E180 (8.59%) (e180-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E180 (8.59%) (e180-il) Reynolds number: 100,000 Max Cl/Cd: 51.84 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e180-il-100000-n5.txt Download as CSV file: xf-e180-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5065 0.10623 0.10158 0.0040 1.0000 0.0359
-8.750 -0.5124 0.09308 0.08853 -0.0055 1.0000 0.0216
-8.500 -0.5087 0.08944 0.08492 -0.0066 1.0000 0.0212
-8.250 -0.5079 0.08504 0.08059 -0.0094 1.0000 0.0211
-8.000 -0.5087 0.08044 0.07606 -0.0129 1.0000 0.0211
-7.750 -0.5091 0.07591 0.07159 -0.0166 1.0000 0.0209
-7.500 -0.5057 0.07111 0.06679 -0.0205 1.0000 0.0205
-7.250 -0.5019 0.06499 0.06063 -0.0255 1.0000 0.0206
-7.000 -0.4956 0.05944 0.05498 -0.0290 1.0000 0.0205
-6.750 -0.4877 0.05389 0.04925 -0.0318 1.0000 0.0204
-6.500 -0.4778 0.04855 0.04365 -0.0338 1.0000 0.0204
-6.250 -0.4656 0.04373 0.03851 -0.0350 1.0000 0.0203
-6.000 -0.4518 0.03927 0.03367 -0.0354 1.0000 0.0201
-5.750 -0.4330 0.03514 0.02908 -0.0361 0.9845 0.0199
-5.500 -0.4027 0.03078 0.02403 -0.0382 0.9570 0.0200
-5.250 -0.3729 0.02749 0.02006 -0.0391 0.9371 0.0202
-5.000 -0.3443 0.02489 0.01689 -0.0393 0.9195 0.0207
-4.750 -0.3171 0.02290 0.01445 -0.0389 0.9037 0.0213
-4.500 -0.2921 0.02120 0.01250 -0.0382 0.8891 0.0225
-4.250 -0.2677 0.02030 0.01150 -0.0376 0.8752 0.0261
-4.000 -0.2431 0.01930 0.01026 -0.0366 0.8625 0.0295
-3.750 -0.2200 0.01804 0.00885 -0.0355 0.8506 0.0332
-3.500 -0.1958 0.01718 0.00780 -0.0344 0.8396 0.0415
-3.250 -0.1722 0.01631 0.00702 -0.0336 0.8296 0.0701
-3.000 -0.1484 0.01551 0.00645 -0.0329 0.8197 0.1252
-2.750 -0.1242 0.01480 0.00600 -0.0323 0.8099 0.1989
-2.500 -0.1005 0.01412 0.00563 -0.0316 0.8014 0.3057
-2.250 -0.0773 0.01340 0.00540 -0.0308 0.7927 0.4484
-2.000 -0.0555 0.01266 0.00526 -0.0291 0.7844 0.6253
-1.750 -0.0195 0.01205 0.00519 -0.0291 0.7776 0.8424
-1.500 0.0460 0.01194 0.00487 -0.0360 0.7705 0.9660
-1.250 0.0917 0.01192 0.00458 -0.0396 0.7635 1.0000
-1.000 0.1161 0.01198 0.00445 -0.0391 0.7551 1.0000
-0.750 0.1402 0.01205 0.00432 -0.0383 0.7482 1.0000
-0.500 0.1653 0.01214 0.00426 -0.0379 0.7399 1.0000
-0.250 0.1897 0.01223 0.00418 -0.0372 0.7335 1.0000
0.000 0.2151 0.01234 0.00419 -0.0368 0.7254 1.0000
0.250 0.2398 0.01245 0.00417 -0.0361 0.7193 1.0000
0.500 0.2653 0.01258 0.00422 -0.0358 0.7114 1.0000
0.750 0.2902 0.01270 0.00423 -0.0351 0.7055 1.0000
1.000 0.3160 0.01285 0.00434 -0.0348 0.6977 1.0000
1.250 0.3410 0.01298 0.00439 -0.0342 0.6919 1.0000
1.500 0.3669 0.01314 0.00456 -0.0339 0.6841 1.0000
1.750 0.3922 0.01328 0.00464 -0.0333 0.6781 1.0000
