EPPLER 330 AIRFOIL (e330-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 330 AIRFOIL (e330-il) Reynolds number: 50,000 Max Cl/Cd: 26.92 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e330-il-50000-n5.txt Download as CSV file: xf-e330-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 330 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4301 0.09497 0.08910 -0.0007 1.0000 0.0521
-9.000 -0.4341 0.09000 0.08417 -0.0028 1.0000 0.0495
-8.750 -0.5360 0.09261 0.08636 -0.0026 1.0000 0.0529
-8.500 -0.5405 0.08806 0.08183 -0.0043 1.0000 0.0500
-8.250 -0.5525 0.08352 0.07729 -0.0056 1.0000 0.0474
-8.000 -0.5675 0.07931 0.07291 -0.0059 1.0000 0.0429
-7.750 -0.5665 0.07554 0.06914 -0.0052 1.0000 0.0418
-7.500 -0.5667 0.07191 0.06545 -0.0044 1.0000 0.0408
-7.250 -0.5665 0.06824 0.06169 -0.0034 1.0000 0.0398
-7.000 -0.5654 0.06450 0.05780 -0.0021 1.0000 0.0387
-6.750 -0.5624 0.06083 0.05394 -0.0006 1.0000 0.0377
-6.500 -0.5572 0.05727 0.05015 0.0012 1.0000 0.0366
-6.250 -0.5507 0.05366 0.04623 0.0033 1.0000 0.0355
-6.000 -0.5420 0.05016 0.04236 0.0057 1.0000 0.0346
-5.750 -0.5311 0.04693 0.03870 0.0082 1.0000 0.0339
-5.500 -0.5177 0.04402 0.03539 0.0105 1.0000 0.0335
-5.250 -0.5026 0.04138 0.03246 0.0125 1.0000 0.0336
-5.000 -0.4870 0.03906 0.03003 0.0140 1.0000 0.0349
-4.750 -0.4706 0.03708 0.02788 0.0156 1.0000 0.0364
-4.500 -0.4547 0.03523 0.02579 0.0174 1.0000 0.0380
-4.250 -0.4171 0.03268 0.02281 0.0157 0.9682 0.0400
-4.000 -0.3669 0.03000 0.01963 0.0122 0.9331 0.0417
-3.750 -0.3100 0.02745 0.01674 0.0079 0.9033 0.0454
-3.500 -0.2550 0.02575 0.01473 0.0038 0.8725 0.0551
-3.250 -0.2147 0.02433 0.01312 0.0023 0.8426 0.0679
-3.000 -0.1873 0.02325 0.01196 0.0030 0.8149 0.0875
-2.750 0.0179 0.02134 0.01248 -0.0218 0.7878 1.0000
-2.500 0.0383 0.02130 0.01202 -0.0205 0.7604 1.0000
-2.250 0.0586 0.02127 0.01161 -0.0192 0.7376 1.0000
-2.000 0.0799 0.02124 0.01124 -0.0182 0.7165 1.0000
-1.750 0.1014 0.02123 0.01092 -0.0172 0.6978 1.0000
-1.500 0.1232 0.02124 0.01065 -0.0162 0.6810 1.0000
-1.250 0.1453 0.02126 0.01041 -0.0153 0.6653 1.0000
-1.000 0.1678 0.02129 0.01020 -0.0145 0.6500 1.0000
-0.750 0.1905 0.02134 0.01005 -0.0138 0.6360 1.0000
-0.500 0.2135 0.02140 0.00994 -0.0131 0.6224 1.0000
-0.250 0.2366 0.02148 0.00987 -0.0124 0.6093 1.0000
0.000 0.2600 0.02159 0.00983 -0.0118 0.5970 1.0000
0.250 0.2833 0.02171 0.00982 -0.0112 0.5854 1.0000
0.500 0.3065 0.02183 0.00982 -0.0105 0.5747 1.0000
0.750 0.3299 0.02198 0.00987 -0.0098 0.5640 1.0000
1.000 0.3534 0.02217 0.01000 -0.0093 0.5531 1.0000
1.250 0.3765 0.02235 0.01011 -0.0086 0.5433 1.0000
