FX 66-H-80 (fx66h80-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-H-80 (fx66h80-il) Reynolds number: 100,000 Max Cl/Cd: 47.52 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66h80-il-100000.txt Download as CSV file: xf-fx66h80-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-H-80
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5597 0.11133 0.10704 0.0235 1.0000 0.0600
-8.500 -0.5642 0.10864 0.10442 0.0188 1.0000 0.0604
-8.250 -0.5700 0.10570 0.10156 0.0139 1.0000 0.0607
-8.000 -0.5728 0.10263 0.09848 0.0090 1.0000 0.0609
-7.750 -0.5451 0.09471 0.09062 0.0177 1.0000 0.0644
-7.500 -0.5416 0.09113 0.08709 0.0164 1.0000 0.0665
-7.250 -0.5397 0.08752 0.08352 0.0140 1.0000 0.0685
-7.000 -0.5361 0.08369 0.07970 0.0100 1.0000 0.0713
-6.750 -0.5327 0.08083 0.07668 0.0019 1.0000 0.0740
-6.500 -0.5251 0.07558 0.07141 0.0001 1.0000 0.0753
-6.250 -0.5125 0.07112 0.06710 0.0024 1.0000 0.0783
-6.000 -0.4999 0.06753 0.06347 0.0012 1.0000 0.0827
-5.750 -0.4866 0.06392 0.05951 -0.0036 1.0000 0.0890
-5.500 -0.4724 0.05961 0.05539 -0.0024 1.0000 0.0926
-5.250 -0.4550 0.05664 0.05205 -0.0050 1.0000 0.1027
-5.000 -0.4388 0.05251 0.04808 -0.0044 1.0000 0.1080
-4.750 -0.4205 0.04916 0.04463 -0.0053 1.0000 0.1200
-4.500 -0.4012 0.04622 0.04167 -0.0059 1.0000 0.1372
-4.250 -0.3808 0.04319 0.03862 -0.0071 1.0000 0.1610
-4.000 -0.3433 0.04000 0.03520 -0.0114 0.9032 0.2002
-3.250 -0.2986 0.03380 0.02852 -0.0046 0.7885 0.3104
-3.000 -0.2255 0.02742 0.01948 -0.0055 0.7736 0.0724
-2.750 -0.1984 0.02490 0.01630 -0.0037 0.7548 0.0628
-2.500 -0.1714 0.02355 0.01448 -0.0023 0.7378 0.0600
-2.250 -0.1444 0.02185 0.01245 -0.0013 0.7229 0.0594
-2.000 -0.1169 0.02046 0.01080 -0.0004 0.7088 0.0620
-1.750 -0.0905 0.01932 0.00962 0.0002 0.6957 0.0712
-1.500 0.0236 0.01328 0.00682 -0.0142 0.6790 1.0000
-1.250 0.0483 0.01341 0.00635 -0.0133 0.6681 1.0000
-1.000 0.0732 0.01354 0.00616 -0.0127 0.6567 1.0000
-0.750 0.0980 0.01369 0.00605 -0.0122 0.6463 1.0000
-0.500 0.1225 0.01387 0.00597 -0.0115 0.6372 1.0000
-0.250 0.1471 0.01405 0.00593 -0.0109 0.6283 1.0000
0.000 0.1723 0.01426 0.00596 -0.0105 0.6192 1.0000
0.250 0.1968 0.01448 0.00599 -0.0099 0.6116 1.0000
0.500 0.2220 0.01471 0.00611 -0.0095 0.6030 1.0000
0.750 0.2470 0.01497 0.00626 -0.0090 0.5955 1.0000
1.000 0.2719 0.01523 0.00640 -0.0085 0.5881 1.0000
1.250 0.2972 0.01553 0.00664 -0.0082 0.5805 1.0000
1.500 0.3219 0.01581 0.00683 -0.0077 0.5738 1.0000
