NACA 66(2)-215 (naca662215-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(2)-215 (naca662215-il) Reynolds number: 100,000 Max Cl/Cd: 37.57 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca662215-il-100000.txt Download as CSV file: xf-naca662215-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-215
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4662 0.11008 0.10524 -0.0472 1.0000 0.1595
-11.000 -0.4975 0.10840 0.10368 -0.0451 1.0000 0.1646
-10.750 -0.5763 0.10467 0.10018 -0.0470 1.0000 0.1667
-10.500 -0.5235 0.10388 0.09930 -0.0402 1.0000 0.1721
-10.250 -0.5359 0.10191 0.09738 -0.0380 1.0000 0.1772
-10.000 -0.6103 0.09690 0.09255 -0.0404 1.0000 0.1814
-9.750 -0.5795 0.09572 0.09134 -0.0354 1.0000 0.1875
-9.500 -0.5994 0.09284 0.08853 -0.0341 1.0000 0.1931
-9.250 -0.4955 0.09386 0.08982 -0.0263 1.0000 0.2066
-7.000 -0.8760 0.04936 0.04215 0.0014 1.0000 0.0956
-6.750 -0.8652 0.04524 0.03698 0.0054 1.0000 0.0801
-6.500 -0.8478 0.04329 0.03475 0.0072 1.0000 0.0783
-6.250 -0.8324 0.04112 0.03224 0.0090 1.0000 0.0784
-6.000 -0.8148 0.03893 0.02976 0.0105 1.0000 0.0782
-5.750 -0.7956 0.03682 0.02741 0.0118 1.0000 0.0777
-5.500 -0.7753 0.03504 0.02536 0.0131 1.0000 0.0775
-5.250 -0.7544 0.03358 0.02367 0.0143 1.0000 0.0777
-5.000 -0.7337 0.03255 0.02239 0.0156 1.0000 0.0788
-4.750 -0.7116 0.03084 0.02073 0.0163 1.0000 0.0814
-4.500 -0.6908 0.02979 0.01969 0.0173 1.0000 0.0841
-4.250 -0.6702 0.02893 0.01881 0.0184 1.0000 0.0864
-4.000 -0.6505 0.02818 0.01803 0.0197 1.0000 0.0896
-3.750 -0.6320 0.02751 0.01734 0.0211 1.0000 0.0937
-3.500 -0.6158 0.02664 0.01660 0.0227 1.0000 0.0998
-3.250 -0.5985 0.02608 0.01598 0.0242 1.0000 0.1065
-3.000 -0.5823 0.02537 0.01536 0.0257 1.0000 0.1165
-2.750 -0.5657 0.02460 0.01480 0.0272 1.0000 0.1433
-2.500 -0.5752 0.02201 0.01547 0.0349 1.0000 0.6861
-2.250 -0.5744 0.02369 0.01720 0.0436 1.0000 0.7883
-2.000 -0.2752 0.03714 0.03009 0.0103 0.9786 0.9332
-1.750 -0.2182 0.03725 0.03002 0.0035 0.9750 0.9407
-1.500 -0.1906 0.03733 0.02999 0.0020 0.9730 0.9480
-1.250 -0.1493 0.03740 0.02993 -0.0021 0.9700 0.9536
-1.000 -0.1360 0.03736 0.02983 -0.0008 0.9681 0.9599
-0.750 -0.0978 0.03729 0.02969 -0.0044 0.9651 0.9644
-0.500 -0.0671 0.03743 0.02975 -0.0066 0.9616 0.9690
-0.250 -0.0320 0.03778 0.03004 -0.0096 0.9573 0.9730
0.000 -0.0067 0.03765 0.02989 -0.0108 0.9532 0.9764
0.250 0.0218 0.03779 0.02999 -0.0125 0.9489 0.9798
0.500 0.0603 0.03823 0.03041 -0.0161 0.9428 0.9824
