Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Davis AIRFOIL (davis-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.03 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-davis-il-1000000-n5.txt Download as CSV file: xf-davis-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Davis 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6002 0.09752 0.09562 -0.0476 1.0000 0.0042
-13.750 -0.6655 0.08249 0.08050 -0.0549 1.0000 0.0040
-13.500 -0.7152 0.07158 0.06953 -0.0601 1.0000 0.0040
-13.250 -0.7909 0.05832 0.05620 -0.0661 1.0000 0.0038
-13.000 -0.8588 0.03333 0.03070 -0.0956 0.9915 0.0037
-12.750 -0.8497 0.02979 0.02692 -0.0988 0.9873 0.0038
-12.500 -0.8371 0.02747 0.02440 -0.0999 0.9832 0.0038
-12.250 -0.8195 0.02556 0.02231 -0.1009 0.9802 0.0039
-12.000 -0.7983 0.02381 0.02038 -0.1021 0.9783 0.0040
-11.750 -0.7775 0.02253 0.01895 -0.1025 0.9752 0.0041
-11.500 -0.7552 0.02129 0.01755 -0.1029 0.9721 0.0041
-11.250 -0.7288 0.02021 0.01634 -0.1040 0.9699 0.0042
-11.000 -0.7047 0.01874 0.01470 -0.1048 0.9671 0.0045
-10.750 -0.6830 0.01774 0.01357 -0.1046 0.9621 0.0046
-10.500 -0.6552 0.01697 0.01270 -0.1054 0.9591 0.0048
-10.250 -0.6308 0.01619 0.01181 -0.1054 0.9548 0.0049
-10.000 -0.6052 0.01559 0.01112 -0.1054 0.9501 0.0051
-9.750 -0.5780 0.01494 0.01037 -0.1058 0.9462 0.0053
-9.500 -0.5547 0.01437 0.00971 -0.1053 0.9401 0.0055
-9.250 -0.5286 0.01383 0.00906 -0.1053 0.9355 0.0058
-9.000 -0.5047 0.01331 0.00844 -0.1048 0.9302 0.0060
-8.750 -0.4797 0.01283 0.00787 -0.1045 0.9247 0.0061
-8.500 -0.4549 0.01233 0.00727 -0.1041 0.9190 0.0064
-8.250 -0.4308 0.01182 0.00669 -0.1035 0.9121 0.0069
-8.000 -0.4052 0.01146 0.00626 -0.1032 0.9057 0.0073
-7.750 -0.3802 0.01112 0.00586 -0.1028 0.8980 0.0078
-7.500 -0.3545 0.01081 0.00548 -0.1024 0.8902 0.0083
-7.250 -0.3290 0.01054 0.00512 -0.1020 0.8805 0.0088
-7.000 -0.3040 0.01020 0.00469 -0.1015 0.8700 0.0095
-6.750 -0.2788 0.00991 0.00435 -0.1010 0.8591 0.0106
-6.500 -0.2535 0.00968 0.00405 -0.1005 0.8471 0.0116
-6.250 -0.2282 0.00949 0.00377 -0.0999 0.8328 0.0126
-6.000 -0.2038 0.00930 0.00349 -0.0992 0.8131 0.0145
-5.750 -0.1799 0.00918 0.00328 -0.0984 0.7908 0.0169
-5.500 -0.1555 0.00910 0.00309 -0.0976 0.7716 0.0184
-5.250 -0.1310 0.00896 0.00288 -0.0969 0.7561 0.0213
-5.000 -0.1058 0.00885 0.00271 -0.0964 0.7451 0.0240
-4.750 -0.0795 0.00876 0.00256 -0.0961 0.7370 0.0260
-4.500 -0.0533 0.00869 0.00243 -0.0957 0.7295 0.0267
