E180 (8.59%) (e180-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E180 (8.59%) (e180-il) Reynolds number: 50,000 Max Cl/Cd: 36.19 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e180-il-50000-n5.txt Download as CSV file: xf-e180-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E180 (8.59%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5024 0.09449 0.08812 -0.0097 1.0000 0.0415
-8.250 -0.4981 0.09050 0.08419 -0.0112 1.0000 0.0407
-8.000 -0.4960 0.08632 0.08008 -0.0135 1.0000 0.0399
-7.750 -0.4951 0.08201 0.07584 -0.0166 1.0000 0.0393
-7.500 -0.4920 0.07734 0.07121 -0.0203 1.0000 0.0385
-7.250 -0.4884 0.07229 0.06616 -0.0240 1.0000 0.0378
-7.000 -0.4835 0.06726 0.06109 -0.0274 1.0000 0.0371
-6.750 -0.4771 0.06226 0.05599 -0.0303 1.0000 0.0366
-6.500 -0.4691 0.05737 0.05093 -0.0327 1.0000 0.0366
-6.250 -0.4589 0.05276 0.04607 -0.0344 1.0000 0.0369
-6.000 -0.4467 0.04842 0.04140 -0.0355 1.0000 0.0377
-5.750 -0.4327 0.04446 0.03701 -0.0360 1.0000 0.0384
-5.500 -0.4177 0.04079 0.03288 -0.0359 1.0000 0.0394
-5.250 -0.4025 0.03760 0.02924 -0.0351 1.0000 0.0401
-5.000 -0.3889 0.03482 0.02602 -0.0336 1.0000 0.0406
-4.750 -0.3763 0.03251 0.02327 -0.0315 1.0000 0.0413
-4.500 -0.3594 0.03039 0.02067 -0.0301 0.9973 0.0422
-4.250 -0.3231 0.02772 0.01775 -0.0323 0.9839 0.0454
-4.000 -0.2844 0.02596 0.01555 -0.0344 0.9719 0.0545
-3.750 -0.2471 0.02415 0.01352 -0.0362 0.9608 0.0660
-3.500 -0.2096 0.02264 0.01194 -0.0382 0.9498 0.0929
-3.250 -0.1727 0.02116 0.01060 -0.0403 0.9392 0.1490
-3.000 -0.1394 0.01970 0.00965 -0.0419 0.9284 0.2508
-2.750 -0.1134 0.01836 0.00919 -0.0420 0.9167 0.4375
-2.500 -0.0885 0.01718 0.00905 -0.0397 0.9066 0.7096
-2.250 0.0245 0.01650 0.00806 -0.0539 0.9109 1.0000
-2.000 0.0531 0.01659 0.00774 -0.0545 0.8970 1.0000
-1.750 0.0799 0.01671 0.00749 -0.0546 0.8839 1.0000
-1.500 0.1056 0.01687 0.00733 -0.0545 0.8719 1.0000
-1.250 0.1303 0.01704 0.00724 -0.0540 0.8604 1.0000
-1.000 0.1538 0.01725 0.00722 -0.0535 0.8489 1.0000
-0.750 0.1773 0.01747 0.00721 -0.0528 0.8381 1.0000
-0.500 0.2011 0.01770 0.00725 -0.0521 0.8284 1.0000
-0.250 0.2249 0.01793 0.00732 -0.0514 0.8190 1.0000
0.000 0.2480 0.01820 0.00746 -0.0507 0.8090 1.0000
0.250 0.2716 0.01848 0.00760 -0.0500 0.8001 1.0000
0.500 0.2954 0.01874 0.00777 -0.0493 0.7915 1.0000
0.750 0.3187 0.01907 0.00802 -0.0487 0.7821 1.0000
1.000 0.3427 0.01935 0.00823 -0.0480 0.7742 1.0000
1.250 0.3663 0.01969 0.00854 -0.0473 0.7652 1.0000