2.000 0.4181 0.01346 0.00484 -0.0330 0.6702 1.0000
2.250 0.4435 0.01360 0.00497 -0.0324 0.6640 1.0000
2.500 0.4694 0.01378 0.00520 -0.0322 0.6554 1.0000
2.750 0.4949 0.01393 0.00534 -0.0316 0.6483 1.0000
3.000 0.5206 0.01409 0.00555 -0.0311 0.6391 1.0000
3.250 0.5462 0.01424 0.00577 -0.0306 0.6296 1.0000
3.500 0.5716 0.01434 0.00591 -0.0300 0.6201 1.0000
3.750 0.5971 0.01446 0.00608 -0.0294 0.6090 1.0000
4.000 0.6225 0.01458 0.00629 -0.0288 0.5967 1.0000
4.250 0.6479 0.01468 0.00652 -0.0282 0.5836 1.0000
4.500 0.6732 0.01477 0.00669 -0.0275 0.5693 1.0000
4.750 0.6984 0.01484 0.00685 -0.0268 0.5532 1.0000
5.000 0.7235 0.01494 0.00707 -0.0261 0.5340 1.0000
5.250 0.7483 0.01504 0.00727 -0.0253 0.5122 1.0000
5.500 0.7729 0.01517 0.00755 -0.0246 0.4853 1.0000
5.750 0.7962 0.01536 0.00771 -0.0235 0.4412 1.0000
6.000 0.8161 0.01591 0.00790 -0.0222 0.3522 1.0000
6.250 0.8307 0.01736 0.00860 -0.0209 0.2346 1.0000
6.500 0.8470 0.01880 0.00958 -0.0200 0.1552 1.0000
6.750 0.8642 0.02013 0.01060 -0.0191 0.0995 1.0000
7.000 0.8809 0.02153 0.01185 -0.0180 0.0608 1.0000
7.250 0.8973 0.02294 0.01323 -0.0168 0.0442 1.0000
7.500 0.9134 0.02431 0.01462 -0.0155 0.0367 1.0000
7.750 0.9307 0.02546 0.01590 -0.0144 0.0321 1.0000
8.000 0.9457 0.02684 0.01739 -0.0130 0.0298 1.0000
8.250 0.9581 0.02853 0.01916 -0.0115 0.0281 1.0000
8.500 0.9735 0.03001 0.02081 -0.0100 0.0272 1.0000
8.750 0.9896 0.03165 0.02261 -0.0087 0.0262 1.0000
9.000 1.0067 0.03348 0.02461 -0.0074 0.0253 1.0000
9.250 1.0244 0.03550 0.02688 -0.0063 0.0245 1.0000
9.500 1.0404 0.03746 0.02905 -0.0052 0.0233 1.0000
9.750 1.0532 0.03927 0.03101 -0.0041 0.0218 1.0000
10.000 1.0645 0.04167 0.03355 -0.0031 0.0207 1.0000
10.250 1.0740 0.04505 0.03716 -0.0020 0.0202 1.0000
10.500 1.0787 0.04794 0.04042 -0.0004 0.0200 1.0000
10.750 1.0770 0.05086 0.04367 0.0015 0.0198 1.0000
11.000 1.0710 0.05398 0.04710 0.0031 0.0197 1.0000
11.250 1.0617 0.05742 0.05084 0.0040 0.0196 1.0000
11.500 1.0498 0.06125 0.05495 0.0043 0.0195 1.0000
11.750 1.0370 0.06539 0.05933 0.0038 0.0196 1.0000
12.000 1.0211 0.07016 0.06434 0.0024 0.0195 1.0000
12.250 1.0047 0.07535 0.06973 0.0003 0.0196 1.0000
12.500 0.9873 0.08115 0.07571 -0.0025 0.0197 1.0000
12.750 0.9691 0.08758 0.08231 -0.0062 0.0197 1.0000
13.000 0.9496 0.09487 0.08974 -0.0107 0.0198 1.0000
13.250 0.9312 0.10273 0.09771 -0.0158 0.0200 1.0000
13.500 0.9138 0.11121 0.10628 -0.0212 0.0201 1.0000
13.750 0.8914 0.12308 0.11827 -0.0291 0.0206 1.0000
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Polar data table (+)
Polar graphs
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