FX 66-S-161 AIRFOIL (fx66s161-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: FX 66-S-161 AIRFOIL (fx66s161-il) Reynolds number: 100,000 Max Cl/Cd: 16.59 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66s161-il-100000.txt Download as CSV file: xf-fx66s161-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-161 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1656 0.09987 0.09613 -0.0646 0.9450 0.1412
-10.250 -0.1442 0.09385 0.09004 -0.0687 0.9300 0.1454
-10.000 -0.2762 0.10479 0.10083 -0.0479 1.0000 0.1348
-9.750 -0.3113 0.10074 0.09704 -0.0604 0.9714 0.1423
-9.500 -0.2486 0.09579 0.09197 -0.0585 0.9583 0.1489
-9.250 -0.1155 0.07569 0.07155 -0.0810 0.8654 0.1741
-9.000 -0.1018 0.07286 0.06863 -0.0808 0.8511 0.1833
-8.750 -0.1835 0.07942 0.07533 -0.0811 0.8974 0.1770
-8.500 -0.1863 0.07491 0.07074 -0.0870 0.8747 0.1889
-8.250 -0.3355 0.04639 0.04078 -0.1100 0.8544 0.0696
-8.000 -0.3259 0.04255 0.03663 -0.1099 0.8412 0.0671
-7.750 -0.3162 0.03895 0.03252 -0.1093 0.8297 0.0646
-7.500 -0.3022 0.03576 0.02871 -0.1085 0.8202 0.0630
-7.250 -0.2850 0.03336 0.02584 -0.1075 0.8099 0.0630
-7.000 -0.2644 0.03167 0.02386 -0.1068 0.8010 0.0658
-6.750 -0.2423 0.03017 0.02194 -0.1060 0.7928 0.0693
-6.500 -0.2195 0.02888 0.02024 -0.1050 0.7841 0.0716
-6.250 -0.1955 0.02681 0.01824 -0.1046 0.7774 0.0771
-6.000 -0.1720 0.02592 0.01717 -0.1038 0.7698 0.0839
-5.750 -0.1485 0.02455 0.01588 -0.1030 0.7636 0.0915
-5.500 -0.1264 0.02362 0.01499 -0.1021 0.7578 0.1032
-5.250 -0.1064 0.02274 0.01422 -0.1010 0.7514 0.1192
-5.000 -0.0865 0.02158 0.01323 -0.1000 0.7465 0.1574
-4.750 -0.0780 0.01985 0.01307 -0.0981 0.7404 0.4084
-4.500 -0.0546 0.02087 0.01394 -0.0964 0.7346 0.4860
-4.250 -0.0295 0.02172 0.01469 -0.0947 0.7306 0.5205
-4.000 -0.0079 0.02243 0.01534 -0.0933 0.7248 0.5461
-3.750 0.0152 0.02308 0.01599 -0.0914 0.7198 0.5676
-3.500 0.0398 0.02352 0.01627 -0.0900 0.7159 0.5910
-3.250 0.0600 0.02409 0.01687 -0.0881 0.7107 0.6084
-3.000 0.0818 0.02446 0.01721 -0.0866 0.7060 0.6250
-2.750 0.1065 0.02459 0.01721 -0.0856 0.7022 0.6396
-2.500 0.1303 0.02474 0.01724 -0.0850 0.6982 0.6527
-2.250 0.1505 0.02503 0.01753 -0.0841 0.6931 0.6628
-2.000 0.1749 0.02511 0.01752 -0.0838 0.6894 0.6722
-1.750 0.2028 0.02508 0.01729 -0.0842 0.6862 0.6824
-1.500 0.2238 0.02537 0.01758 -0.0834 0.6820 0.6897
-1.250 0.2455 0.02569 0.01783 -0.0834 0.6770 0.6983
-1.000 0.2701 0.02582 0.01791 -0.0831 0.6735 0.7057
