I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 960 (isa960-il) Reynolds number: 500,000 Max Cl/Cd: 72.08 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa960-il-500000-n5.txt Download as CSV file: xf-isa960-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3620 0.11454 0.11161 -0.0282 0.7899 0.0075
-11.500 -0.3606 0.11071 0.10751 -0.0294 0.7339 0.0075
-10.500 -0.5373 0.02897 0.02566 -0.0967 0.9147 0.0075
-10.250 -0.5184 0.02529 0.02156 -0.0983 0.9025 0.0077
-10.000 -0.4972 0.02306 0.01900 -0.0988 0.8912 0.0079
-9.750 -0.4748 0.02133 0.01697 -0.0989 0.8797 0.0082
-9.500 -0.4513 0.01998 0.01536 -0.0988 0.8676 0.0087
-9.250 -0.4272 0.01884 0.01394 -0.0986 0.8526 0.0090
-9.000 -0.4032 0.01778 0.01261 -0.0982 0.8295 0.0094
-8.750 -0.3806 0.01679 0.01126 -0.0975 0.7816 0.0099
-8.500 -0.3573 0.01630 0.01041 -0.0967 0.7301 0.0104
-8.250 -0.3325 0.01585 0.00966 -0.0962 0.6941 0.0109
-8.000 -0.3072 0.01540 0.00894 -0.0957 0.6526 0.0115
-7.750 -0.2909 0.01645 0.00852 -0.0942 0.2545 0.0121
-7.500 -0.2646 0.01611 0.00791 -0.0939 0.2091 0.0127
-7.250 -0.2378 0.01559 0.00725 -0.0938 0.1959 0.0138
-7.000 -0.2106 0.01534 0.00689 -0.0937 0.1776 0.0151
-6.750 -0.1837 0.01518 0.00652 -0.0935 0.1179 0.0164
-6.250 -0.1288 0.01447 0.00561 -0.0933 0.1112 0.0192
-6.000 -0.1012 0.01424 0.00532 -0.0932 0.1101 0.0213
-5.750 -0.0734 0.01405 0.00504 -0.0931 0.1091 0.0235
-5.500 -0.0456 0.01391 0.00481 -0.0930 0.1082 0.0247
-5.250 -0.0181 0.01354 0.00436 -0.0929 0.1073 0.0277
-5.000 0.0096 0.01332 0.00408 -0.0928 0.1066 0.0304
-4.750 0.0373 0.01318 0.00384 -0.0927 0.1058 0.0326
-4.500 0.0651 0.01305 0.00365 -0.0926 0.1052 0.0351
-4.250 0.0928 0.01290 0.00348 -0.0924 0.1045 0.0400
-4.000 0.1203 0.01275 0.00343 -0.0924 0.1040 0.0574
-3.750 0.1481 0.01275 0.00340 -0.0923 0.1035 0.0684
-3.500 0.1758 0.01278 0.00338 -0.0922 0.1030 0.0737
-3.250 0.2035 0.01282 0.00337 -0.0920 0.1027 0.0767
-3.000 0.2310 0.01279 0.00332 -0.0920 0.1024 0.0811
-2.750 0.2586 0.01281 0.00332 -0.0919 0.1021 0.0840
-2.500 0.2860 0.01285 0.00332 -0.0917 0.1018 0.0867
-2.250 0.3135 0.01290 0.00334 -0.0916 0.1016 0.0892
-2.000 0.3409 0.01295 0.00336 -0.0915 0.1016 0.0915
-1.750 0.3682 0.01300 0.00340 -0.0914 0.1015 0.0952
-1.500 0.3955 0.01306 0.00345 -0.0913 0.1014 0.0997
-1.250 0.4227 0.01311 0.00353 -0.0912 0.1012 0.1101
-1.000 0.4499 0.01318 0.00363 -0.0911 0.1011 0.1286
-0.750 0.4770 0.01328 0.00373 -0.0910 0.1009 0.1417
-0.500 0.5040 0.01338 0.00384 -0.0909 0.1008 0.1494
-0.250 0.5309 0.01351 0.00395 -0.0907 0.1008 0.1568
0.000 0.5576 0.01364 0.00408 -0.0906 0.1007 0.1634
0.250 0.5843 0.01377 0.00423 -0.0904 0.1007 0.1711
0.500 0.6108 0.01392 0.00439 -0.0903 0.1007 0.1806
0.750 0.6372 0.01406 0.00457 -0.0901 0.1006 0.1965
1.000 0.6634 0.01414 0.00479 -0.0899 0.1006 0.2488
1.250 0.6894 0.01422 0.00501 -0.0898 0.1006 0.3132
1.750 0.7376 0.01315 0.00554 -0.0887 0.1006 1.0000