1.750 0.3474 0.01616 0.00717 -0.0074 0.5666 1.0000
2.000 0.3721 0.01647 0.00743 -0.0069 0.5601 1.0000
2.250 0.3974 0.01686 0.00784 -0.0067 0.5529 1.0000
2.500 0.4222 0.01721 0.00816 -0.0062 0.5467 1.0000
2.750 0.4475 0.01766 0.00865 -0.0060 0.5402 1.0000
3.000 0.4723 0.01805 0.00905 -0.0055 0.5337 1.0000
3.250 0.4972 0.01853 0.00961 -0.0052 0.5276 1.0000
3.500 0.5223 0.01903 0.01018 -0.0050 0.5211 1.0000
3.750 0.5467 0.01947 0.01063 -0.0044 0.5159 1.0000
4.000 0.5718 0.02010 0.01143 -0.0044 0.5084 1.0000
4.250 0.5962 0.02053 0.01187 -0.0037 0.5038 1.0000
4.500 0.6209 0.02135 0.01298 -0.0039 0.4963 1.0000
4.750 0.6453 0.02181 0.01348 -0.0033 0.4911 1.0000
5.000 0.6694 0.02272 0.01463 -0.0034 0.4842 1.0000
5.250 0.6936 0.02330 0.01533 -0.0028 0.4784 1.0000
5.500 0.7173 0.02417 0.01641 -0.0027 0.4720 1.0000
5.750 0.7410 0.02489 0.01738 -0.0023 0.4652 1.0000
6.000 0.7643 0.02571 0.01842 -0.0019 0.4585 1.0000
6.250 0.7885 0.02573 0.01856 -0.0006 0.4496 1.0000
6.500 0.8128 0.02318 0.01588 0.0030 0.4231 1.0000
6.750 0.8368 0.02056 0.01314 0.0061 0.3884 1.0000
7.000 0.8602 0.01810 0.01080 0.0086 0.3173 1.0000
7.250 0.8627 0.02211 0.01320 0.0096 0.0801 1.0000
7.500 0.8758 0.02439 0.01556 0.0107 0.0658 1.0000
7.750 0.8888 0.02627 0.01752 0.0121 0.0568 1.0000
8.000 0.8992 0.02836 0.01948 0.0140 0.0508 1.0000
8.250 0.9175 0.03002 0.02120 0.0159 0.0479 1.0000
8.500 0.9386 0.03211 0.02331 0.0177 0.0456 1.0000
8.750 0.9590 0.03445 0.02571 0.0189 0.0427 1.0000
9.000 0.9791 0.03882 0.03004 0.0198 0.0396 1.0000
9.250 0.9962 0.04164 0.03324 0.0209 0.0391 1.0000
9.500 1.0119 0.04589 0.03779 0.0219 0.0396 1.0000
9.750 1.0266 0.04878 0.04105 0.0231 0.0404 1.0000
10.000 1.0313 0.05109 0.04415 0.0249 0.0428 1.0000
10.250 1.0256 0.05548 0.04912 0.0260 0.0456 1.0000
10.500 1.0195 0.05994 0.05391 0.0266 0.0478 1.0000
10.750 1.0139 0.06493 0.05909 0.0268 0.0498 1.0000
11.000 0.9074 0.05713 0.05167 0.0288 0.0470 1.0000
11.250 1.0039 0.07672 0.07139 0.0268 0.0642 1.0000
11.500 0.9796 0.08043 0.07526 0.0247 0.0644 1.0000
11.750 0.9551 0.08559 0.08053 0.0210 0.0644 1.0000
12.000 0.9336 0.09138 0.08634 0.0168 0.0643 1.0000
12.250 0.9102 0.09815 0.09319 0.0117 0.0642 1.0000
12.500 0.8856 0.10582 0.10089 0.0059 0.0642 1.0000
12.750 0.8589 0.11476 0.10986 -0.0011 0.0643 1.0000
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Polar data table (+)
Polar graphs
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