EPPLER 361 AIRFOIL (e361-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 361 AIRFOIL (e361-il) Reynolds number: 200,000 Max Cl/Cd: 54.38 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e361-il-200000-n5.txt Download as CSV file: xf-e361-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5297 0.08938 0.08573 -0.0222 1.0000 0.0125
-10.250 -0.5404 0.08221 0.07861 -0.0266 1.0000 0.0123
-10.000 -0.5569 0.07280 0.06921 -0.0342 1.0000 0.0120
-9.750 -0.5825 0.06488 0.06118 -0.0392 1.0000 0.0117
-9.500 -0.6091 0.05911 0.05528 -0.0402 1.0000 0.0115
-9.250 -0.6361 0.05422 0.05020 -0.0379 1.0000 0.0113
-9.000 -0.6905 0.04414 0.03944 -0.0319 1.0000 0.0106
-8.750 -0.7034 0.03931 0.03407 -0.0278 1.0000 0.0104
-8.500 -0.7032 0.03630 0.03072 -0.0247 1.0000 0.0104
-8.250 -0.6988 0.03360 0.02766 -0.0218 1.0000 0.0104
-7.750 -0.6809 0.02940 0.02291 -0.0167 1.0000 0.0105
-7.500 -0.6673 0.02770 0.02101 -0.0147 0.9987 0.0106
-7.250 -0.6364 0.02570 0.01873 -0.0161 0.9847 0.0108
-7.000 -0.6057 0.02402 0.01683 -0.0172 0.9657 0.0111
-6.750 -0.5725 0.02245 0.01502 -0.0186 0.9452 0.0115
-6.500 -0.5380 0.02100 0.01336 -0.0202 0.9253 0.0120
-6.250 -0.5053 0.01977 0.01193 -0.0213 0.9040 0.0125
-6.000 -0.4763 0.01870 0.01067 -0.0216 0.8824 0.0133
-5.750 -0.4507 0.01801 0.00991 -0.0213 0.8615 0.0141
-5.500 -0.4265 0.01743 0.00921 -0.0205 0.8427 0.0154
-5.250 -0.4036 0.01685 0.00851 -0.0196 0.8258 0.0169
-5.000 -0.3812 0.01629 0.00786 -0.0185 0.8102 0.0185
-4.750 -0.3591 0.01572 0.00716 -0.0173 0.7960 0.0205
-4.500 -0.3364 0.01525 0.00660 -0.0162 0.7832 0.0235
-4.250 -0.3133 0.01481 0.00611 -0.0152 0.7710 0.0295
-4.000 -0.2906 0.01434 0.00563 -0.0142 0.7596 0.0386
-3.750 -0.2677 0.01391 0.00522 -0.0132 0.7493 0.0557
-3.500 -0.2451 0.01346 0.00487 -0.0123 0.7390 0.0855
-3.250 -0.2237 0.01289 0.00452 -0.0112 0.7300 0.1420
-3.000 -0.2052 0.01210 0.00418 -0.0098 0.7211 0.2541
-2.750 -0.1910 0.01110 0.00386 -0.0076 0.7126 0.4203
-2.500 -0.1780 0.01027 0.00376 -0.0045 0.7048 0.5974
-2.250 -0.1562 0.01004 0.00383 -0.0027 0.6974 0.6928
-2.000 -0.1313 0.01003 0.00386 -0.0016 0.6899 0.7418
-1.750 -0.1057 0.01007 0.00389 -0.0006 0.6830 0.7763
-1.500 -0.0804 0.01016 0.00398 0.0005 0.6758 0.8093
-1.250 -0.0541 0.01031 0.00409 0.0016 0.6698 0.8366
-1.000 -0.0270 0.01042 0.00418 0.0023 0.6627 0.8550
-0.750 0.0007 0.01052 0.00419 0.0027 0.6564 0.8672
-0.500 0.0270 0.01058 0.00417 0.0033 0.6505 0.8779
-0.250 0.0580 0.01065 0.00419 0.0029 0.6439 0.8840
0.000 0.0861 0.01071 0.00415 0.0030 0.6384 0.8910
0.250 0.1147 0.01074 0.00415 0.0029 0.6322 0.8969
0.500 0.1458 0.01081 0.00416 0.0024 0.6259 0.9014
0.750 0.1744 0.01087 0.00414 0.0023 0.6207 0.9072
1.000 0.2032 0.01090 0.00417 0.0021 0.6139 0.9126
1.250 0.2355 0.01098 0.00419 0.0013 0.6074 0.9163
1.500 0.2658 0.01104 0.00422 0.0008 0.5997 0.9212
1.750 0.2925 0.01108 0.00420 0.0011 0.5907 0.9274
2.000 0.3257 0.01112 0.00422 0.0000 0.5784 0.9305
2.250 0.3574 0.01117 0.00423 -0.0007 0.5650 0.9344
2.500 0.3861 0.01122 0.00423 -0.0009 0.5520 0.9398
2.750 0.4163 0.01128 0.00425 -0.0014 0.5397 0.9442
3.000 0.4498 0.01135 0.00431 -0.0026 0.5272 0.9473
3.250 0.4821 0.01142 0.00438 -0.0036 0.5144 0.9512
