Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Davis AIRFOIL (davis-il) Reynolds number: 100,000 Max Cl/Cd: 54.01 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-davis-il-100000.txt Download as CSV file: xf-davis-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3617 0.10195 0.09722 -0.0362 1.0000 0.1214
-8.750 -0.3931 0.10097 0.09640 -0.0377 1.0000 0.1248
-8.500 -0.4276 0.10020 0.09581 -0.0376 1.0000 0.1253
-8.250 -0.3982 0.09451 0.09008 -0.0346 1.0000 0.1278
-8.000 -0.3930 0.09196 0.08756 -0.0321 1.0000 0.1305
-7.750 -0.4029 0.09000 0.08568 -0.0300 1.0000 0.1337
-7.500 -0.4249 0.08854 0.08434 -0.0276 1.0000 0.1360
-7.000 -0.4973 0.08389 0.07989 -0.0315 1.0000 0.1404
-6.750 -0.4882 0.08095 0.07702 -0.0265 1.0000 0.1418
-6.500 -0.4851 0.07891 0.07502 -0.0227 1.0000 0.1444
-6.250 -0.4900 0.07662 0.07275 -0.0215 1.0000 0.1490
-6.000 -0.5255 0.04848 0.04330 -0.0406 1.0000 0.0731
-5.750 -0.5151 0.04415 0.03855 -0.0401 1.0000 0.0701
-5.500 -0.5030 0.04010 0.03403 -0.0396 1.0000 0.0698
-5.250 -0.4882 0.03649 0.02987 -0.0388 1.0000 0.0696
-5.000 -0.4540 0.03260 0.02525 -0.0410 0.9954 0.0692
-4.750 -0.4189 0.03006 0.02198 -0.0427 0.9900 0.0709
-4.500 -0.3831 0.02811 0.01983 -0.0448 0.9849 0.0762
-4.250 -0.3483 0.02670 0.01811 -0.0462 0.9789 0.0809
-4.000 -0.3116 0.02550 0.01676 -0.0480 0.9731 0.0890
-3.750 -0.2769 0.02465 0.01574 -0.0493 0.9671 0.0989
-3.500 -0.2431 0.02395 0.01516 -0.0507 0.9604 0.1165
-3.250 -0.2076 0.02310 0.01448 -0.0523 0.9545 0.1592
-3.000 -0.1765 0.02279 0.01440 -0.0533 0.9463 0.2357
-2.750 -0.1416 0.02275 0.01434 -0.0550 0.9394 0.2766
-2.500 -0.1098 0.02270 0.01436 -0.0562 0.9314 0.3160
-2.250 -0.0778 0.02262 0.01440 -0.0573 0.9240 0.3563
-2.000 -0.0438 0.02241 0.01431 -0.0586 0.9163 0.3997
-1.750 -0.0130 0.02212 0.01419 -0.0593 0.9080 0.4480
-1.500 0.0236 0.02161 0.01399 -0.0609 0.9013 0.5205
-1.250 0.1205 0.02018 0.01393 -0.0734 0.9020 1.0000
-1.000 0.1550 0.02026 0.01370 -0.0749 0.8920 1.0000
-0.750 0.2059 0.02012 0.01329 -0.0791 0.8854 1.0000
-0.500 0.2369 0.02009 0.01308 -0.0796 0.8738 1.0000
-0.250 0.2751 0.01998 0.01281 -0.0814 0.8644 1.0000
0.000 0.3240 0.01963 0.01231 -0.0849 0.8576 1.0000
0.250 0.3582 0.01945 0.01202 -0.0858 0.8469 1.0000
0.500 0.4132 0.01884 0.01131 -0.0902 0.8419 1.0000
0.750 0.4414 0.01874 0.01114 -0.0900 0.8304 1.0000
1.000 0.4768 0.01851 0.01085 -0.0909 0.8216 1.0000
1.250 0.5178 0.01811 0.01040 -0.0928 0.8139 1.0000
1.500 0.5461 0.01801 0.01026 -0.0925 0.8026 1.0000
1.750 0.5817 0.01773 0.00994 -0.0933 0.7930 1.0000
2.000 0.6211 0.01733 0.00950 -0.0948 0.7840 1.0000
2.250 0.6488 0.01724 0.00940 -0.0942 0.7713 1.0000
2.500 0.6777 0.01715 0.00929 -0.0939 0.7586 1.0000
2.750 0.7070 0.01707 0.00919 -0.0936 0.7457 1.0000