1.500 0.3995 0.02255 0.01024 -0.0079 0.5342 1.0000
1.750 0.4228 0.02280 0.01049 -0.0074 0.5242 1.0000
2.000 0.4462 0.02304 0.01067 -0.0067 0.5155 1.0000
2.250 0.4698 0.02331 0.01093 -0.0062 0.5065 1.0000
2.500 0.4931 0.02362 0.01128 -0.0057 0.4976 1.0000
2.750 0.5160 0.02388 0.01149 -0.0049 0.4900 1.0000
3.000 0.5391 0.02428 0.01196 -0.0044 0.4807 1.0000
3.250 0.5617 0.02456 0.01220 -0.0035 0.4738 1.0000
3.500 0.5844 0.02502 0.01276 -0.0031 0.4646 1.0000
3.750 0.6068 0.02539 0.01320 -0.0023 0.4576 1.0000
4.000 0.6290 0.02585 0.01375 -0.0016 0.4491 1.0000
4.250 0.6510 0.02631 0.01427 -0.0009 0.4416 1.0000
4.500 0.6729 0.02678 0.01483 -0.0001 0.4339 1.0000
4.750 0.6943 0.02733 0.01552 0.0006 0.4259 1.0000
5.000 0.7159 0.02778 0.01605 0.0015 0.4186 1.0000
5.250 0.7365 0.02844 0.01687 0.0023 0.4104 1.0000
5.500 0.7578 0.02885 0.01735 0.0033 0.4034 1.0000
5.750 0.7773 0.02965 0.01838 0.0041 0.3948 1.0000
6.000 0.7987 0.02999 0.01877 0.0053 0.3882 1.0000
6.250 0.8166 0.03091 0.01994 0.0062 0.3789 1.0000
6.500 0.8378 0.03122 0.02030 0.0074 0.3723 1.0000
6.750 0.8545 0.03219 0.02157 0.0085 0.3628 1.0000
7.000 0.8728 0.03286 0.02239 0.0097 0.3547 1.0000
7.250 0.8913 0.03341 0.02309 0.0110 0.3464 1.0000
7.500 0.9061 0.03440 0.02433 0.0123 0.3370 1.0000
7.750 0.9277 0.03446 0.02442 0.0138 0.3298 1.0000
8.250 0.9526 0.03654 0.02706 0.0170 0.3096 1.0000
8.500 0.9734 0.03649 0.02706 0.0187 0.3011 1.0000
8.750 0.9816 0.03770 0.02856 0.0206 0.2902 1.0000
9.000 0.9905 0.03874 0.02981 0.0226 0.2798 1.0000
9.250 1.0035 0.03923 0.03044 0.0246 0.2698 1.0000
9.500 1.0192 0.03931 0.03062 0.0267 0.2595 1.0000
9.750 1.0190 0.04082 0.03242 0.0292 0.2485 1.0000
10.000 1.0196 0.04215 0.03393 0.0318 0.2383 1.0000
10.250 1.0243 0.04289 0.03475 0.0344 0.2279 1.0000
10.500 1.0317 0.04330 0.03519 0.0369 0.2174 1.0000
10.750 1.0112 0.04609 0.03816 0.0402 0.2096 1.0000
11.000 1.0052 0.04731 0.03938 0.0432 0.2016 1.0000
11.250 0.9806 0.05068 0.04284 0.0451 0.1955 1.0000
11.500 0.9731 0.05290 0.04508 0.0463 0.1874 1.0000
11.750 0.9585 0.05638 0.04862 0.0465 0.1799 1.0000
12.000 0.9412 0.06069 0.05297 0.0460 0.1731 1.0000
12.250 0.9511 0.06118 0.05343 0.0474 0.1630 1.0000
12.500 0.9061 0.07047 0.06282 0.0437 0.1593 1.0000
12.750 0.9238 0.06982 0.06218 0.0455 0.1492 1.0000
13.000 0.8677 0.08215 0.07452 0.0399 0.1466 1.0000
13.250 0.8298 0.09218 0.08449 0.0356 0.1413 1.0000
13.500 0.8344 0.09415 0.08653 0.0358 0.1347 1.0000
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Polar data table (+)
Polar graphs
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