2.000 0.7632 0.01342 0.00578 -0.0884 0.1006 1.0000
2.250 0.7886 0.01370 0.00603 -0.0881 0.1007 1.0000
2.500 0.8139 0.01400 0.00630 -0.0877 0.1007 1.0000
2.750 0.8390 0.01431 0.00659 -0.0874 0.1007 1.0000
3.000 0.8639 0.01462 0.00689 -0.0870 0.1008 1.0000
3.250 0.8886 0.01495 0.00720 -0.0866 0.1008 1.0000
3.500 0.9132 0.01529 0.00754 -0.0862 0.1008 1.0000
3.750 0.9375 0.01565 0.00788 -0.0857 0.1009 1.0000
4.000 0.9619 0.01599 0.00822 -0.0853 0.1008 1.0000
4.250 0.9868 0.01625 0.00850 -0.0850 0.1005 1.0000
4.500 1.0116 0.01652 0.00877 -0.0846 0.1000 1.0000
4.750 1.0358 0.01683 0.00910 -0.0842 0.0997 1.0000
5.000 1.0597 0.01717 0.00946 -0.0838 0.0995 1.0000
5.250 1.0837 0.01749 0.00980 -0.0833 0.0989 1.0000
5.500 1.1075 0.01780 0.01014 -0.0828 0.0982 1.0000
5.750 1.1315 0.01804 0.01041 -0.0825 0.0964 1.0000
6.000 1.1547 0.01834 0.01072 -0.0820 0.0939 1.0000
6.250 1.1745 0.01905 0.01140 -0.0810 0.0923 1.0000
6.500 1.2016 0.01886 0.01131 -0.0810 0.0910 1.0000
6.750 1.2281 0.01880 0.01133 -0.0810 0.0886 1.0000
7.000 1.2553 0.01870 0.01128 -0.0811 0.0856 1.0000
7.250 1.2819 0.01867 0.01132 -0.0811 0.0818 1.0000
7.500 1.3141 0.01823 0.01063 -0.0821 0.0465 1.0000
7.750 1.3245 0.01950 0.01171 -0.0797 0.0176 1.0000
8.000 1.3421 0.02014 0.01237 -0.0784 0.0136 1.0000
8.250 1.3601 0.02069 0.01298 -0.0771 0.0119 1.0000
8.500 1.3759 0.02126 0.01363 -0.0754 0.0109 1.0000
8.750 1.3904 0.02193 0.01438 -0.0735 0.0100 1.0000
9.000 1.4029 0.02277 0.01529 -0.0715 0.0092 1.0000
9.250 1.4152 0.02363 0.01623 -0.0695 0.0086 1.0000
9.500 1.4283 0.02445 0.01714 -0.0678 0.0081 1.0000
9.750 1.4403 0.02537 0.01813 -0.0661 0.0076 1.0000
10.000 1.4515 0.02638 0.01922 -0.0644 0.0072 1.0000
10.250 1.4615 0.02751 0.02042 -0.0627 0.0068 1.0000
10.500 1.4691 0.02887 0.02188 -0.0609 0.0065 1.0000
10.750 1.4729 0.03059 0.02371 -0.0589 0.0062 1.0000
11.000 1.4798 0.03211 0.02534 -0.0574 0.0060 1.0000
11.250 1.4859 0.03375 0.02708 -0.0560 0.0058 1.0000
11.500 1.4907 0.03557 0.02901 -0.0546 0.0057 1.0000
11.750 1.4941 0.03761 0.03117 -0.0534 0.0055 1.0000
12.000 1.4961 0.03985 0.03353 -0.0524 0.0054 1.0000
12.250 1.4971 0.04232 0.03611 -0.0515 0.0052 1.0000
12.500 1.4971 0.04497 0.03888 -0.0509 0.0051 1.0000
12.750 1.4963 0.04780 0.04182 -0.0504 0.0049 1.0000
13.000 1.4945 0.05083 0.04496 -0.0501 0.0048 1.0000
13.250 1.4913 0.05412 0.04836 -0.0500 0.0047 1.0000
13.500 1.4868 0.05769 0.05204 -0.0501 0.0046 1.0000
13.750 1.4802 0.06172 0.05621 -0.0505 0.0045 1.0000
14.000 1.4719 0.06620 0.06081 -0.0513 0.0044 1.0000
14.250 1.4609 0.07122 0.06596 -0.0523 0.0043 1.0000
14.500 1.4478 0.07676 0.07164 -0.0537 0.0043 1.0000
14.750 1.4326 0.08280 0.07782 -0.0555 0.0042 1.0000
15.000 1.4218 0.08828 0.08342 -0.0572 0.0042 1.0000
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Polar data table (+)
Polar graphs
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