EPPLER 334 AIRFOIL (e334-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 334 AIRFOIL (e334-il) Reynolds number: 200,000 Max Cl/Cd: 66.06 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e334-il-200000.txt Download as CSV file: xf-e334-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 334 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2294 0.10296 0.09979 -0.0305 1.0000 0.0289
-9.750 -0.2313 0.09970 0.09656 -0.0322 1.0000 0.0290
-9.500 -0.2365 0.09624 0.09315 -0.0344 1.0000 0.0291
-9.250 -0.2268 0.09208 0.08903 -0.0329 1.0000 0.0295
-9.000 -0.2168 0.08882 0.08580 -0.0314 1.0000 0.0303
-8.750 -0.2153 0.08559 0.08261 -0.0317 1.0000 0.0307
-8.500 -0.2148 0.08234 0.07941 -0.0320 1.0000 0.0314
-8.250 -0.2159 0.07906 0.07618 -0.0324 1.0000 0.0319
-8.000 -0.2187 0.07579 0.07298 -0.0329 1.0000 0.0326
-7.750 -0.3143 0.08301 0.07999 -0.0351 1.0000 0.0297
-7.500 -0.3171 0.08045 0.07750 -0.0340 1.0000 0.0301
-7.250 -0.3270 0.07805 0.07518 -0.0331 1.0000 0.0302
-7.000 -0.3311 0.07558 0.07280 -0.0321 0.9992 0.0308
-6.750 -0.3021 0.07025 0.06740 -0.0402 0.9796 0.0321
-6.500 -0.2735 0.06475 0.06177 -0.0484 0.9495 0.0340
-6.250 -0.2401 0.05812 0.05468 -0.0580 0.9202 0.0357
-6.000 -0.2078 0.05374 0.05028 -0.0622 0.8924 0.0368
-5.750 -0.1825 0.05047 0.04679 -0.0647 0.8586 0.0388
-5.500 -0.1643 0.04926 0.04478 -0.0639 0.8279 0.0429
-5.250 -0.1532 0.04445 0.03995 -0.0635 0.8051 0.0440
-5.000 -0.1388 0.04212 0.03752 -0.0625 0.7831 0.0453
-4.750 -0.1228 0.04020 0.03539 -0.0613 0.7637 0.0485
-4.500 -0.1072 0.03780 0.03258 -0.0597 0.7470 0.0544
-4.250 -0.0897 0.03597 0.03063 -0.0587 0.7305 0.0578
-4.000 -0.0709 0.03442 0.02853 -0.0567 0.7162 0.0651
-3.750 -0.0521 0.03205 0.02612 -0.0560 0.7023 0.0679
-3.250 -0.0109 0.02875 0.02230 -0.0535 0.6764 0.0815
-3.000 0.0107 0.02762 0.02082 -0.0522 0.6639 0.0939
-2.750 0.0333 0.02597 0.01909 -0.0514 0.6525 0.1010
-2.500 0.0554 0.02458 0.01748 -0.0505 0.6418 0.1154
-2.250 0.0976 0.02043 0.01192 -0.0463 0.6331 0.0354
-2.000 0.1246 0.01859 0.00994 -0.0458 0.6237 0.0334
-1.750 0.1518 0.01735 0.00854 -0.0450 0.6129 0.0322
-1.500 0.1782 0.01648 0.00752 -0.0442 0.6033 0.0321
-1.250 0.2036 0.01577 0.00671 -0.0433 0.5943 0.0334
-1.000 0.2277 0.01514 0.00606 -0.0422 0.5853 0.0367
-0.750 0.2514 0.01468 0.00556 -0.0413 0.5773 0.0459
-0.500 0.4378 0.01224 0.00548 -0.0695 0.5602 1.0000
-0.250 0.4608 0.01227 0.00541 -0.0687 0.5516 1.0000
0.000 0.4840 0.01236 0.00530 -0.0679 0.5447 1.0000
0.250 0.5070 0.01243 0.00528 -0.0671 0.5367 1.0000
0.500 0.5303 0.01251 0.00522 -0.0663 0.5300 1.0000
0.750 0.5537 0.01262 0.00525 -0.0656 0.5234 1.0000
1.000 0.5770 0.01271 0.00525 -0.0648 0.5166 1.0000
1.250 0.6007 0.01286 0.00526 -0.0641 0.5110 1.0000
1.500 0.6237 0.01296 0.00534 -0.0633 0.5042 1.0000
1.750 0.6473 0.01308 0.00536 -0.0626 0.4986 1.0000
2.000 0.6708 0.01324 0.00547 -0.0619 0.4931 1.0000
2.250 0.6939 0.01336 0.00556 -0.0611 0.4868 1.0000
2.500 0.7176 0.01351 0.00562 -0.0604 0.4819 1.0000
2.750 0.7407 0.01369 0.00580 -0.0596 0.4765 1.0000
3.000 0.7636 0.01383 0.00593 -0.0588 0.4708 1.0000
