EPPLER 361 AIRFOIL (e361-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 361 AIRFOIL (e361-il) Reynolds number: 200,000 Max Cl/Cd: 64.54 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e361-il-200000.txt Download as CSV file: xf-e361-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 361 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4121 0.09787 0.09459 -0.0231 1.0000 0.0514
-10.250 -0.4347 0.09012 0.08686 -0.0298 1.0000 0.0516
-10.000 -0.4571 0.08272 0.07944 -0.0357 1.0000 0.0517
-9.750 -0.4262 0.08179 0.07859 -0.0286 1.0000 0.0530
-9.500 -0.4205 0.07865 0.07548 -0.0282 1.0000 0.0540
-9.250 -0.4248 0.07391 0.07075 -0.0299 1.0000 0.0547
-9.000 -0.4417 0.06707 0.06394 -0.0345 1.0000 0.0552
-8.750 -0.4688 0.06064 0.05747 -0.0384 1.0000 0.0551
-8.500 -0.4924 0.05616 0.05293 -0.0389 1.0000 0.0553
-8.250 -0.5119 0.05269 0.04941 -0.0371 1.0000 0.0557
-8.000 -0.5235 0.04925 0.04590 -0.0354 1.0000 0.0565
-7.750 -0.5330 0.04565 0.04219 -0.0334 1.0000 0.0581
-7.500 -0.5629 0.04452 0.04045 -0.0276 1.0000 0.0619
-6.750 -0.5409 0.03201 0.02804 -0.0256 0.9901 0.0663
-6.500 -0.5186 0.02758 0.02297 -0.0276 0.9751 0.0753
-6.250 -0.5598 0.02969 0.02327 -0.0149 0.9837 0.0287
-6.000 -0.5239 0.02608 0.01925 -0.0167 0.9738 0.0273
-5.750 -0.4858 0.02318 0.01591 -0.0184 0.9634 0.0264
-5.500 -0.4461 0.02113 0.01359 -0.0205 0.9523 0.0266
-5.250 -0.4057 0.01956 0.01184 -0.0227 0.9406 0.0281
-5.000 -0.3686 0.01821 0.01043 -0.0245 0.9265 0.0313
-4.750 -0.3362 0.01725 0.00940 -0.0251 0.9097 0.0347
-4.500 -0.3113 0.01612 0.00827 -0.0243 0.8919 0.0382
-4.250 -0.2896 0.01534 0.00744 -0.0228 0.8745 0.0450
-4.000 -0.2695 0.01464 0.00675 -0.0211 0.8585 0.0584
-3.750 -0.2517 0.01375 0.00597 -0.0190 0.8443 0.0918
-3.500 -0.2392 0.01245 0.00535 -0.0165 0.8317 0.2226
-3.250 -0.2387 0.01072 0.00498 -0.0117 0.8185 0.5170
-3.000 -0.2254 0.01025 0.00525 -0.0077 0.8072 0.7134
-2.750 -0.2030 0.01041 0.00546 -0.0054 0.7979 0.7785
-2.500 -0.1791 0.01064 0.00563 -0.0036 0.7878 0.8146
-2.250 -0.1525 0.01093 0.00584 -0.0023 0.7790 0.8393
-2.000 -0.1265 0.01119 0.00599 -0.0009 0.7702 0.8595
-1.750 -0.0987 0.01151 0.00622 0.0001 0.7620 0.8777
-1.500 -0.0607 0.01209 0.00668 -0.0003 0.7542 0.8961
-1.250 -0.0174 0.01263 0.00711 -0.0021 0.7468 0.9104
-1.000 0.0384 0.01300 0.00732 -0.0070 0.7390 0.9155
-0.750 0.0815 0.01317 0.00737 -0.0098 0.7320 0.9217
-0.500 0.1143 0.01322 0.00734 -0.0108 0.7240 0.9289
-0.250 0.1571 0.01330 0.00729 -0.0137 0.7177 0.9328
0.000 0.1899 0.01333 0.00729 -0.0148 0.7097 0.9394
0.250 0.2236 0.01335 0.00721 -0.0160 0.7032 0.9448
0.500 0.2621 0.01336 0.00720 -0.0184 0.6954 0.9488
0.750 0.2936 0.01337 0.00713 -0.0192 0.6883 0.9546
1.000 0.3258 0.01336 0.00709 -0.0203 0.6801 0.9595
1.250 0.3629 0.01329 0.00694 -0.0222 0.6711 0.9633
1.500 0.3942 0.01322 0.00686 -0.0231 0.6597 0.9687
1.750 0.4265 0.01312 0.00669 -0.0241 0.6478 0.9734
2.000 0.4622 0.01298 0.00648 -0.0257 0.6360 0.9773
2.250 0.4941 0.01289 0.00638 -0.0267 0.6246 0.9825
2.500 0.5294 0.01277 0.00625 -0.0285 0.6136 0.9864
2.750 0.5646 0.01265 0.00609 -0.0302 0.6037 0.9906
