FX 66-S-161 AIRFOIL (fx66s161-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-161 AIRFOIL (fx66s161-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.45 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66s161-il-1000000-n5.txt Download as CSV file: xf-fx66s161-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.6110 0.11794 0.11601 -0.0350 1.0000 0.0049
-16.000 -0.6856 0.09828 0.09613 -0.0448 1.0000 0.0048
-15.750 -0.7255 0.08623 0.08394 -0.0513 1.0000 0.0048
-15.500 -0.7610 0.07547 0.07302 -0.0576 1.0000 0.0048
-15.250 -0.7924 0.06617 0.06356 -0.0633 1.0000 0.0048
-15.000 -0.8181 0.05860 0.05582 -0.0680 1.0000 0.0047
-14.750 -0.8218 0.05423 0.05137 -0.0711 0.9997 0.0048
-14.500 -0.8262 0.04793 0.04489 -0.0777 0.9509 0.0048
-14.250 -0.7374 0.04071 0.03713 -0.1040 0.8809 0.0049
-14.000 -0.7449 0.03760 0.03354 -0.1053 0.7932 0.0049
-13.750 -0.7528 0.03459 0.03031 -0.1059 0.7614 0.0048
-13.500 -0.7536 0.03228 0.02782 -0.1063 0.7373 0.0049
-13.250 -0.7597 0.02955 0.02489 -0.1067 0.7181 0.0050
-13.000 -0.7606 0.02738 0.02257 -0.1067 0.7029 0.0051
-12.750 -0.7623 0.02529 0.02034 -0.1065 0.6903 0.0051
-12.500 -0.7632 0.02361 0.01853 -0.1056 0.6791 0.0052
-12.250 -0.7652 0.02240 0.01719 -0.1032 0.6687 0.0053
-12.000 -0.7603 0.02144 0.01612 -0.1011 0.6595 0.0053
-11.750 -0.7474 0.02064 0.01521 -0.0998 0.6513 0.0054
-11.500 -0.7320 0.01991 0.01439 -0.0988 0.6434 0.0055
-11.250 -0.7158 0.01916 0.01354 -0.0978 0.6368 0.0056
-11.000 -0.6967 0.01857 0.01285 -0.0970 0.6300 0.0057
-10.750 -0.6775 0.01794 0.01213 -0.0963 0.6238 0.0058
-10.500 -0.6568 0.01736 0.01147 -0.0957 0.6179 0.0059
-10.250 -0.6355 0.01682 0.01084 -0.0951 0.6117 0.0060
-10.000 -0.6135 0.01631 0.01025 -0.0946 0.6062 0.0062
-9.750 -0.5909 0.01581 0.00967 -0.0941 0.5999 0.0064
-9.500 -0.5678 0.01536 0.00913 -0.0937 0.5941 0.0066
-9.250 -0.5439 0.01493 0.00863 -0.0934 0.5889 0.0068
-9.000 -0.5196 0.01455 0.00816 -0.0931 0.5835 0.0070
-8.750 -0.4957 0.01409 0.00763 -0.0927 0.5790 0.0073
-8.500 -0.4712 0.01365 0.00713 -0.0924 0.5748 0.0076
-8.250 -0.4461 0.01328 0.00672 -0.0922 0.5702 0.0079
-8.000 -0.4206 0.01296 0.00634 -0.0920 0.5659 0.0083
-7.750 -0.3947 0.01266 0.00598 -0.0919 0.5622 0.0087
-7.500 -0.3684 0.01237 0.00565 -0.0918 0.5582 0.0092
-7.250 -0.3421 0.01210 0.00532 -0.0917 0.5541 0.0096
-7.000 -0.3159 0.01181 0.00498 -0.0915 0.5503 0.0104
-6.750 -0.2891 0.01156 0.00471 -0.0915 0.5471 0.0114
-6.500 -0.2620 0.01134 0.00445 -0.0915 0.5436 0.0124