1.500 0.3902 0.02004 0.00887 -0.0468 0.7566 1.0000
1.750 0.4148 0.02033 0.00914 -0.0461 0.7489 1.0000
2.000 0.4384 0.02074 0.00958 -0.0456 0.7395 1.0000
2.250 0.4627 0.02107 0.00995 -0.0449 0.7316 1.0000
2.500 0.4865 0.02145 0.01037 -0.0443 0.7226 1.0000
2.750 0.5100 0.02186 0.01085 -0.0437 0.7132 1.0000
3.000 0.5347 0.02214 0.01117 -0.0427 0.7052 1.0000
3.250 0.5578 0.02256 0.01173 -0.0420 0.6946 1.0000
3.500 0.5810 0.02295 0.01224 -0.0412 0.6839 1.0000
3.750 0.6047 0.02326 0.01266 -0.0403 0.6734 1.0000
4.000 0.6291 0.02345 0.01295 -0.0390 0.6630 1.0000
4.250 0.6524 0.02370 0.01339 -0.0379 0.6504 1.0000
4.500 0.6756 0.02390 0.01376 -0.0366 0.6368 1.0000
4.750 0.6990 0.02402 0.01404 -0.0352 0.6224 1.0000
5.000 0.7220 0.02412 0.01433 -0.0338 0.6062 1.0000
5.250 0.7443 0.02422 0.01464 -0.0323 0.5871 1.0000
5.500 0.7678 0.02404 0.01472 -0.0304 0.5675 1.0000
5.750 0.7897 0.02397 0.01489 -0.0287 0.5431 1.0000
6.000 0.8116 0.02381 0.01493 -0.0267 0.5147 1.0000
6.250 0.8326 0.02368 0.01500 -0.0247 0.4786 1.0000
6.500 0.8522 0.02361 0.01500 -0.0224 0.4274 1.0000
6.750 0.8679 0.02398 0.01514 -0.0199 0.3468 1.0000
7.000 0.8760 0.02551 0.01594 -0.0174 0.2490 1.0000
7.250 0.8794 0.02793 0.01772 -0.0157 0.1639 1.0000
7.500 0.8840 0.03032 0.01963 -0.0141 0.1097 1.0000
7.750 0.8906 0.03253 0.02163 -0.0125 0.0829 1.0000
8.000 0.8986 0.03461 0.02368 -0.0107 0.0688 1.0000
8.250 0.9073 0.03665 0.02570 -0.0090 0.0613 1.0000
8.500 0.9225 0.03846 0.02773 -0.0073 0.0558 1.0000
8.750 0.9403 0.04036 0.02971 -0.0058 0.0518 1.0000
9.000 0.9637 0.04247 0.03203 -0.0047 0.0479 1.0000
9.250 0.9829 0.04463 0.03452 -0.0036 0.0437 1.0000
9.500 0.9990 0.04698 0.03706 -0.0027 0.0409 1.0000
9.750 1.0163 0.04999 0.04032 -0.0019 0.0394 1.0000
10.000 1.0290 0.05356 0.04419 -0.0010 0.0385 1.0000
10.250 1.0334 0.05705 0.04812 0.0003 0.0380 1.0000
10.500 1.0309 0.06065 0.05211 0.0016 0.0377 1.0000
10.750 1.0231 0.06428 0.05606 0.0028 0.0376 1.0000
11.000 1.0118 0.06820 0.06025 0.0032 0.0375 1.0000
11.250 0.9977 0.07254 0.06484 0.0027 0.0375 1.0000
11.500 0.9817 0.07737 0.06989 0.0014 0.0375 1.0000
11.750 0.9654 0.08260 0.07530 -0.0008 0.0377 1.0000
12.000 0.9468 0.08865 0.08150 -0.0039 0.0379 1.0000
12.250 0.9286 0.09520 0.08817 -0.0076 0.0381 1.0000
12.500 0.9113 0.10233 0.09538 -0.0119 0.0383 1.0000
12.750 0.8956 0.10988 0.10299 -0.0165 0.0386 1.0000
13.000 0.8737 0.12026 0.11346 -0.0235 0.0394 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E180 (8.59%) (e180-il)