482 0.03492 0.02940 -0.0502 0.0069 1.0000
12.500 1.5512 0.03701 0.03159 -0.0491 0.0068 1.0000
12.750 1.5527 0.03935 0.03402 -0.0482 0.0066 1.0000
13.000 1.5532 0.04189 0.03667 -0.0475 0.0065 1.0000
13.250 1.5529 0.04463 0.03950 -0.0471 0.0063 1.0000
13.500 1.5506 0.04765 0.04261 -0.0467 0.0062 1.0000
13.750 1.5470 0.05093 0.04599 -0.0465 0.0061 1.0000
14.000 1.5417 0.05455 0.04971 -0.0466 0.0060 1.0000
14.250 1.5343 0.05860 0.05387 -0.0469 0.0059 1.0000
14.500 1.5246 0.06315 0.05853 -0.0476 0.0059 1.0000
14.750 1.5134 0.06813 0.06362 -0.0486 0.0058 1.0000
15.000 1.5002 0.07354 0.06915 -0.0499 0.0057 1.0000
15.250 1.4858 0.07929 0.07502 -0.0515 0.0057 1.0000
15.500 1.4697 0.08543 0.08128 -0.0532 0.0056 1.0000
15.750 1.4534 0.09167 0.08765 -0.0551 0.0056 1.0000
16.000 1.4365 0.09806 0.09415 -0.0571 0.0055 1.0000
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Polar data table (+)
Polar graphs
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