-6.250 -0.2350 0.01112 0.00419 -0.0915 0.5400 0.0137
-6.000 -0.2079 0.01092 0.00396 -0.0914 0.5365 0.0152
-5.750 -0.1805 0.01075 0.00375 -0.0915 0.5333 0.0167
-5.500 -0.1530 0.01055 0.00353 -0.0915 0.5302 0.0187
-5.250 -0.1255 0.01037 0.00334 -0.0916 0.5270 0.0211
-5.000 -0.0979 0.01022 0.00315 -0.0916 0.5242 0.0235
-4.750 -0.0703 0.01006 0.00298 -0.0916 0.5213 0.0271
-4.500 -0.0426 0.00989 0.00281 -0.0917 0.5187 0.0332
-4.250 -0.0148 0.00971 0.00265 -0.0918 0.5160 0.0423
-4.000 0.0129 0.00952 0.00249 -0.0919 0.5131 0.0565
-3.750 0.0405 0.00932 0.00234 -0.0920 0.5107 0.0769
-3.500 0.0680 0.00909 0.00220 -0.0921 0.5084 0.1056
-3.250 0.0954 0.00886 0.00206 -0.0922 0.5062 0.1433
-2.750 0.1495 0.00808 0.00173 -0.0926 0.5024 0.2836
-2.500 0.1772 0.00785 0.00165 -0.0927 0.5003 0.3343
-2.250 0.2053 0.00771 0.00159 -0.0929 0.4982 0.3692
-2.000 0.2334 0.00760 0.00157 -0.0930 0.4963 0.4067
-1.750 0.2618 0.00756 0.00158 -0.0932 0.4944 0.4339
-1.500 0.2902 0.00756 0.00159 -0.0933 0.4925 0.4510
-1.000 0.3476 0.00759 0.00160 -0.0937 0.4886 0.4708
-0.750 0.3764 0.00759 0.00161 -0.0939 0.4866 0.4772
-0.500 0.4052 0.00761 0.00161 -0.0941 0.4844 0.4816
-0.250 0.4340 0.00764 0.00162 -0.0943 0.4820 0.4847
0.000 0.4625 0.00766 0.00163 -0.0945 0.4797 0.4879
0.250 0.4909 0.00770 0.00165 -0.0947 0.4775 0.4913
0.500 0.5193 0.00774 0.00167 -0.0948 0.4756 0.4946
0.750 0.5481 0.00777 0.00170 -0.0951 0.4742 0.4978
1.000 0.5768 0.00779 0.00172 -0.0953 0.4724 0.5009
1.250 0.6054 0.00781 0.00176 -0.0955 0.4703 0.5043
1.500 0.6338 0.00784 0.00180 -0.0957 0.4682 0.5078
1.750 0.6622 0.00788 0.00184 -0.0959 0.4660 0.5111
2.000 0.6905 0.00793 0.00188 -0.0960 0.4639 0.5141
2.250 0.7186 0.00799 0.00194 -0.0962 0.4620 0.5173
2.500 0.7468 0.00803 0.00200 -0.0963 0.4603 0.5211
2.750 0.7753 0.00806 0.00207 -0.0965 0.4586 0.5249
3.000 0.8036 0.00810 0.00213 -0.0967 0.4568 0.5287
3.250 0.8319 0.00815 0.00221 -0.0969 0.4548 0.5329
3.500 0.8599 0.00819 0.00228 -0.0971 0.4526 0.5380
3.750 0.8878 0.00826 0.00237 -0.0972 0.4501 0.5432
4.000 0.9153 0.00833 0.00246 -0.0973 0.4474 0.5486
4.250 0.9432 0.00838 0.00255 -0.0974 0.4451 0.5549
4.500 0.9713 0.00843 0.00265 -0.0976 0.4425 0.5618
4.750 0.9991 0.00847 0.00275 -0.0977 0.4395 0.5698
5.250 1.0539 0.00861 0.00297 -0.0978 0.4342 0.5840
5.500 1.0810 0.00870 0.00310 -0.0979 0.4316 0.5925
5.750 1.1087 0.00875 0.00323 -0.0980 0.4292 0.6028
6.000 1.1362 0.00880 0.00336 -0.0981 0.4261 0.6134