3.000 0.5988 0.01252 0.00598 -0.0317 0.5916 0.9949
3.250 0.6349 0.01235 0.00583 -0.0337 0.5788 0.9989
3.500 0.6600 0.01229 0.00577 -0.0334 0.5670 1.0000
3.750 0.6806 0.01226 0.00574 -0.0322 0.5551 1.0000
4.000 0.7010 0.01222 0.00569 -0.0309 0.5413 1.0000
4.250 0.7211 0.01219 0.00568 -0.0296 0.5257 1.0000
4.500 0.7410 0.01218 0.00570 -0.0282 0.5081 1.0000
4.750 0.7604 0.01217 0.00571 -0.0268 0.4862 1.0000
5.000 0.7791 0.01221 0.00572 -0.0252 0.4594 1.0000
5.250 0.7964 0.01234 0.00575 -0.0234 0.4207 1.0000
5.500 0.8109 0.01270 0.00588 -0.0211 0.3655 1.0000
5.750 0.8217 0.01338 0.00620 -0.0185 0.3028 1.0000
6.000 0.8318 0.01415 0.00668 -0.0158 0.2572 1.0000
6.250 0.8428 0.01485 0.00719 -0.0131 0.2282 1.0000
6.500 0.8545 0.01548 0.00771 -0.0106 0.2085 1.0000
6.750 0.8668 0.01608 0.00823 -0.0081 0.1939 1.0000
7.000 0.8797 0.01666 0.00875 -0.0056 0.1822 1.0000
7.250 0.8918 0.01734 0.00932 -0.0031 0.1727 1.0000
7.500 0.9070 0.01783 0.00986 -0.0011 0.1641 1.0000
7.750 0.9205 0.01852 0.01048 0.0012 0.1569 1.0000
8.000 0.9362 0.01903 0.01103 0.0031 0.1497 1.0000
8.250 0.9505 0.01985 0.01175 0.0051 0.1438 1.0000
8.500 0.9669 0.02035 0.01236 0.0069 0.1380 1.0000
8.750 0.9822 0.02103 0.01300 0.0087 0.1324 1.0000
9.000 0.9987 0.02182 0.01382 0.0103 0.1274 1.0000
9.250 1.0151 0.02243 0.01450 0.0120 0.1225 1.0000
9.500 1.0318 0.02325 0.01528 0.0134 0.1178 1.0000
9.750 1.0485 0.02409 0.01621 0.0148 0.1134 1.0000
10.000 1.0643 0.02477 0.01699 0.0164 0.1091 1.0000
10.250 1.0808 0.02557 0.01776 0.0178 0.1050 1.0000
10.500 1.0981 0.02667 0.01894 0.0189 0.1010 1.0000
10.750 1.1113 0.02741 0.01983 0.0208 0.0973 1.0000
11.000 1.1245 0.02815 0.02061 0.0225 0.0938 1.0000
11.250 1.1448 0.02960 0.02202 0.0229 0.0898 1.0000
11.500 1.1518 0.03038 0.02302 0.0256 0.0873 1.0000
11.750 1.1602 0.03127 0.02405 0.0278 0.0842 1.0000
12.000 1.1707 0.03213 0.02493 0.0295 0.0813 1.0000
12.250 1.1889 0.03380 0.02659 0.0299 0.0780 1.0000
12.500 1.1912 0.03488 0.02790 0.0324 0.0760 1.0000
12.750 1.1950 0.03608 0.02928 0.0343 0.0734 1.0000
13.000 1.2017 0.03724 0.03053 0.0357 0.0710 1.0000
13.250 1.2133 0.03843 0.03168 0.0366 0.0686 1.0000
13.500 1.2176 0.04057 0.03400 0.0378 0.0665 1.0000
13.750 1.2153 0.04243 0.03609 0.0391 0.0648 1.0000
14.000 1.2144 0.04443 0.03828 0.0401 0.0629 1.0000
14.250 1.2162 0.04615 0.04009 0.0407 0.0610 1.0000
14.500 1.2240 0.04759 0.04151 0.0411 0.0590 1.0000
14.750 1.2255 0.05046 0.04447 0.0415 0.0573 1.0000
15.000 1.2144 0.05354 0.04784 0.0416 0.0563 1.0000
15.250 1.2031 0.05710 0.05165 0.0413 0.0552 1.0000
15.500 1.1927 0.06063 0.05537 0.0405 0.0539 1.0000
15.750 1.1806 0.06471 0.05965 0.0395 0.0530 1.0000
16.000 1.1705 0.06866 0.06375 0.0382 0.0520 1.0000
16.250 1.1664 0.07198 0.06715 0.0370 0.0509 1.0000
16.500 1.1732 0.07410 0.06922 0.0367 0.0495 1.0000
16.750 1.1539 0.08003 0.07531 0.0345 0.0488 1.0000
17.000 1.1265 0.08735 0.08286 0.0307 0.0486 1.0000
17.250 1.0945 0.09609 0.09183 0.0258 0.0487 1.0000
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Polar data table (+)
Polar graphs
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