I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: I.S.A. 961 (isa961-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.63 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa961-il-1000000.txt Download as CSV file: xf-isa961-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 961
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 -0.2692 0.09930 0.09778 -0.0345 1.0000 0.0131
-11.000 -0.2706 0.09523 0.09372 -0.0351 1.0000 0.0131
-10.750 -0.2789 0.09017 0.08869 -0.0355 1.0000 0.0135
-10.500 -0.2774 0.08752 0.08606 -0.0353 1.0000 0.0137
-10.250 -0.2771 0.08497 0.08352 -0.0349 1.0000 0.0139
-10.000 -0.2748 0.08190 0.08048 -0.0354 0.9995 0.0142
-9.750 -0.2665 0.07760 0.07618 -0.0383 0.9978 0.0145
-9.500 -0.4857 0.02488 0.02207 -0.0901 0.9848 0.0089
-9.250 -0.4600 0.02163 0.01842 -0.0920 0.9807 0.0090
-9.000 -0.4332 0.01947 0.01596 -0.0931 0.9756 0.0091
-8.750 -0.4034 0.01798 0.01423 -0.0942 0.9719 0.0094
-8.500 -0.3759 0.01712 0.01321 -0.0944 0.9648 0.0096
-8.250 -0.3474 0.01584 0.01170 -0.0949 0.9588 0.0099
-8.000 -0.3237 0.01380 0.00939 -0.0947 0.9502 0.0104
-7.750 -0.2963 0.01299 0.00847 -0.0947 0.9428 0.0108
-7.500 -0.2699 0.01239 0.00776 -0.0943 0.9332 0.0112
-7.250 -0.2436 0.01183 0.00708 -0.0938 0.9226 0.0116
-7.000 -0.2175 0.01135 0.00647 -0.0933 0.9116 0.0120
-6.750 -0.1911 0.01092 0.00591 -0.0928 0.9013 0.0125
-6.500 -0.1643 0.01054 0.00544 -0.0924 0.8919 0.0129
-6.250 -0.1376 0.01009 0.00486 -0.0919 0.8830 0.0133
-6.000 -0.1112 0.00946 0.00412 -0.0915 0.8731 0.0144
-5.750 -0.0839 0.00914 0.00373 -0.0912 0.8638 0.0156
-5.500 -0.0565 0.00889 0.00339 -0.0908 0.8548 0.0167
-5.250 -0.0289 0.00858 0.00301 -0.0906 0.8451 0.0179
-5.000 -0.0016 0.00827 0.00264 -0.0902 0.8337 0.0206
-4.750 0.0257 0.00796 0.00229 -0.0899 0.8215 0.0293
-4.500 0.0531 0.00780 0.00228 -0.0897 0.8087 0.0594
-4.250 0.0812 0.00791 0.00234 -0.0895 0.7941 0.0649
-4.000 0.1091 0.00791 0.00227 -0.0893 0.7785 0.0679
-3.750 0.1365 0.00781 0.00210 -0.0890 0.7604 0.0715
-3.500 0.1639 0.00780 0.00201 -0.0888 0.7402 0.0743
-3.250 0.1914 0.00782 0.00194 -0.0886 0.7208 0.0771
-3.000 0.2190 0.00784 0.00187 -0.0884 0.7026 0.0787
-2.750 0.2465 0.00779 0.00174 -0.0882 0.6837 0.0809
-2.500 0.2737 0.00772 0.00159 -0.0879 0.6631 0.0853
-2.250 0.3011 0.00771 0.00149 -0.0877 0.6416 0.0874
-2.000 0.3283 0.00775 0.00142 -0.0875 0.6167 0.0894
-1.750 0.3549 0.00786 0.00137 -0.0872 0.5797 0.0912
-1.500 0.3807 0.00807 0.00136 -0.0867 0.5285 0.0929
-1.250 0.4065 0.00828 0.00137 -0.0863 0.4779 0.0978
-1.000 0.4327 0.00845 0.00141 -0.0860 0.4389 0.1060
-0.750 0.4592 0.00856 0.00149 -0.0858 0.4073 0.1377
-0.500 0.4858 0.00870 0.00155 -0.0856 0.3785 0.1564
-0.250 0.5121 0.00891 0.00162 -0.0853 0.3422 0.1693
0.000 0.5382 0.00913 0.00170 -0.0851 0.3055 0.1812
0.250 0.5641 0.00936 0.00181 -0.0848 0.2696 0.1975
0.500 0.5901 0.00953 0.00194 -0.0845 0.2410 0.2325
0.750 0.6163 0.00957 0.00207 -0.0844 0.2209 0.3067
1.000 0.6316 0.00829 0.00229 -0.0822 0.2014 0.9028
1.500 0.6970 0.00908 0.00272 -0.0848 0.1181 1.0000
