WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Reynolds number: 100,000 Max Cl/Cd: 12.65 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66a175-il-100000.txt Download as CSV file: xf-fx66a175-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 66-17A-175 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2539 0.13080 0.12670 -0.0446 1.0000 0.0963
-11.750 -0.2731 0.12840 0.12445 -0.0493 1.0000 0.1004
-11.500 -0.2726 0.12416 0.12037 -0.0509 1.0000 0.1020
-11.250 -0.2267 0.11873 0.11495 -0.0538 0.9376 0.1077
-11.000 -0.2430 0.11345 0.10965 -0.0697 0.9037 0.1150
-10.750 -0.1694 0.10639 0.10216 -0.0745 0.8560 0.1269
-10.500 -0.1617 0.10163 0.09720 -0.0796 0.8290 0.1314
-10.250 -0.1561 0.09897 0.09439 -0.0822 0.8086 0.1423
-10.000 -0.1367 0.09531 0.09060 -0.0822 0.7922 0.1480
-9.750 -0.1624 0.09243 0.08775 -0.0880 0.7829 0.1575
-9.500 -0.1272 0.08880 0.08396 -0.0856 0.7699 0.1620
-9.250 -0.1461 0.08550 0.08073 -0.0895 0.7614 0.1732
-9.000 -0.1205 0.08241 0.07752 -0.0883 0.7515 0.1764
-8.750 -0.1171 0.07926 0.07431 -0.0893 0.7439 0.1816
-8.500 -0.2298 0.04279 0.03796 -0.1069 0.7344 0.0829
-8.250 -0.2816 0.04957 0.04388 -0.1130 0.7427 0.0688
-8.000 -0.2925 0.04659 0.03990 -0.1116 0.7356 0.0604
-7.750 -0.2775 0.04275 0.03583 -0.1113 0.7292 0.0591
-7.500 -0.2642 0.03964 0.03242 -0.1107 0.7222 0.0582
-7.250 -0.2478 0.03674 0.02915 -0.1099 0.7160 0.0566
-7.000 -0.2289 0.03427 0.02629 -0.1090 0.7100 0.0556
-6.750 -0.2076 0.03218 0.02385 -0.1081 0.7039 0.0555
-6.500 -0.1833 0.03042 0.02174 -0.1072 0.6990 0.0563
-6.250 -0.1601 0.02925 0.02036 -0.1064 0.6925 0.0590
-6.000 -0.1366 0.02762 0.01872 -0.1056 0.6874 0.0633
-5.750 -0.1134 0.02658 0.01766 -0.1046 0.6828 0.0680
-5.500 -0.0917 0.02580 0.01687 -0.1032 0.6775 0.0737
-5.250 -0.0728 0.02492 0.01609 -0.1018 0.6732 0.0861
-5.000 -0.0558 0.02378 0.01507 -0.1005 0.6697 0.1126
-4.750 -0.0524 0.02241 0.01557 -0.0977 0.6653 0.4569
-4.500 -0.0290 0.02475 0.01788 -0.0943 0.6606 0.5129
-4.250 -0.0052 0.02634 0.01940 -0.0912 0.6568 0.5440
-4.000 0.0150 0.02779 0.02088 -0.0875 0.6524 0.5699
-3.750 0.0350 0.02854 0.02156 -0.0850 0.6478 0.5924
-3.500 0.0571 0.02900 0.02192 -0.0827 0.6441 0.6086
-3.250 0.0806 0.02918 0.02191 -0.0814 0.6412 0.6227
-3.000 0.0996 0.02943 0.02212 -0.0803 0.6370 0.6336
-2.750 0.1203 0.02955 0.02218 -0.0791 0.6333 0.6418
-2.500 0.1454 0.02943 0.02185 -0.0797 0.6301 0.6503