-4.250 -0.0271 0.00854 0.00223 -0.0953 0.7229 0.0296
-3.750 0.0255 0.00830 0.00192 -0.0947 0.7102 0.0349
-3.500 0.0519 0.00820 0.00179 -0.0943 0.7041 0.0395
-3.250 0.0773 0.00796 0.00163 -0.0939 0.6987 0.0642
-3.000 0.1033 0.00776 0.00151 -0.0936 0.6921 0.0921
-2.750 0.1289 0.00763 0.00143 -0.0931 0.6850 0.1173
-2.500 0.1556 0.00752 0.00136 -0.0929 0.6779 0.1346
-2.250 0.1819 0.00749 0.00130 -0.0926 0.6700 0.1449
-2.000 0.2085 0.00740 0.00124 -0.0923 0.6614 0.1576
-1.750 0.2348 0.00736 0.00119 -0.0920 0.6521 0.1680
-1.500 0.2606 0.00732 0.00114 -0.0915 0.6382 0.1821
-1.250 0.2859 0.00729 0.00111 -0.0910 0.6196 0.2032
-1.000 0.3098 0.00734 0.00110 -0.0902 0.5906 0.2238
-0.750 0.3330 0.00744 0.00111 -0.0893 0.5601 0.2456
-0.500 0.3573 0.00752 0.00113 -0.0886 0.5393 0.2601
-0.250 0.3826 0.00755 0.00115 -0.0881 0.5263 0.2780
0.000 0.4075 0.00749 0.00118 -0.0876 0.5162 0.3191
0.250 0.4328 0.00747 0.00122 -0.0871 0.5069 0.3529
0.500 0.4588 0.00745 0.00125 -0.0868 0.5003 0.3813
0.750 0.4845 0.00744 0.00129 -0.0864 0.4927 0.4090
1.000 0.5103 0.00743 0.00134 -0.0860 0.4851 0.4408
1.250 0.5356 0.00743 0.00139 -0.0855 0.4759 0.4720
1.500 0.5610 0.00742 0.00144 -0.0850 0.4649 0.5048
1.750 0.5855 0.00738 0.00150 -0.0844 0.4539 0.5532
2.000 0.6022 0.00694 0.00160 -0.0822 0.4415 0.7552
2.250 0.6211 0.00680 0.00170 -0.0802 0.4226 0.8556
2.500 0.6703 0.00700 0.00194 -0.0851 0.3828 0.9585
2.750 0.7175 0.00733 0.00213 -0.0897 0.3540 0.9786
3.000 0.7534 0.00755 0.00228 -0.0917 0.3391 0.9899
3.250 0.7859 0.00775 0.00242 -0.0929 0.3286 0.9978
3.500 0.8169 0.00791 0.00255 -0.0937 0.3206 1.0000
3.750 0.8389 0.00806 0.00268 -0.0926 0.3137 1.0000
4.000 0.8616 0.00819 0.00279 -0.0915 0.3080 1.0000
4.250 0.8841 0.00833 0.00293 -0.0905 0.3018 1.0000
4.500 0.9059 0.00852 0.00307 -0.0893 0.2907 1.0000
4.750 0.9277 0.00871 0.00323 -0.0882 0.2809 1.0000
5.000 0.9500 0.00888 0.00337 -0.0871 0.2703 1.0000
5.250 0.9718 0.00908 0.00353 -0.0860 0.2583 1.0000
5.500 0.9910 0.00941 0.00373 -0.0844 0.2337 1.0000
5.750 1.0110 0.00970 0.00395 -0.0829 0.2161 1.0000
6.000 1.0293 0.01009 0.00421 -0.0812 0.1927 1.0000
6.250 1.0310 0.01138 0.00498 -0.0766 0.0975 1.0000
6.500 1.0448 0.01203 0.00547 -0.0741 0.0641 1.0000
6.750 1.0563 0.01281 0.00602 -0.0712 0.0251 1.0000
7.000 1.0732 0.01323 0.00641 -0.0692 0.0153 1.0000
7.250 1.0907 0.01356 0.00674 -0.0673 0.0128 1.0000
7.500 1.1074 0.01391 0.00711 -0.0653 0.0108 1.0000
7.750 1.1247 0.01424 0.00748 -0.0634 0.0099 1.0000
