Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Davis AIRFOIL (davis-il) Reynolds number: 50,000 Max Cl/Cd: 22.18 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-davis-il-50000.txt Download as CSV file: xf-davis-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3662 0.10925 0.10265 -0.0292 1.0000 0.2424
-8.500 -0.3460 0.10434 0.09773 -0.0275 1.0000 0.2514
-8.250 -0.3711 0.10416 0.09773 -0.0266 1.0000 0.2574
-8.000 -0.3530 0.09951 0.09306 -0.0248 1.0000 0.2665
-7.750 -0.3869 0.09992 0.09370 -0.0228 1.0000 0.2727
-7.500 -0.3654 0.09497 0.08871 -0.0212 1.0000 0.2803
-7.250 -0.3996 0.09525 0.08922 -0.0181 1.0000 0.2875
-7.000 -0.3865 0.09105 0.08502 -0.0163 1.0000 0.2939
-6.750 -0.4155 0.09074 0.08489 -0.0126 1.0000 0.3017
-6.500 -0.4190 0.08783 0.08206 -0.0101 1.0000 0.3072
-6.250 -0.4420 0.08685 0.08122 -0.0078 1.0000 0.3173
-6.000 -0.4373 0.08350 0.07792 -0.0051 1.0000 0.3241
-5.750 -0.4864 0.06760 0.06162 -0.0320 1.0000 0.1698
-5.500 -0.4816 0.05836 0.05193 -0.0363 1.0000 0.1411
-5.250 -0.4712 0.05418 0.04755 -0.0361 1.0000 0.1361
-5.000 -0.4594 0.04917 0.04214 -0.0370 1.0000 0.1320
-4.750 -0.4444 0.04504 0.03752 -0.0375 1.0000 0.1325
-4.500 -0.4267 0.04151 0.03342 -0.0376 1.0000 0.1355
-4.250 -0.4066 0.03817 0.02940 -0.0375 1.0000 0.1377
-4.000 -0.3866 0.03577 0.02662 -0.0368 1.0000 0.1433
-3.750 -0.3660 0.03407 0.02449 -0.0360 1.0000 0.1534
-3.500 -0.3457 0.03247 0.02277 -0.0350 1.0000 0.1639
-3.250 -0.3250 0.03117 0.02124 -0.0341 1.0000 0.1810
-3.000 -0.3049 0.03008 0.02014 -0.0329 1.0000 0.2062
-2.750 -0.2842 0.02896 0.01897 -0.0317 1.0000 0.2576
-2.500 -0.2667 0.02826 0.01850 -0.0302 1.0000 0.3173
-2.250 -0.2524 0.02819 0.01868 -0.0283 1.0000 0.3688
-2.000 -0.2373 0.02808 0.01869 -0.0264 1.0000 0.4163
-1.750 -0.2175 0.02778 0.01834 -0.0255 1.0000 0.4566
-1.500 -0.1957 0.02746 0.01800 -0.0250 1.0000 0.5004
-1.250 -0.1736 0.02703 0.01776 -0.0245 1.0000 0.5564
-1.000 -0.1524 0.02637 0.01770 -0.0234 1.0000 0.6498
-0.750 -0.1055 0.02553 0.01733 -0.0282 1.0000 1.0000
-0.500 -0.0856 0.02616 0.01747 -0.0285 1.0000 1.0000
-0.250 -0.0675 0.02682 0.01779 -0.0283 1.0000 1.0000
0.000 -0.0226 0.02822 0.01880 -0.0332 0.9884 1.0000
0.250 0.0213 0.02957 0.01980 -0.0377 0.9753 1.0000
0.500 0.0698 0.03091 0.02086 -0.0428 0.9591 1.0000
0.750 0.1190 0.03209 0.02178 -0.0477 0.9407 1.0000
1.000 0.1597 0.03291 0.02242 -0.0510 0.9218 1.0000
1.250 0.1990 0.03374 0.02310 -0.0538 0.9055 1.0000
1.500 0.2351 0.03454 0.02378 -0.0561 0.8907 1.0000
1.750 0.2703 0.03530 0.02445 -0.0581 0.8760 1.0000
2.000 0.3052 0.03601 0.02509 -0.0600 0.8611 1.0000
2.250 0.3405 0.03667 0.02569 -0.0617 0.8457 1.0000
2.500 0.3768 0.03725 0.02623 -0.0635 0.8301 1.0000