-2.250 0.1703 0.02939 0.02167 -0.0791 0.6276 0.6558
-2.000 0.1916 0.02960 0.02179 -0.0793 0.6242 0.6630
-1.750 0.2106 0.02986 0.02203 -0.0786 0.6201 0.6680
-1.500 0.2344 0.02994 0.02201 -0.0786 0.6166 0.6727
-1.250 0.2624 0.02991 0.02179 -0.0796 0.6139 0.6772
-1.000 0.2888 0.03002 0.02175 -0.0800 0.6117 0.6810
-0.750 0.3013 0.03089 0.02273 -0.0790 0.6078 0.6846
-0.500 0.3207 0.03146 0.02326 -0.0790 0.6043 0.6885
-0.250 0.3457 0.03178 0.02347 -0.0796 0.6014 0.6927
0.000 0.3733 0.03187 0.02344 -0.0800 0.5991 0.6957
0.250 0.3924 0.03259 0.02414 -0.0798 0.5964 0.6984
0.500 0.3936 0.03445 0.02613 -0.0783 0.5917 0.7014
0.750 0.4098 0.03543 0.02708 -0.0781 0.5884 0.7049
1.000 0.4341 0.03604 0.02759 -0.0786 0.5861 0.7082
1.250 0.4604 0.03640 0.02790 -0.0789 0.5845 0.7109
1.500 0.4426 0.03983 0.03148 -0.0763 0.5809 0.7133
1.750 0.2576 0.05661 0.04873 -0.0688 0.6262 0.7126
2.000 0.2804 0.05657 0.04862 -0.0681 0.6112 0.7159
2.250 0.2112 0.06272 0.05492 -0.0662 0.6576 0.7171
2.500 0.2474 0.06457 0.05669 -0.0683 0.6559 0.7211
2.750 0.2362 0.06499 0.05708 -0.0655 0.6452 0.7239
3.000 0.2696 0.06648 0.05854 -0.0668 0.6423 0.7282
3.250 0.2646 0.06742 0.05947 -0.0649 0.6338 0.7315
3.500 0.2909 0.06877 0.06077 -0.0659 0.6296 0.7358
3.750 0.3267 0.07060 0.06258 -0.0676 0.6273 0.7404
4.000 0.3181 0.07137 0.06336 -0.0656 0.6175 0.7441
4.250 0.3480 0.07298 0.06492 -0.0669 0.6143 0.7502
4.500 0.3841 0.07511 0.06706 -0.0688 0.6126 0.7566
4.750 0.3719 0.07574 0.06771 -0.0667 0.6021 0.7613
5.000 0.4051 0.07753 0.06951 -0.0682 0.5992 0.7691
5.250 0.4426 0.07998 0.07200 -0.0702 0.5978 0.7788
5.500 0.4236 0.08038 0.07246 -0.0678 0.5870 0.7852
5.750 0.4566 0.08232 0.07447 -0.0693 0.5845 0.7978
6.000 0.4502 0.08358 0.07584 -0.0682 0.5758 0.8095
6.250 0.4769 0.08514 0.07762 -0.0693 0.5717 0.8378
6.500 0.5132 0.08723 0.07991 -0.0715 0.5696 1.0000
6.750 0.5012 0.08853 0.08119 -0.0705 0.5599 1.0000
7.000 0.5327 0.09064 0.08326 -0.0722 0.5563 1.0000
7.250 0.5706 0.09352 0.08612 -0.0744 0.5546 1.0000
7.500 0.5520 0.09444 0.08704 -0.0728 0.5438 1.0000
7.750 0.5859 0.09685 0.08941 -0.0743 0.5410 1.0000
8.000 0.5744 0.09853 0.09111 -0.0734 0.5322 1.0000
8.250 0.6015 0.10057 0.09313 -0.0742 0.5279 1.0000
8.500 0.6380 0.10349 0.09609 -0.0756 0.5260 1.0000
8.750 0.6166 0.10472 0.09733 -0.0743 0.5157 1.0000
9.000 0.6463 0.10710 0.09974 -0.0752 0.5126 1.0000
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