8.000 1.1423 0.01458 0.00784 -0.0617 0.0092 1.0000
8.250 1.1591 0.01496 0.00825 -0.0598 0.0083 1.0000
8.500 1.1753 0.01540 0.00870 -0.0579 0.0076 1.0000
8.750 1.1905 0.01589 0.00923 -0.0559 0.0069 1.0000
9.000 1.2077 0.01628 0.00965 -0.0542 0.0066 1.0000
9.250 1.2236 0.01675 0.01016 -0.0524 0.0062 1.0000
9.500 1.2392 0.01725 0.01071 -0.0506 0.0059 1.0000
9.750 1.2541 0.01778 0.01128 -0.0488 0.0056 1.0000
10.000 1.2681 0.01838 0.01191 -0.0468 0.0053 1.0000
10.250 1.2801 0.01911 0.01269 -0.0447 0.0049 1.0000
10.500 1.2913 0.01990 0.01354 -0.0425 0.0048 1.0000
10.750 1.3057 0.02051 0.01420 -0.0409 0.0045 1.0000
11.000 1.3167 0.02135 0.01510 -0.0389 0.0044 1.0000
11.250 1.3283 0.02217 0.01598 -0.0371 0.0043 1.0000
11.500 1.3408 0.02296 0.01681 -0.0354 0.0040 1.0000
11.750 1.3518 0.02387 0.01779 -0.0338 0.0038 1.0000
12.000 1.3603 0.02499 0.01898 -0.0319 0.0037 1.0000
12.250 1.3697 0.02609 0.02013 -0.0303 0.0037 1.0000
12.500 1.3779 0.02731 0.02141 -0.0287 0.0034 1.0000
12.750 1.3833 0.02881 0.02298 -0.0270 0.0034 1.0000
13.000 1.3878 0.03046 0.02471 -0.0255 0.0033 1.0000
13.250 1.3890 0.03246 0.02681 -0.0239 0.0031 1.0000
13.500 1.3937 0.03425 0.02868 -0.0228 0.0031 1.0000
13.750 1.3959 0.03635 0.03087 -0.0217 0.0031 1.0000
14.000 1.4007 0.03826 0.03287 -0.0209 0.0030 1.0000
14.250 1.3982 0.04099 0.03570 -0.0200 0.0029 1.0000
14.500 1.4019 0.04316 0.03796 -0.0195 0.0029 1.0000
14.750 1.4022 0.04575 0.04066 -0.0190 0.0028 1.0000
15.000 1.3974 0.04903 0.04405 -0.0187 0.0028 1.0000
15.250 1.3973 0.05189 0.04701 -0.0186 0.0027 1.0000
15.500 1.3956 0.05506 0.05027 -0.0188 0.0027 1.0000
15.750 1.3950 0.05815 0.05345 -0.0190 0.0026 1.0000
16.000 1.3882 0.06215 0.05756 -0.0195 0.0026 1.0000
16.250 1.3812 0.06630 0.06182 -0.0202 0.0026 1.0000
16.500 1.3756 0.07033 0.06596 -0.0210 0.0025 1.0000
16.750 1.3727 0.07404 0.06975 -0.0218 0.0025 1.0000
17.000 1.3628 0.07883 0.07465 -0.0230 0.0025 1.0000
17.250 1.3494 0.08423 0.08018 -0.0244 0.0025 1.0000
17.500 1.3484 0.08790 0.08392 -0.0256 0.0024 1.0000
17.750 1.3368 0.09322 0.08936 -0.0272 0.0024 1.0000
18.000 1.3277 0.09828 0.09451 -0.0290 0.0024 1.0000
18.250 1.3187 0.10345 0.09979 -0.0308 0.0024 1.0000
18.500 1.3149 0.10784 0.10425 -0.0326 0.0023 1.0000
18.750 1.3004 0.11400 0.11053 -0.0350 0.0023 1.0000
19.000 1.2902 0.11958 0.11622 -0.0373 0.0023 1.0000
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Polar data table (+)
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