2.750 0.4140 0.03776 0.02673 -0.0652 0.8144 1.0000
3.000 0.4539 0.03811 0.02710 -0.0671 0.7986 1.0000
3.250 0.4955 0.03833 0.02735 -0.0690 0.7829 1.0000
3.500 0.5161 0.03894 0.02800 -0.0680 0.7631 1.0000
3.750 0.5504 0.03921 0.02831 -0.0687 0.7454 1.0000
4.000 0.5890 0.03925 0.02842 -0.0697 0.7284 1.0000
4.250 0.6292 0.03911 0.02839 -0.0706 0.7121 1.0000
4.500 0.6689 0.03890 0.02827 -0.0714 0.6964 1.0000
4.750 0.7084 0.03862 0.02810 -0.0720 0.6811 1.0000
5.000 0.7450 0.03854 0.02815 -0.0724 0.6659 1.0000
5.250 0.7779 0.03864 0.02837 -0.0724 0.6509 1.0000
5.500 0.8053 0.03905 0.02888 -0.0719 0.6364 1.0000
5.750 0.8271 0.03981 0.02977 -0.0709 0.6223 1.0000
6.000 0.8446 0.04087 0.03093 -0.0696 0.6086 1.0000
6.250 0.8567 0.04233 0.03248 -0.0679 0.5956 1.0000
6.500 0.8616 0.04436 0.03459 -0.0657 0.5835 1.0000
6.750 0.9294 0.04261 0.03315 -0.0688 0.5766 1.0000
7.000 0.9114 0.04615 0.03672 -0.0649 0.5638 1.0000
7.250 0.8732 0.05159 0.04210 -0.0606 0.5515 1.0000
7.500 0.8474 0.05708 0.04757 -0.0589 0.5417 1.0000
7.750 0.8704 0.05838 0.04904 -0.0585 0.5342 1.0000
8.000 0.8277 0.06546 0.05602 -0.0571 0.5258 1.0000
8.250 0.8410 0.06790 0.05860 -0.0569 0.5196 1.0000
8.500 0.8266 0.07273 0.06345 -0.0565 0.5145 1.0000
8.750 0.8071 0.07786 0.06859 -0.0563 0.5102 1.0000
9.000 0.8452 0.07849 0.06948 -0.0562 0.5022 1.0000
9.250 0.8147 0.08459 0.07554 -0.0563 0.4996 1.0000
9.500 0.8010 0.08920 0.08020 -0.0564 0.4959 1.0000
9.750 0.8153 0.09108 0.08225 -0.0556 0.4818 1.0000
10.000 0.8621 0.08912 0.08066 -0.0530 0.4554 1.0000
10.250 0.8692 0.09109 0.08279 -0.0518 0.4388 1.0000
10.500 0.9235 0.08724 0.07942 -0.0480 0.4119 1.0000
10.750 0.9336 0.08820 0.08065 -0.0459 0.3904 1.0000
11.000 1.0928 0.04928 0.03959 -0.0164 0.1264 1.0000
11.250 1.0965 0.05203 0.04219 -0.0145 0.1133 1.0000
11.500 1.1274 0.05383 0.04390 -0.0127 0.1011 1.0000
11.750 1.1839 0.05624 0.04626 -0.0127 0.0902 1.0000
12.000 1.2009 0.05925 0.04963 -0.0117 0.0857 1.0000
12.250 1.2256 0.06280 0.05347 -0.0113 0.0827 1.0000
12.500 1.2411 0.06687 0.05782 -0.0105 0.0814 1.0000
12.750 1.2410 0.07083 0.06210 -0.0091 0.0810 1.0000
13.000 1.2307 0.07479 0.06639 -0.0074 0.0811 1.0000
13.250 1.2116 0.07890 0.07083 -0.0061 0.0814 1.0000
13.500 1.1765 0.08372 0.07603 -0.0056 0.0826 1.0000
13.750 1.1410 0.08970 0.08232 -0.0068 0.0837 1.0000
14.000 1.1033 0.09698 0.08987 -0.0097 0.0851 1.0000
14.250 1.0637 0.10581 0.09887 -0.0144 0.0868 1.0000
14.500 1.0271 0.11585 0.10903 -0.0203 0.0888 1.0000
14.750 1.0012 0.12563 0.11885 -0.0257 0.0906 1.0000
15.000 0.9870 0.13412 0.12735 -0.0297 0.0918 1.0000
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Polar data table (+)
Polar graphs
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