3.000 0.7360 0.01702 0.00912 -0.0933 0.7322 1.0000
3.250 0.7639 0.01702 0.00910 -0.0928 0.7180 1.0000
3.500 0.7903 0.01706 0.00912 -0.0920 0.7028 1.0000
3.750 0.8154 0.01713 0.00920 -0.0910 0.6866 1.0000
4.000 0.8398 0.01720 0.00926 -0.0898 0.6696 1.0000
4.250 0.8647 0.01724 0.00929 -0.0888 0.6519 1.0000
4.500 0.8889 0.01728 0.00931 -0.0876 0.6330 1.0000
4.750 0.9095 0.01741 0.00946 -0.0858 0.6116 1.0000
5.000 0.9352 0.01750 0.00947 -0.0849 0.5917 1.0000
5.250 0.9567 0.01780 0.00974 -0.0834 0.5702 1.0000
5.500 0.9812 0.01817 0.01004 -0.0825 0.5507 1.0000
5.750 1.0068 0.01864 0.01044 -0.0819 0.5330 1.0000
6.000 1.0302 0.01920 0.01097 -0.0810 0.5163 1.0000
6.250 1.0539 0.01979 0.01157 -0.0802 0.5016 1.0000
6.500 1.0770 0.02039 0.01226 -0.0793 0.4885 1.0000
6.750 1.0979 0.02097 0.01295 -0.0781 0.4755 1.0000
7.000 1.1181 0.02136 0.01340 -0.0766 0.4603 1.0000
7.250 1.1353 0.02152 0.01355 -0.0743 0.4415 1.0000
7.500 1.1472 0.02161 0.01372 -0.0712 0.4204 1.0000
7.750 1.1612 0.02172 0.01380 -0.0684 0.3999 1.0000
8.000 1.1697 0.02195 0.01408 -0.0649 0.3766 1.0000
8.250 1.1794 0.02234 0.01442 -0.0616 0.3538 1.0000
8.500 1.1852 0.02282 0.01491 -0.0577 0.3284 1.0000
8.750 1.1848 0.02339 0.01548 -0.0529 0.2974 1.0000
9.000 1.1731 0.02405 0.01616 -0.0462 0.2440 1.0000
9.250 1.1475 0.02644 0.01761 -0.0389 0.1231 1.0000
9.500 1.1304 0.02942 0.02011 -0.0335 0.0872 1.0000
9.750 1.1232 0.03172 0.02237 -0.0295 0.0756 1.0000
10.000 1.1178 0.03391 0.02459 -0.0262 0.0685 1.0000
10.250 1.1158 0.03597 0.02677 -0.0235 0.0633 1.0000
10.500 1.1151 0.03805 0.02891 -0.0211 0.0589 1.0000
10.750 1.1142 0.04032 0.03117 -0.0189 0.0564 1.0000
11.000 1.1230 0.04223 0.03310 -0.0170 0.0539 1.0000
11.250 1.1402 0.04384 0.03478 -0.0155 0.0512 1.0000
11.500 1.1586 0.04550 0.03646 -0.0144 0.0482 1.0000
11.750 1.2036 0.04801 0.03882 -0.0151 0.0445 1.0000
12.000 1.2301 0.05050 0.04159 -0.0146 0.0437 1.0000
12.250 1.2516 0.05348 0.04487 -0.0140 0.0433 1.0000
12.500 1.2626 0.05675 0.04846 -0.0126 0.0432 1.0000
12.750 1.2652 0.06006 0.05209 -0.0109 0.0432 1.0000
13.000 1.2615 0.06345 0.05578 -0.0090 0.0432 1.0000
13.250 1.2512 0.06677 0.05941 -0.0071 0.0430 1.0000
13.500 1.2402 0.07048 0.06339 -0.0057 0.0430 1.0000
13.750 1.2275 0.07457 0.06773 -0.0047 0.0433 1.0000
14.000 1.2107 0.07879 0.07221 -0.0042 0.0433 1.0000
14.250 1.1913 0.08342 0.07708 -0.0043 0.0433 1.0000
14.500 1.1731 0.08849 0.08237 -0.0051 0.0435 1.0000
14.750 1.1534 0.09395 0.08804 -0.0065 0.0437 1.0000
15.000 1.1342 0.09993 0.09419 -0.0084 0.0441 1.0000
15.250 1.1175 0.10641 0.10082 -0.0107 0.0445 1.0000
15.500 1.1013 0.11313 0.10770 -0.0133 0.0449 1.0000
15.750 0.8005 0.13384 0.12951 -0.0328 0.0522 1.0000
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