EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 67 AIRFOIL (e67-il) Reynolds number: 100,000 Max Cl/Cd: 60.87 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e67-il-100000.txt Download as CSV file: xf-e67-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 67 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4139 0.10288 0.09842 -0.0349 1.0000 0.1173
-8.250 -0.4513 0.10194 0.09764 -0.0348 1.0000 0.1183
-8.000 -0.4870 0.10082 0.09667 -0.0337 1.0000 0.1185
-7.750 -0.4439 0.09531 0.09109 -0.0298 1.0000 0.1214
-7.500 -0.4450 0.09332 0.08914 -0.0271 1.0000 0.1244
-7.250 -0.4610 0.09169 0.08759 -0.0247 1.0000 0.1273
-7.000 -0.4817 0.08977 0.08576 -0.0229 1.0000 0.1284
-6.750 -0.5328 0.08359 0.07960 -0.0366 1.0000 0.1331
-6.500 -0.5218 0.08116 0.07727 -0.0305 1.0000 0.1344
-6.250 -0.5393 0.05298 0.04790 -0.0517 1.0000 0.0632
-6.000 -0.5275 0.04822 0.04295 -0.0528 1.0000 0.0610
-5.750 -0.5101 0.04285 0.03706 -0.0549 1.0000 0.0597
-5.500 -0.4885 0.03866 0.03224 -0.0565 1.0000 0.0608
-5.250 -0.4645 0.03515 0.02807 -0.0575 1.0000 0.0618
-5.000 -0.4392 0.03222 0.02453 -0.0580 1.0000 0.0627
-4.750 -0.4137 0.02998 0.02172 -0.0581 1.0000 0.0646
-4.500 -0.3776 0.02799 0.01964 -0.0605 0.9964 0.0705
-4.250 -0.3383 0.02685 0.01831 -0.0631 0.9915 0.0835
-4.000 -0.2992 0.02595 0.01717 -0.0655 0.9864 0.1045
-3.750 -0.2611 0.02513 0.01646 -0.0681 0.9814 0.1342
-3.500 -0.2261 0.02452 0.01601 -0.0702 0.9755 0.1680
-3.250 -0.1858 0.02413 0.01575 -0.0731 0.9708 0.2141
-3.000 -0.1549 0.02365 0.01546 -0.0743 0.9637 0.2655
-2.750 -0.1154 0.02343 0.01553 -0.0771 0.9589 0.3364
-2.500 -0.0871 0.02316 0.01554 -0.0777 0.9513 0.4048
-2.250 -0.0494 0.02315 0.01582 -0.0798 0.9460 0.4882
-2.000 -0.0239 0.02310 0.01599 -0.0795 0.9379 0.5569
-1.750 0.0111 0.02322 0.01632 -0.0805 0.9324 0.6309
-1.500 0.0326 0.02327 0.01650 -0.0791 0.9237 0.6904
-1.250 0.0648 0.02342 0.01676 -0.0791 0.9182 0.7558
-1.000 0.0803 0.02345 0.01689 -0.0763 0.9088 0.8125
-0.750 0.1082 0.02342 0.01695 -0.0750 0.9034 0.8861
-0.500 0.1453 0.02326 0.01675 -0.0774 0.8938 1.0000
-0.250 0.1957 0.02348 0.01671 -0.0825 0.8892 1.0000
0.000 0.2224 0.02375 0.01680 -0.0833 0.8791 1.0000
0.250 0.2702 0.02391 0.01679 -0.0872 0.8748 1.0000
0.500 0.2939 0.02422 0.01698 -0.0872 0.8642 1.0000
0.750 0.3297 0.02443 0.01708 -0.0890 0.8570 1.0000
1.000 0.3642 0.02460 0.01716 -0.0905 0.8491 1.0000
1.250 0.3943 0.02485 0.01733 -0.0913 0.8403 1.0000
1.500 0.4352 0.02483 0.01726 -0.0935 0.8340 1.0000
1.750 0.4619 0.02510 0.01748 -0.0936 0.8241 1.0000
2.000 0.5068 0.02487 0.01723 -0.0963 0.8190 1.0000
2.250 0.5321 0.02513 0.01748 -0.0961 0.8084 1.0000
2.500 0.5805 0.02465 0.01700 -0.0991 0.8043 1.0000
2.750 0.6048 0.02488 0.01723 -0.0985 0.7931 1.0000
3.000 0.6574 0.02408 0.01648 -0.1020 0.7899 1.0000
3.250 0.6820 0.02422 0.01665 -0.1013 0.7785 1.0000