1.750 0.7236 0.00925 0.00285 -0.0845 0.1153 1.0000
2.000 0.7500 0.00942 0.00297 -0.0843 0.1127 1.0000
2.250 0.7764 0.00960 0.00311 -0.0840 0.1095 1.0000
2.500 0.8028 0.00978 0.00326 -0.0838 0.1065 1.0000
2.750 0.8296 0.00991 0.00338 -0.0836 0.1051 1.0000
3.000 0.8564 0.01004 0.00349 -0.0835 0.1036 1.0000
3.250 0.8829 0.01019 0.00362 -0.0833 0.1009 1.0000
3.500 0.9089 0.01040 0.00379 -0.0831 0.0965 1.0000
3.750 0.9351 0.01059 0.00395 -0.0828 0.0925 1.0000
4.000 0.9617 0.01073 0.00407 -0.0827 0.0906 1.0000
4.250 0.9879 0.01090 0.00423 -0.0825 0.0844 1.0000
4.500 1.0114 0.01137 0.00452 -0.0819 0.0603 1.0000
4.750 1.0364 0.01167 0.00479 -0.0815 0.0571 1.0000
5.000 1.0617 0.01192 0.00504 -0.0812 0.0546 1.0000
5.250 1.0870 0.01217 0.00530 -0.0809 0.0532 1.0000
5.500 1.1122 0.01242 0.00557 -0.0805 0.0518 1.0000
5.750 1.1372 0.01267 0.00584 -0.0802 0.0508 1.0000
6.000 1.1621 0.01293 0.00613 -0.0799 0.0501 1.0000
6.250 1.1867 0.01321 0.00644 -0.0795 0.0491 1.0000
6.500 1.2110 0.01350 0.00677 -0.0791 0.0477 1.0000
6.750 1.2346 0.01386 0.00714 -0.0786 0.0457 1.0000
7.000 1.2575 0.01427 0.00758 -0.0779 0.0430 1.0000
7.250 1.2813 0.01457 0.00790 -0.0775 0.0409 1.0000
7.500 1.3070 0.01467 0.00797 -0.0774 0.0375 1.0000
7.750 1.3255 0.01542 0.00852 -0.0761 0.0155 1.0000
8.000 1.3455 0.01603 0.00917 -0.0750 0.0129 1.0000
8.250 1.3662 0.01656 0.00976 -0.0740 0.0116 1.0000
8.500 1.3866 0.01706 0.01031 -0.0730 0.0110 1.0000
8.750 1.4059 0.01763 0.01094 -0.0719 0.0103 1.0000
9.000 1.4236 0.01829 0.01166 -0.0705 0.0097 1.0000
9.250 1.4380 0.01916 0.01261 -0.0686 0.0090 1.0000
9.500 1.4500 0.02005 0.01361 -0.0662 0.0085 1.0000
9.750 1.4645 0.02064 0.01425 -0.0643 0.0082 1.0000
10.000 1.4771 0.02135 0.01502 -0.0622 0.0079 1.0000
10.250 1.4885 0.02216 0.01591 -0.0600 0.0076 1.0000
10.500 1.4989 0.02306 0.01688 -0.0578 0.0073 1.0000
10.750 1.5081 0.02407 0.01796 -0.0556 0.0071 1.0000
11.000 1.5160 0.02522 0.01918 -0.0535 0.0068 1.0000
11.250 1.5213 0.02660 0.02066 -0.0512 0.0066 1.0000
11.500 1.5220 0.02841 0.02258 -0.0488 0.0064 1.0000
11.750 1.5144 0.03102 0.02532 -0.0460 0.0062 1.0000
12.000 1.5056 0.03394 0.02838 -0.0437 0.0061 1.0000
12.250 1.5112 0.03573 0.03026 -0.0427 0.0060 1.0000
12.500 1.5139 0.03789 0.03251 -0.0417 0.0059 1.0000
12.750 1.5149 0.04031 0.03504 -0.0409 0.0059 1.0000
13.000 1.5150 0.04297 0.03779 -0.0404 0.0058 1.0000
13.250 1.5140 0.04589 0.04081 -0.0401 0.0056 1.0000
13.500 1.5108 0.04917 0.04420 -0.0400 0.0055 1.0000
13.750 1.5068 0.05269 0.04783 -0.0402 0.0054 1.0000
14.000 1.5017 0.05654 0.05179 -0.0407 0.0053 1.0000
14.250 1.4950 0.06074 0.05610 -0.0414 0.0052 1.0000
14.500 1.4875 0.06523 0.06071 -0.0425 0.0051 1.0000
14.750 1.4788 0.07006 0.06565 -0.0437 0.0051 1.0000
15.000 1.4690 0.07517 0.07087 -0.0452 0.0050 1.0000
15.250 1.4576 0.08060 0.07641 -0.0469 0.0050 1.0000
15.500 1.4459 0.08620 0.08212 -0.0487 0.0049 1.0000
15.750 1.4335 0.09195 0.08798 -0.0506 0.0049 1.0000
16.000 1.4214 0.09769 0.09382 -0.0526 0.0048 1.0000
|
Polar data table (+)
Polar graphs
<< Back to I.S.A. 961 (isa961-il)