6.250 1.1632 0.00888 0.00350 -0.0981 0.4223 0.6247
6.750 1.2165 0.00905 0.00379 -0.0981 0.4122 0.6510
7.250 1.2652 0.00941 0.00417 -0.0972 0.3813 0.6870
7.500 1.2835 0.00993 0.00456 -0.0959 0.3452 0.7102
7.750 1.2975 0.01067 0.00514 -0.0938 0.3032 0.7418
8.000 1.3080 0.01149 0.00583 -0.0912 0.2548 0.7885
8.250 1.3119 0.01238 0.00677 -0.0875 0.1987 0.9692
8.500 1.3108 0.01370 0.00779 -0.0831 0.1479 1.0000
8.750 1.3076 0.01471 0.00864 -0.0781 0.1149 1.0000
9.250 1.2996 0.01700 0.01069 -0.0690 0.0644 1.0000
9.500 1.2989 0.01822 0.01186 -0.0657 0.0492 1.0000
9.750 1.2993 0.01956 0.01318 -0.0629 0.0377 1.0000
10.000 1.2992 0.02114 0.01474 -0.0605 0.0278 1.0000
10.250 1.3002 0.02286 0.01645 -0.0586 0.0207 1.0000
10.500 1.3051 0.02446 0.01808 -0.0573 0.0174 1.0000
10.750 1.3082 0.02631 0.01995 -0.0561 0.0139 1.0000
11.000 1.3146 0.02798 0.02166 -0.0552 0.0128 1.0000
11.250 1.3178 0.02996 0.02368 -0.0542 0.0109 1.0000
11.500 1.3234 0.03179 0.02555 -0.0534 0.0100 1.0000
11.750 1.3288 0.03367 0.02749 -0.0528 0.0094 1.0000
12.000 1.3319 0.03578 0.02964 -0.0520 0.0085 1.0000
12.250 1.3348 0.03793 0.03184 -0.0514 0.0079 1.0000
12.500 1.3388 0.04002 0.03397 -0.0508 0.0073 1.0000
12.750 1.3422 0.04218 0.03620 -0.0503 0.0070 1.0000
13.000 1.3449 0.04447 0.03854 -0.0498 0.0064 1.0000
13.250 1.3473 0.04686 0.04097 -0.0495 0.0060 1.0000
13.500 1.3490 0.04937 0.04353 -0.0491 0.0056 1.0000
13.750 1.3531 0.05169 0.04591 -0.0489 0.0053 1.0000
14.000 1.3560 0.05419 0.04846 -0.0488 0.0048 1.0000
14.250 1.3600 0.05661 0.05093 -0.0488 0.0047 1.0000
14.500 1.3627 0.05921 0.05359 -0.0487 0.0044 1.0000
14.750 1.3646 0.06196 0.05639 -0.0488 0.0042 1.0000
15.000 1.3668 0.06471 0.05919 -0.0489 0.0039 1.0000
15.250 1.3692 0.06750 0.06205 -0.0491 0.0037 1.0000
15.500 1.3731 0.07010 0.06471 -0.0494 0.0036 1.0000
15.750 1.3745 0.07311 0.06778 -0.0497 0.0034 1.0000
16.000 1.3781 0.07584 0.07057 -0.0500 0.0033 1.0000
16.250 1.3804 0.07880 0.07359 -0.0505 0.0032 1.0000
16.500 1.3828 0.08175 0.07660 -0.0510 0.0030 1.0000
16.750 1.3841 0.08493 0.07984 -0.0516 0.0029 1.0000
17.000 1.3863 0.08799 0.08295 -0.0522 0.0028 1.0000
17.250 1.3871 0.09133 0.08636 -0.0530 0.0027 1.0000
17.500 1.3880 0.09465 0.08974 -0.0538 0.0026 1.0000
17.750 1.3876 0.09823 0.09339 -0.0547 0.0025 1.0000
18.000 1.3882 0.10169 0.09692 -0.0557 0.0025 1.0000
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Polar data table (+)
Polar graphs
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