davissm (davissm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: davissm (davissm-il) Reynolds number: 100,000 Max Cl/Cd: 70.21 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-davissm-il-100000.txt Download as CSV file: xf-davissm-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: davissm
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
------ -------- --------- --------- -------- -------- --------
-5.750 -0.3515 0.09520 0.09092 -0.0249 1.0000 0.0500
-5.500 -0.3508 0.09195 0.08771 -0.0221 1.0000 0.0514
-5.250 -0.3451 0.08924 0.08502 -0.0221 1.0000 0.0529
-5.000 -0.3358 0.08655 0.08231 -0.0236 1.0000 0.0546
-4.750 -0.3226 0.08377 0.07953 -0.0262 1.0000 0.0567
-4.500 -0.3019 0.08095 0.07668 -0.0312 1.0000 0.0596
-4.250 -0.2305 0.07882 0.07428 -0.0527 1.0000 0.0625
-4.000 -0.2359 0.07400 0.06958 -0.0479 1.0000 0.0635
-3.750 -0.2166 0.06990 0.06549 -0.0486 0.9968 0.0660
-3.500 -0.1138 0.06682 0.06189 -0.0732 0.9916 0.0766
-3.250 -0.1104 0.06125 0.05652 -0.0698 0.9883 0.0793
-3.000 -0.0416 0.05762 0.05257 -0.0837 0.9833 0.0917
-2.750 -0.0174 0.05395 0.04896 -0.0849 0.9793 0.0965
-2.500 0.0369 0.05045 0.04525 -0.0939 0.9749 0.1088
-2.250 0.0844 0.04745 0.04206 -0.1007 0.9700 0.1235
-2.000 0.1373 0.04481 0.03919 -0.1084 0.9665 0.1510
-0.500 0.4420 0.03035 0.02225 -0.1395 0.9406 0.1116
-0.250 0.4915 0.02909 0.02039 -0.1431 0.9369 0.1040
0.000 0.5264 0.02820 0.01932 -0.1446 0.9290 0.1082
0.250 0.5740 0.02714 0.01809 -0.1483 0.9251 0.1097
0.500 0.6069 0.02669 0.01761 -0.1493 0.9167 0.1145
0.750 0.6521 0.02596 0.01690 -0.1526 0.9117 0.1315
1.000 0.6901 0.02551 0.01648 -0.1545 0.9043 0.1509
1.250 0.7346 0.02343 0.01596 -0.1576 0.8992 1.0000
1.500 0.7841 0.02303 0.01530 -0.1615 0.8953 1.0000
1.750 0.8121 0.02323 0.01541 -0.1615 0.8840 1.0000
2.250 0.8875 0.02289 0.01501 -0.1647 0.8684 1.0000
2.500 0.9166 0.02296 0.01509 -0.1647 0.8577 1.0000
2.750 0.9596 0.02241 0.01456 -0.1669 0.8522 1.0000
3.000 0.9863 0.02248 0.01467 -0.1663 0.8403 1.0000
3.250 1.0150 0.02244 0.01473 -0.1660 0.8291 1.0000
3.500 1.0484 0.02213 0.01449 -0.1663 0.8197 1.0000
3.750 1.0850 0.02134 0.01377 -0.1665 0.8091 1.0000
4.000 1.1116 0.02077 0.01327 -0.1648 0.7913 1.0000
4.250 1.1397 0.02012 0.01274 -0.1633 0.7731 1.0000
4.500 1.1685 0.01955 0.01225 -0.1621 0.7556 1.0000
4.750 1.1957 0.01901 0.01177 -0.1605 0.7344 1.0000
5.000 1.2214 0.01861 0.01144 -0.1587 0.7104 1.0000
5.250 1.2447 0.01828 0.01119 -0.1565 0.6790 1.0000
5.500 1.2651 0.01810 0.01100 -0.1536 0.6354 1.0000
5.750 1.2799 0.01823 0.01089 -0.1496 0.5615 1.0000
6.000 1.2796 0.01970 0.01127 -0.1429 0.3874 1.0000
6.250 1.2646 0.02356 0.01320 -0.1359 0.1428 1.0000
6.500 1.2691 0.02585 0.01516 -0.1319 0.1109 1.0000
6.750 1.2742 0.02781 0.01712 -0.1279 0.0982 1.0000
7.000 1.2804 0.02967 0.01896 -0.1242 0.0878 1.0000
7.250 1.2922 0.03156 0.02092 -0.1212 0.0799 1.0000
7.500 1.3206 0.03465 0.02369 -0.1214 0.0720 1.0000
7.750 1.3443 0.03615 0.02542 -0.1203 0.0657 1.0000
8.000 1.3809 0.03907 0.02830 -0.1216 0.0611 1.0000
8.250 1.4235 0.04408 0.03346 -0.1239 0.0587 1.0000
8.500 1.4402 0.04569 0.03556 -0.1213 0.0565 1.0000
8.750 1.4592 0.04839 0.03871 -0.1193 0.0546 1.0000
9.000 1.4784 0.05221 0.04298 -0.1174 0.0550 1.0000
9.250 1.4939 0.05668 0.04788 -0.1152 0.0563 1.0000
9.500 1.5192 0.06361 0.05499 -0.1151 0.0596 1.0000
19.000 0.8809 0.23584 0.23172 -0.1162 0.0693 1.0000
19.250 0.8809 0.23922 0.23511 -0.1177 0.0665 1.0000
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Polar data table (+)
Polar graphs
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