3.500 0.7386 0.02325 0.01576 -0.1053 0.7752 1.0000
3.750 0.7654 0.02321 0.01578 -0.1048 0.7636 1.0000
4.000 0.8002 0.02287 0.01550 -0.1054 0.7539 1.0000
4.250 0.8503 0.02191 0.01461 -0.1081 0.7474 1.0000
4.500 0.8814 0.02162 0.01443 -0.1080 0.7353 1.0000
4.750 0.9163 0.02119 0.01408 -0.1084 0.7234 1.0000
5.000 0.9537 0.02065 0.01361 -0.1092 0.7109 1.0000
5.250 0.9889 0.02019 0.01325 -0.1095 0.6967 1.0000
5.500 1.0215 0.01982 0.01295 -0.1095 0.6807 1.0000
5.750 1.0539 0.01947 0.01265 -0.1094 0.6631 1.0000
6.000 1.0871 0.01915 0.01237 -0.1095 0.6443 1.0000
6.250 1.1081 0.01919 0.01249 -0.1076 0.6217 1.0000
6.500 1.1340 0.01912 0.01243 -0.1065 0.5982 1.0000
6.750 1.1579 0.01914 0.01243 -0.1051 0.5723 1.0000
7.000 1.1766 0.01933 0.01261 -0.1029 0.5436 1.0000
7.250 1.1928 0.01962 0.01291 -0.1004 0.5123 1.0000
7.500 1.2065 0.02001 0.01327 -0.0975 0.4782 1.0000
7.750 1.2190 0.02052 0.01365 -0.0944 0.4422 1.0000
8.000 1.2276 0.02118 0.01421 -0.0909 0.4039 1.0000
8.250 1.2338 0.02199 0.01486 -0.0871 0.3649 1.0000
8.500 1.2366 0.02295 0.01562 -0.0829 0.3275 1.0000
8.750 1.2382 0.02407 0.01657 -0.0787 0.2897 1.0000
9.000 1.2388 0.02540 0.01768 -0.0747 0.2549 1.0000
9.250 1.2397 0.02685 0.01896 -0.0710 0.2212 1.0000
9.500 1.2403 0.02844 0.02038 -0.0674 0.1908 1.0000
9.750 1.2409 0.03018 0.02195 -0.0642 0.1638 1.0000
10.000 1.2415 0.03207 0.02365 -0.0611 0.1408 1.0000
10.250 1.2433 0.03399 0.02552 -0.0584 0.1195 1.0000
10.500 1.2456 0.03617 0.02750 -0.0559 0.1026 1.0000
10.750 1.2515 0.03836 0.02965 -0.0537 0.0880 1.0000
11.000 1.2631 0.04065 0.03185 -0.0521 0.0763 1.0000
11.250 1.2716 0.04260 0.03394 -0.0503 0.0678 1.0000
11.500 1.2908 0.04505 0.03652 -0.0493 0.0607 1.0000
11.750 1.3097 0.04734 0.03885 -0.0485 0.0556 1.0000
12.000 1.3302 0.05044 0.04213 -0.0479 0.0511 1.0000
12.250 1.3366 0.05291 0.04490 -0.0461 0.0480 1.0000
12.500 1.3457 0.05581 0.04804 -0.0448 0.0459 1.0000
12.750 1.3558 0.05908 0.05147 -0.0437 0.0442 1.0000
13.000 1.3675 0.06472 0.05733 -0.0434 0.0425 1.0000
13.250 1.3534 0.06805 0.06099 -0.0409 0.0421 1.0000
13.500 1.3378 0.07168 0.06497 -0.0389 0.0418 1.0000
13.750 1.3204 0.07579 0.06941 -0.0376 0.0416 1.0000
14.000 1.3017 0.08038 0.07430 -0.0369 0.0414 1.0000
14.250 1.2811 0.08543 0.07964 -0.0370 0.0413 1.0000
14.500 1.2595 0.09100 0.08549 -0.0378 0.0413 1.0000
14.750 1.2372 0.09711 0.09184 -0.0395 0.0414 1.0000
15.000 1.2150 0.10374 0.09869 -0.0420 0.0417 1.0000
15.250 1.1932 0.11092 0.10605 -0.0452 0.0420 1.0000
15.500 1.1723 0.11862 0.11392 -0.0491 0.0423 1.0000
15.750 1.0579 0.15030 0.14612 -0.0732 0.0510 1.0000
16.000 1.0427 0.16105 0.15680 -0.0792 0.0523 1.0000
16.250 1.0399 0.16807 0.16380 -0.0822 0.0531 1.0000
16.500 1.0234 0.18616 0.18185 -0.0906 0.0650 1.0000
16.750 0.7895 0.19812 0.19437 -0.0925 0.1150 1.0000
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