E180 (8.59%) (e180-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E180 (8.59%) (e180-il) Reynolds number: 200,000 Max Cl/Cd: 71 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e180-il-200000.txt Download as CSV file: xf-e180-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5148 0.09422 0.09110 -0.0092 1.0000 0.0394
-8.250 -0.5161 0.08977 0.08669 -0.0138 1.0000 0.0394
-8.000 -0.5179 0.08350 0.08049 -0.0127 1.0000 0.0405
-7.750 -0.5108 0.08041 0.07742 -0.0122 1.0000 0.0415
-7.500 -0.5050 0.07692 0.07395 -0.0139 1.0000 0.0425
-7.250 -0.4989 0.07285 0.06990 -0.0171 1.0000 0.0437
-7.000 -0.4915 0.06837 0.06541 -0.0211 1.0000 0.0450
-6.750 -0.4825 0.06343 0.06042 -0.0255 1.0000 0.0469
-6.500 -0.4692 0.05780 0.05426 -0.0333 1.0000 0.0514
-6.250 -0.4623 0.05071 0.04709 -0.0355 1.0000 0.0528
-6.000 -0.4454 0.04748 0.04396 -0.0361 1.0000 0.0544
-5.750 -0.4259 0.04447 0.04088 -0.0375 0.9918 0.0569
-5.500 -0.3922 0.03906 0.03475 -0.0428 0.9651 0.0662
-5.250 -0.3621 0.03007 0.02500 -0.0433 0.9468 0.0365
-5.000 -0.3395 0.02594 0.02029 -0.0425 0.9286 0.0336
-4.750 -0.3185 0.02319 0.01700 -0.0408 0.9111 0.0329
-4.500 -0.2957 0.02042 0.01351 -0.0385 0.8966 0.0299
-4.250 -0.2724 0.01882 0.01157 -0.0370 0.8835 0.0295
-4.000 -0.2492 0.01720 0.00972 -0.0355 0.8719 0.0300
-3.750 -0.2256 0.01590 0.00832 -0.0343 0.8606 0.0317
-3.500 -0.2012 0.01497 0.00728 -0.0333 0.8497 0.0347
-3.250 -0.1772 0.01408 0.00630 -0.0323 0.8398 0.0419
-3.000 -0.1539 0.01308 0.00531 -0.0310 0.8312 0.0676
-2.750 -0.1302 0.01208 0.00474 -0.0304 0.8213 0.1552
-2.500 -0.1081 0.01116 0.00448 -0.0297 0.8128 0.3132
-2.250 -0.0876 0.01033 0.00427 -0.0284 0.8048 0.4931
-2.000 -0.0696 0.00950 0.00422 -0.0260 0.7964 0.6991
-1.750 -0.0159 0.00905 0.00419 -0.0294 0.7904 0.9323
-1.500 0.0555 0.00907 0.00396 -0.0381 0.7833 0.9954
-1.250 0.0863 0.00909 0.00377 -0.0388 0.7761 1.0000
-1.000 0.1111 0.00914 0.00368 -0.0384 0.7678 1.0000
-0.750 0.1351 0.00921 0.00358 -0.0376 0.7612 1.0000
-0.500 0.1606 0.00928 0.00354 -0.0372 0.7530 1.0000
-0.250 0.1851 0.00937 0.00349 -0.0365 0.7469 1.0000
0.000 0.2110 0.00946 0.00351 -0.0362 0.7388 1.0000
0.500 0.2619 0.00966 0.00355 -0.0352 0.7250 1.0000
0.750 0.2870 0.00978 0.00355 -0.0346 0.7192 1.0000
1.000 0.3132 0.00990 0.00366 -0.0344 0.7115 1.0000
1.250 0.3386 0.01001 0.00370 -0.0338 0.7055 1.0000
1.500 0.3648 0.01014 0.00382 -0.0335 0.6978 1.0000
1.750 0.3903 0.01026 0.00387 -0.0329 0.6915 1.0000
2.000 0.4165 0.01038 0.00401 -0.0326 0.6833 1.0000
2.250 0.4420 0.01049 0.00406 -0.0319 0.6768 1.0000
2.500 0.4681 0.01060 0.00422 -0.0316 0.6676 1.0000
2.750 0.4938 0.01070 0.00429 -0.0310 0.6595 1.0000
3.000 0.5196 0.01077 0.00436 -0.0305 0.6505 1.0000
3.250 0.5455 0.01086 0.00449 -0.0300 0.6408 1.0000
3.500 0.5714 0.01093 0.00458 -0.0294 0.6318 1.0000
3.750 0.5972 0.01098 0.00464 -0.0288 0.6216 1.0000
4.000 0.6232 0.01103 0.00475 -0.0283 0.6099 1.0000
4.250 0.6491 0.01107 0.00483 -0.0278 0.5978 1.0000
4.500 0.6750 0.01110 0.00494 -0.0272 0.5851 1.0000
4.750 0.7008 0.01111 0.00501 -0.0266 0.5708 1.0000
5.000 0.7264 0.01109 0.00502 -0.0259 0.5528 1.0000
5.250 0.7513 0.01102 0.00497 -0.0250 0.5241 1.0000
5.500 0.7757 0.01105 0.00498 -0.0242 0.4825 1.0000
5.750 0.8002 0.01127 0.00516 -0.0235 0.4403 1.0000
6.000 0.8219 0.01185 0.00543 -0.0226 0.3571 1.0000
6.250 0.8399 0.01308 0.00610 -0.0217 0.2481 1.0000
6.500 0.8556 0.01476 0.00713 -0.0208 0.1363 1.0000
6.750 0.8676 0.01707 0.00880 -0.0193 0.0490 1.0000
7.000 0.8867 0.01824 0.01005 -0.0181 0.0405 1.0000
7.250 0.9017 0.01985 0.01169 -0.0166 0.0362 1.0000
7.500 0.9197 0.02111 0.01304 -0.0153 0.0346 1.0000
7.750 0.9384 0.02235 0.01439 -0.0140 0.0328 1.0000
8.000 0.9577 0.02353 0.01564 -0.0129 0.0304 1.0000
8.250 0.9768 0.02497 0.01713 -0.0117 0.0289 1.0000
8.500 0.9967 0.02676 0.01903 -0.0106 0.0280 1.0000
8.750 1.0177 0.02909 0.02148 -0.0097 0.0272 1.0000
9.000 1.0387 0.03184 0.02445 -0.0087 0.0269 1.0000
9.250 1.0575 0.03480 0.02770 -0.0077 0.0268 1.0000
9.500 1.0693 0.03948 0.03277 -0.0065 0.0262 1.0000
10.000 1.0838 0.04717 0.04121 -0.0034 0.0261 1.0000
10.250 1.0934 0.04904 0.04335 -0.0018 0.0266 1.0000
10.500 1.0692 0.05463 0.04987 0.0025 0.0309 1.0000
11.500 0.9121 0.06322 0.05945 0.0072 0.0318 1.0000
11.750 0.8860 0.06960 0.06599 0.0050 0.0319 1.0000
12.000 0.8594 0.07668 0.07320 0.0019 0.0320 1.0000
12.250 0.8319 0.08456 0.08121 -0.0023 0.0321 1.0000
12.500 0.8019 0.09368 0.09044 -0.0077 0.0322 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E180 (8.59%) (e180-il)