EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 66 AIRFOIL (e66-il) Reynolds number: 200,000 Max Cl/Cd: 86.76 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e66-il-200000-n5.txt Download as CSV file: xf-e66-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 66 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2983 0.13441 0.13101 -0.0369 1.0000 0.0243
-11.250 -0.3771 0.12624 0.12252 -0.0372 1.0000 0.0179
-11.000 -0.3717 0.12385 0.12014 -0.0361 1.0000 0.0170
-10.750 -0.3711 0.12083 0.11716 -0.0360 1.0000 0.0162
-10.500 -0.3726 0.11745 0.11381 -0.0360 1.0000 0.0155
-10.000 -0.3888 0.10703 0.10348 -0.0375 1.0000 0.0131
-9.750 -0.3928 0.10392 0.10042 -0.0371 1.0000 0.0130
-9.500 -0.3983 0.10076 0.09731 -0.0367 1.0000 0.0129
-9.250 -0.3995 0.09711 0.09369 -0.0377 0.9993 0.0128
-9.000 -0.3921 0.09198 0.08858 -0.0421 0.9966 0.0127
-8.750 -0.3863 0.08643 0.08305 -0.0471 0.9936 0.0126
-8.500 -0.3824 0.08089 0.07753 -0.0520 0.9892 0.0125
-8.250 -0.3833 0.07316 0.06984 -0.0596 0.9841 0.0125
-8.000 -0.3882 0.06583 0.06255 -0.0668 0.9750 0.0123
-7.750 -0.4002 0.03967 0.03571 -0.0986 0.9605 0.0116
-7.500 -0.3883 0.03239 0.02763 -0.1039 0.9530 0.0119
-7.250 -0.3628 0.02789 0.02242 -0.1073 0.9493 0.0123
-7.000 -0.3319 0.02494 0.01884 -0.1098 0.9472 0.0130
-6.750 -0.3065 0.02341 0.01712 -0.1106 0.9431 0.0142
-6.500 -0.2794 0.02242 0.01597 -0.1113 0.9389 0.0155
-6.250 -0.2483 0.02090 0.01416 -0.1126 0.9363 0.0167
-6.000 -0.2153 0.01952 0.01252 -0.1140 0.9344 0.0179
-5.750 -0.1816 0.01820 0.01106 -0.1159 0.9329 0.0197
-5.500 -0.1579 0.01757 0.01034 -0.1154 0.9271 0.0223
-5.250 -0.1268 0.01676 0.00941 -0.1164 0.9239 0.0261
-5.000 -0.0933 0.01609 0.00866 -0.1178 0.9217 0.0305
-4.750 -0.0585 0.01539 0.00790 -0.1195 0.9199 0.0369
-4.500 -0.0287 0.01493 0.00734 -0.1200 0.9161 0.0440
-4.250 0.0000 0.01442 0.00680 -0.1203 0.9114 0.0554
-4.000 0.0336 0.01389 0.00630 -0.1217 0.9087 0.0724
-3.750 0.0691 0.01344 0.00589 -0.1235 0.9066 0.0976
-3.500 0.1060 0.01302 0.00551 -0.1255 0.9048 0.1266
-3.250 0.1300 0.01275 0.00534 -0.1249 0.8977 0.1592
-3.000 0.1640 0.01239 0.00508 -0.1263 0.8944 0.1990
-2.750 0.2000 0.01205 0.00480 -0.1281 0.8918 0.2377
-2.500 0.2281 0.01182 0.00466 -0.1282 0.8858 0.2746
-2.250 0.2599 0.01156 0.00448 -0.1291 0.8809 0.3165
-2.000 0.2954 0.01125 0.00428 -0.1307 0.8775 0.3665
-1.750 0.3230 0.01107 0.00421 -0.1307 0.8708 0.4125
-1.500 0.3552 0.01084 0.00410 -0.1316 0.8655 0.4625
-1.250 0.3877 0.01062 0.00399 -0.1325 0.8604 0.5123
-1.000 0.4154 0.01047 0.00397 -0.1324 0.8529 0.5597
-0.750 0.4492 0.01026 0.00386 -0.1334 0.8481 0.6099
-0.500 0.4741 0.01017 0.00390 -0.1327 0.8392 0.6544
-0.250 0.5048 0.01002 0.00383 -0.1330 0.8328 0.6999
0.000 0.5297 0.00994 0.00385 -0.1321 0.8237 0.7421
0.250 0.5557 0.00984 0.00383 -0.1313 0.8153 0.7849
0.500 0.5812 0.00974 0.00379 -0.1304 0.8066 0.8274
0.750 0.6031 0.00967 0.00377 -0.1287 0.7962 0.8721
1.000 0.6280 0.00957 0.00370 -0.1276 0.7864 0.9247
1.250 0.6638 0.00949 0.00358 -0.1291 0.7765 1.0000
1.500 0.6918 0.00956 0.00360 -0.1291 0.7648 1.0000
1.750 0.7199 0.00963 0.00362 -0.1292 0.7527 1.0000
2.000 0.7480 0.00972 0.00365 -0.1291 0.7399 1.0000
2.250 0.7757 0.00982 0.00371 -0.1291 0.7262 1.0000
2.500 0.8030 0.00993 0.00377 -0.1289 0.7116 1.0000
2.750 0.8299 0.01006 0.00384 -0.1286 0.6958 1.0000