-0.750 0.2982 0.02587 0.01783 -0.0834 0.6709 0.7146
-0.500 0.3168 0.02646 0.01844 -0.0828 0.6668 0.7226
-0.250 0.3349 0.02708 0.01906 -0.0824 0.6617 0.7305
0.000 0.3600 0.02728 0.01921 -0.0822 0.6582 0.7389
0.250 0.3885 0.02733 0.01918 -0.0823 0.6556 0.7476
0.500 0.3994 0.02852 0.02044 -0.0814 0.6503 0.7570
0.750 0.4164 0.02916 0.02111 -0.0804 0.6453 0.7659
1.000 0.4442 0.02922 0.02113 -0.0804 0.6420 0.7769
1.250 0.4763 0.02911 0.02095 -0.0807 0.6397 0.7889
1.500 0.4650 0.03149 0.02353 -0.0776 0.6312 0.7995
1.750 0.4905 0.03167 0.02372 -0.0773 0.6278 0.8122
2.000 0.5225 0.03150 0.02352 -0.0774 0.6255 0.8265
2.250 0.4955 0.03506 0.02728 -0.0736 0.6163 0.8424
2.500 0.5176 0.03547 0.02776 -0.0730 0.6129 0.8637
2.750 0.5527 0.03506 0.02741 -0.0732 0.6108 0.8924
3.000 0.5396 0.03935 0.03195 -0.0740 0.6000 1.0000
3.250 0.5830 0.03949 0.03198 -0.0773 0.5972 1.0000
3.500 0.6305 0.03916 0.03155 -0.0800 0.5955 1.0000
3.750 0.5654 0.04576 0.03811 -0.0754 0.5833 1.0000
4.000 0.6122 0.04531 0.03759 -0.0771 0.5811 1.0000
4.250 0.5651 0.05081 0.04307 -0.0738 0.5716 1.0000
4.500 0.5944 0.05141 0.04362 -0.0743 0.5676 1.0000
4.750 0.6405 0.05098 0.04316 -0.0754 0.5653 1.0000
5.000 0.5912 0.05673 0.04889 -0.0726 0.5564 1.0000
5.250 0.6207 0.05733 0.04949 -0.0728 0.5524 1.0000
5.500 0.6697 0.05672 0.04886 -0.0738 0.5500 1.0000
5.750 0.6139 0.06323 0.05539 -0.0715 0.5432 1.0000
6.000 0.5567 0.07208 0.06434 -0.0722 0.5691 1.0000
6.250 0.5801 0.07385 0.06612 -0.0728 0.5667 1.0000
6.500 0.6007 0.07606 0.06834 -0.0734 0.5654 1.0000
6.750 0.6435 0.07227 0.06451 -0.0705 0.5264 1.0000
7.000 0.7074 0.07050 0.06276 -0.0711 0.5207 1.0000
7.250 0.6724 0.07587 0.06815 -0.0703 0.5162 1.0000
7.500 0.6675 0.07924 0.07156 -0.0702 0.5138 1.0000
7.750 0.6824 0.08112 0.07349 -0.0702 0.5093 1.0000
8.000 0.6784 0.08482 0.07724 -0.0705 0.5097 1.0000
8.250 0.6925 0.08725 0.07974 -0.0709 0.5079 1.0000
8.500 0.7025 0.09013 0.08267 -0.0713 0.5070 1.0000
8.750 0.7242 0.08924 0.08181 -0.0696 0.4832 1.0000
9.000 0.7739 0.08804 0.08069 -0.0691 0.4740 1.0000
9.250 0.7530 0.09252 0.08523 -0.0692 0.4677 1.0000
9.500 0.8206 0.08982 0.08264 -0.0686 0.4606 1.0000
9.750 0.7888 0.09503 0.08789 -0.0687 0.4510 1.0000
10.000 0.8092 0.09609 0.08903 -0.0683 0.4427 1.0000
10.250 0.8247 0.09756 0.09060 -0.0681 0.4351 1.0000
10.500 0.8301 0.09993 0.09305 -0.0680 0.4263 1.0000
10.750 0.8598 0.10009 0.09332 -0.0676 0.4198 1.0000
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