3.250 0.7872 0.01401 0.00603 -0.0581 0.4660 1.0000
3.500 0.8098 0.01422 0.00626 -0.0572 0.4610 1.0000
3.750 0.8322 0.01440 0.00647 -0.0563 0.4555 1.0000
4.000 0.8555 0.01459 0.00660 -0.0555 0.4509 1.0000
4.250 0.8780 0.01484 0.00686 -0.0547 0.4462 1.0000
4.500 0.8997 0.01504 0.00711 -0.0537 0.4408 1.0000
4.750 0.9224 0.01524 0.00730 -0.0528 0.4360 1.0000
5.000 0.9451 0.01552 0.00755 -0.0520 0.4316 1.0000
5.250 0.9654 0.01574 0.00787 -0.0507 0.4261 1.0000
5.500 0.9874 0.01594 0.00807 -0.0498 0.4212 1.0000
5.750 1.0106 0.01624 0.00833 -0.0490 0.4170 1.0000
6.000 1.0292 0.01647 0.00871 -0.0475 0.4112 1.0000
6.250 1.0504 0.01668 0.00894 -0.0464 0.4061 1.0000
6.500 1.0734 0.01697 0.00916 -0.0456 0.4015 1.0000
6.750 1.0905 0.01721 0.00959 -0.0438 0.3958 1.0000
7.000 1.1108 0.01741 0.00982 -0.0425 0.3904 1.0000
7.250 1.1329 0.01771 0.01008 -0.0416 0.3858 1.0000
7.500 1.1486 0.01794 0.01050 -0.0395 0.3796 1.0000
7.750 1.1687 0.01813 0.01070 -0.0382 0.3742 1.0000
8.000 1.1877 0.01842 0.01103 -0.0367 0.3687 1.0000
8.250 1.2041 0.01864 0.01139 -0.0348 0.3624 1.0000
8.500 1.2253 0.01883 0.01154 -0.0337 0.3568 1.0000
8.750 1.2400 0.01909 0.01196 -0.0315 0.3499 1.0000
9.000 1.2591 0.01924 0.01214 -0.0301 0.3433 1.0000
9.250 1.2763 0.01950 0.01251 -0.0284 0.3365 1.0000
9.500 1.2945 0.01968 0.01276 -0.0269 0.3292 1.0000
9.750 1.3124 0.01994 0.01310 -0.0254 0.3219 1.0000
10.000 1.3300 0.02014 0.01340 -0.0239 0.3140 1.0000
10.250 1.3468 0.02043 0.01380 -0.0223 0.3058 1.0000
10.500 1.3641 0.02065 0.01405 -0.0208 0.2975 1.0000
10.750 1.3778 0.02098 0.01455 -0.0188 0.2878 1.0000
11.000 1.3920 0.02133 0.01496 -0.0169 0.2784 1.0000
11.250 1.4042 0.02170 0.01536 -0.0148 0.2683 1.0000
11.500 1.4128 0.02218 0.01598 -0.0121 0.2573 1.0000
11.750 1.4183 0.02274 0.01662 -0.0091 0.2465 1.0000
12.000 1.4224 0.02345 0.01738 -0.0060 0.2356 1.0000
12.250 1.4242 0.02436 0.01830 -0.0031 0.2244 1.0000
12.500 1.4246 0.02549 0.01948 -0.0005 0.2128 1.0000
12.750 1.4239 0.02688 0.02094 0.0018 0.2009 1.0000
13.000 1.4216 0.02858 0.02269 0.0037 0.1896 1.0000
13.250 1.4177 0.03061 0.02476 0.0052 0.1789 1.0000
13.500 1.4115 0.03304 0.02721 0.0064 0.1688 1.0000
13.750 1.4042 0.03580 0.02998 0.0071 0.1591 1.0000
14.000 1.3975 0.03873 0.03300 0.0075 0.1493 1.0000
14.250 1.3890 0.04197 0.03627 0.0076 0.1409 1.0000
14.500 1.3786 0.04553 0.03982 0.0075 0.1333 1.0000
14.750 1.3704 0.04905 0.04344 0.0072 0.1252 1.0000
15.000 1.3591 0.05290 0.04726 0.0068 0.1187 1.0000
15.250 1.3509 0.05667 0.05114 0.0061 0.1117 1.0000
15.500 1.3407 0.06070 0.05516 0.0053 0.1057 1.0000
15.750 1.3323 0.06477 0.05932 0.0043 0.0994 1.0000
16.000 1.3234 0.06887 0.06341 0.0033 0.0940 1.0000
16.250 1.3155 0.07313 0.06778 0.0020 0.0883 1.0000
16.500 1.3079 0.07720 0.07181 0.0009 0.0832 1.0000
16.750 1.3000 0.08170 0.07645 -0.0007 0.0781 1.0000
17.000 1.2941 0.08559 0.08026 -0.0018 0.0733 1.0000
17.250 1.2871 0.09017 0.08501 -0.0035 0.0690 1.0000
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Polar data table (+)
Polar graphs
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