3.000 0.8563 0.01021 0.00395 -0.1282 0.6793 1.0000
3.250 0.8824 0.01038 0.00405 -0.1278 0.6618 1.0000
3.500 0.9074 0.01057 0.00420 -0.1272 0.6425 1.0000
3.750 0.9322 0.01078 0.00434 -0.1265 0.6220 1.0000
4.000 0.9561 0.01102 0.00454 -0.1257 0.5997 1.0000
4.250 0.9793 0.01130 0.00473 -0.1247 0.5755 1.0000
4.500 1.0018 0.01159 0.00495 -0.1236 0.5496 1.0000
4.750 1.0235 0.01193 0.00520 -0.1224 0.5221 1.0000
5.000 1.0444 0.01231 0.00550 -0.1210 0.4932 1.0000
5.250 1.0643 0.01274 0.00582 -0.1195 0.4625 1.0000
5.500 1.0832 0.01321 0.00617 -0.1179 0.4300 1.0000
5.750 1.1016 0.01373 0.00656 -0.1161 0.3958 1.0000
6.000 1.1186 0.01431 0.00700 -0.1143 0.3601 1.0000
6.250 1.1355 0.01492 0.00750 -0.1124 0.3247 1.0000
6.500 1.1521 0.01556 0.00801 -0.1105 0.2912 1.0000
6.750 1.1685 0.01622 0.00855 -0.1086 0.2607 1.0000
7.000 1.1838 0.01690 0.00913 -0.1066 0.2310 1.0000
7.250 1.1981 0.01765 0.00974 -0.1044 0.2004 1.0000
7.500 1.2114 0.01849 0.01043 -0.1021 0.1674 1.0000
7.750 1.2244 0.01938 0.01118 -0.0999 0.1373 1.0000
8.000 1.2382 0.02023 0.01194 -0.0978 0.1140 1.0000
8.250 1.2523 0.02107 0.01272 -0.0959 0.0958 1.0000
8.500 1.2658 0.02196 0.01356 -0.0938 0.0797 1.0000
8.750 1.2794 0.02285 0.01443 -0.0918 0.0659 1.0000
9.000 1.2922 0.02380 0.01538 -0.0898 0.0548 1.0000
9.500 1.3157 0.02588 0.01754 -0.0855 0.0381 1.0000
9.750 1.3261 0.02705 0.01876 -0.0833 0.0326 1.0000
10.000 1.3358 0.02827 0.02003 -0.0811 0.0283 1.0000
10.250 1.3435 0.02967 0.02152 -0.0788 0.0256 1.0000
10.500 1.3530 0.03096 0.02294 -0.0767 0.0233 1.0000
10.750 1.3614 0.03235 0.02442 -0.0747 0.0212 1.0000
11.000 1.3645 0.03422 0.02636 -0.0724 0.0193 1.0000
11.250 1.3723 0.03575 0.02804 -0.0706 0.0181 1.0000
11.500 1.3791 0.03740 0.02985 -0.0688 0.0167 1.0000
11.750 1.3853 0.03912 0.03169 -0.0672 0.0153 1.0000
12.000 1.3873 0.04131 0.03397 -0.0655 0.0144 1.0000
12.250 1.3857 0.04396 0.03674 -0.0637 0.0137 1.0000
12.500 1.3888 0.04625 0.03922 -0.0623 0.0131 1.0000
12.750 1.3905 0.04878 0.04192 -0.0611 0.0124 1.0000
13.000 1.3915 0.05144 0.04475 -0.0601 0.0118 1.0000
13.250 1.3922 0.05419 0.04764 -0.0593 0.0111 1.0000
13.500 1.3919 0.05714 0.05072 -0.0588 0.0106 1.0000
13.750 1.3892 0.06049 0.05420 -0.0585 0.0101 1.0000
14.000 1.3817 0.06465 0.05846 -0.0585 0.0097 1.0000
14.250 1.3803 0.06819 0.06223 -0.0586 0.0093 1.0000
14.500 1.3771 0.07213 0.06639 -0.0590 0.0089 1.0000
14.750 1.3718 0.07652 0.07102 -0.0598 0.0086 1.0000
15.000 1.3654 0.08123 0.07593 -0.0608 0.0084 1.0000
15.250 1.3581 0.08627 0.08117 -0.0623 0.0082 1.0000
15.500 1.3497 0.09168 0.08677 -0.0642 0.0080 1.0000
15.750 1.3404 0.09743 0.09272 -0.0665 0.0079 1.0000
16.000 1.3304 0.10354 0.09903 -0.0692 0.0077 1.0000
16.250 1.3197 0.11001 0.10568 -0.0724 0.0076 1.0000
16.500 1.3083 0.11684 0.11270 -0.0760 0.0076 1.0000
16.750 1.2963 0.12405 0.12009 -0.0801 0.0075 1.0000
17.000 1.2834 0.13172 0.12795 -0.0846 0.0075 1.0000
17.250 1.2696 0.13992 0.13634 -0.0897 0.0074 1.0000
17.500 1.2546 0.14880 0.14540 -0.0954 0.0075 1.0000
17.750 1.2375 0.15868 0.15548 -0.1018 0.0075 1.0000
18.000 1.2156 0.17059 0.16758 -0.1097 0.0077 1.0000
18.250 1.1812 0.18800 0.18516 -0.1208 0.0081 1.0000
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Polar data table (+)
Polar graphs
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