3.500 0.5100 0.01149 0.00446 -0.0037 0.5010 0.9569
3.750 0.5436 0.01158 0.00453 -0.0050 0.4842 0.9598
4.000 0.5767 0.01169 0.00460 -0.0062 0.4644 0.9631
4.250 0.6073 0.01182 0.00470 -0.0069 0.4402 0.9677
4.500 0.6357 0.01202 0.00480 -0.0073 0.4075 0.9726
4.750 0.6669 0.01234 0.00494 -0.0084 0.3640 0.9762
5.000 0.6947 0.01280 0.00520 -0.0089 0.3158 0.9813
5.250 0.7227 0.01337 0.00553 -0.0096 0.2693 0.9858
5.500 0.7523 0.01394 0.00592 -0.0107 0.2320 0.9901
5.750 0.7815 0.01446 0.00633 -0.0117 0.2049 0.9945
6.000 0.8124 0.01494 0.00673 -0.0130 0.1834 0.9985
6.250 0.8337 0.01538 0.00711 -0.0124 0.1688 1.0000
6.500 0.8480 0.01580 0.00750 -0.0102 0.1584 1.0000
6.750 0.8631 0.01617 0.00787 -0.0081 0.1496 1.0000
7.000 0.8775 0.01660 0.00828 -0.0060 0.1421 1.0000
7.250 0.8925 0.01701 0.00870 -0.0039 0.1350 1.0000
7.500 0.9067 0.01749 0.00917 -0.0018 0.1292 1.0000
7.750 0.9225 0.01789 0.00962 0.0002 0.1237 1.0000
8.000 0.9369 0.01839 0.01011 0.0022 0.1185 1.0000
8.250 0.9516 0.01888 0.01063 0.0042 0.1141 1.0000
8.500 0.9670 0.01934 0.01115 0.0061 0.1097 1.0000
8.750 0.9808 0.01989 0.01170 0.0082 0.1054 1.0000
9.000 0.9939 0.02048 0.01231 0.0103 0.1018 1.0000
9.250 1.0091 0.02098 0.01289 0.0121 0.0980 1.0000
9.500 1.0228 0.02155 0.01352 0.0141 0.0945 1.0000
9.750 1.0333 0.02222 0.01419 0.0164 0.0913 1.0000
10.000 1.0440 0.02285 0.01488 0.0188 0.0885 1.0000
10.250 1.0559 0.02346 0.01558 0.0208 0.0853 1.0000
10.500 1.0669 0.02415 0.01635 0.0228 0.0823 1.0000
10.750 1.0762 0.02500 0.01721 0.0247 0.0796 1.0000
11.000 1.0863 0.02590 0.01817 0.0264 0.0770 1.0000
11.250 1.0984 0.02673 0.01912 0.0278 0.0741 1.0000
11.500 1.1091 0.02768 0.02015 0.0291 0.0714 1.0000
11.750 1.1179 0.02878 0.02130 0.0304 0.0691 1.0000
12.000 1.1260 0.03003 0.02260 0.0315 0.0668 1.0000
12.250 1.1368 0.03116 0.02387 0.0325 0.0645 1.0000
12.500 1.1462 0.03240 0.02522 0.0333 0.0620 1.0000
12.750 1.1542 0.03379 0.02668 0.0341 0.0599 1.0000
13.000 1.1595 0.03543 0.02835 0.0347 0.0580 1.0000
13.250 1.1671 0.03699 0.03005 0.0353 0.0561 1.0000
13.500 1.1745 0.03860 0.03180 0.0358 0.0540 1.0000
13.750 1.1805 0.04036 0.03367 0.0361 0.0522 1.0000
14.000 1.1844 0.04234 0.03572 0.0363 0.0505 1.0000
14.250 1.1859 0.04460 0.03801 0.0363 0.0489 1.0000
14.500 1.1902 0.04671 0.04029 0.0364 0.0473 1.0000
14.750 1.1928 0.04903 0.04276 0.0363 0.0457 1.0000
15.000 1.1942 0.05152 0.04538 0.0360 0.0442 1.0000
15.250 1.1940 0.05426 0.04822 0.0354 0.0430 1.0000
15.500 1.1916 0.05730 0.05132 0.0346 0.0417 1.0000
15.750 1.1889 0.06051 0.05463 0.0339 0.0407 1.0000
16.000 1.1867 0.06384 0.05815 0.0329 0.0396 1.0000
16.250 1.1830 0.06749 0.06196 0.0317 0.0384 1.0000
16.500 1.1781 0.07141 0.06602 0.0301 0.0374 1.0000
16.750 1.1717 0.07570 0.07044 0.0283 0.0366 1.0000
17.000 1.1642 0.08031 0.07516 0.0262 0.0357 1.0000
17.250 1.1559 0.08516 0.08010 0.0239 0.0351 1.0000
17.500 1.1468 0.09023 0.08523 0.0214 0.0344 1.0000
17.750 1.1339 0.09626 0.09147 0.0183 0.0338 1.0000
18.000 1.1190 0.10288 0.09827 0.0148 0.0332 1.0000
18.250 1.1015 0.11021 0.10578 0.0108 0.0327 1.0000
18.500 1.0813 0.11833 0.11407 0.0062 0.0323 1.0000
18.750 1.0560 0.12785 0.12376 0.0008 0.0320 1.0000
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