0.750 0.0790 0.03820 0.03037 -0.0160 0.9373 0.9852
1.000 0.1207 0.03852 0.03069 -0.0201 0.9309 0.9874
1.250 0.1438 0.03866 0.03085 -0.0208 0.9239 0.9898
1.500 0.1774 0.03896 0.03117 -0.0233 0.9169 0.9918
1.750 0.2027 0.03922 0.03146 -0.0243 0.9086 0.9939
2.000 0.2400 0.03951 0.03180 -0.0274 0.9009 0.9954
2.250 0.2642 0.03972 0.03206 -0.0281 0.8915 0.9973
2.500 0.3131 0.04009 0.03250 -0.0330 0.8836 0.9987
2.750 0.3281 0.04020 0.03267 -0.0319 0.8721 1.0000
3.000 0.3530 0.04043 0.03298 -0.0323 0.8619 1.0000
3.250 0.3888 0.04058 0.03322 -0.0344 0.8525 1.0000
3.500 0.4006 0.04070 0.03341 -0.0324 0.8398 1.0000
3.750 0.4232 0.04082 0.03363 -0.0321 0.8283 1.0000
4.000 0.4707 0.04073 0.03369 -0.0357 0.8198 1.0000
4.250 0.4849 0.04068 0.03374 -0.0338 0.8060 1.0000
4.500 0.5058 0.04054 0.03371 -0.0328 0.7925 1.0000
4.750 0.5644 0.03906 0.03246 -0.0363 0.7758 1.0000
5.000 0.8355 0.02224 0.01634 -0.0588 0.6730 1.0000
5.250 0.8182 0.02218 0.01387 -0.0469 0.2862 1.0000
5.500 0.7925 0.02401 0.01477 -0.0383 0.1649 1.0000
5.750 0.7779 0.02512 0.01552 -0.0313 0.1295 1.0000
6.000 0.7689 0.02585 0.01616 -0.0253 0.1164 1.0000
6.250 0.7615 0.02655 0.01684 -0.0197 0.1080 1.0000
6.500 0.7561 0.02722 0.01750 -0.0146 0.1020 1.0000
6.750 0.7525 0.02794 0.01820 -0.0098 0.0970 1.0000
7.000 0.7532 0.02853 0.01881 -0.0057 0.0919 1.0000
7.250 0.7577 0.02933 0.01952 -0.0023 0.0872 1.0000
7.500 0.7810 0.03031 0.02047 -0.0014 0.0831 1.0000
7.750 0.8128 0.03136 0.02155 -0.0019 0.0786 1.0000
8.000 0.9180 0.03505 0.02517 -0.0149 0.0715 1.0000
8.250 0.9515 0.03688 0.02725 -0.0158 0.0704 1.0000
8.500 0.9719 0.03855 0.02918 -0.0145 0.0693 1.0000
8.750 0.9854 0.04017 0.03108 -0.0123 0.0683 1.0000
9.000 0.9934 0.04174 0.03290 -0.0092 0.0674 1.0000
9.250 0.9988 0.04354 0.03497 -0.0058 0.0673 1.0000
9.500 1.0003 0.04552 0.03724 -0.0018 0.0680 1.0000
9.750 0.9970 0.04747 0.03945 0.0029 0.0690 1.0000
10.000 0.9903 0.04937 0.04156 0.0080 0.0699 1.0000
10.250 0.9859 0.05165 0.04402 0.0124 0.0710 1.0000
10.500 1.0059 0.05638 0.04886 0.0126 0.0734 1.0000
10.750 0.9605 0.05713 0.05044 0.0230 0.0790 1.0000
11.000 0.9776 0.06411 0.05754 0.0223 0.0851 1.0000
11.250 0.8856 0.06173 0.05601 0.0328 0.0992 1.0000
11.500 0.8449 0.06328 0.05780 0.0383 0.0986 1.0000
11.750 0.7987 0.06604 0.06082 0.0422 0.0977 1.0000
12.000 0.6238 0.11231 0.10739 0.0154 0.1966 1.0000
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Polar data table (+)
Polar graphs
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