EPPLER 266 AIRFOIL (e266-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 266 AIRFOIL (e266-il) Reynolds number: 500,000 Max Cl/Cd: 100.39 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e266-il-500000.txt Download as CSV file: xf-e266-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 266 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.2396 0.10960 0.10612 -0.0901 0.7425 0.0237
-13.000 -0.2428 0.10416 0.10065 -0.0928 0.7367 0.0238
-12.750 -0.2518 0.09749 0.09399 -0.0955 0.7321 0.0240
-12.500 -0.2387 0.09806 0.09450 -0.0938 0.7253 0.0246
-12.250 -0.2370 0.09465 0.09106 -0.0952 0.7207 0.0249
-12.000 -0.2347 0.09138 0.08778 -0.0966 0.7164 0.0253
-11.750 -0.2372 0.08705 0.08345 -0.0986 0.7126 0.0257
-11.500 -0.2235 0.06633 0.06287 -0.1000 0.6999 0.0290
-11.250 -0.2319 0.06122 0.05774 -0.1023 0.6976 0.0287
-11.000 -0.2639 0.05383 0.05026 -0.1061 0.6961 0.0286
-10.750 -0.2730 0.05015 0.04654 -0.1068 0.6937 0.0279
-10.500 -0.3077 0.04487 0.04111 -0.1072 0.6919 0.0282
-10.250 -0.3415 0.04119 0.03721 -0.1054 0.6897 0.0286
-10.000 -0.3749 0.03945 0.03525 -0.1013 0.6876 0.0290
-9.750 -0.3979 0.03799 0.03364 -0.0967 0.6851 0.0292
-9.500 -0.4173 0.03642 0.03189 -0.0916 0.6827 0.0293
-9.250 -0.4286 0.03437 0.02962 -0.0875 0.6804 0.0293
-9.000 -0.4617 0.03960 0.03441 -0.0885 0.6820 0.0302
-8.750 -0.4473 0.03775 0.03254 -0.0876 0.6796 0.0307
-8.500 -0.4362 0.03616 0.03084 -0.0860 0.6774 0.0312
-8.250 -0.4523 0.02687 0.02011 -0.0775 0.6758 0.0194
-8.000 -0.4267 0.02429 0.01740 -0.0777 0.6737 0.0185
-7.750 -0.4036 0.02253 0.01545 -0.0772 0.6718 0.0183
-7.500 -0.3785 0.02109 0.01385 -0.0769 0.6699 0.0182
-7.250 -0.3522 0.01988 0.01251 -0.0768 0.6679 0.0181
-7.000 -0.3268 0.01904 0.01156 -0.0766 0.6658 0.0184
-6.750 -0.3017 0.01833 0.01076 -0.0763 0.6637 0.0188
-6.500 -0.2772 0.01779 0.01012 -0.0759 0.6618 0.0191
-6.250 -0.2527 0.01693 0.00920 -0.0755 0.6600 0.0194
-6.000 -0.2312 0.01615 0.00838 -0.0747 0.6583 0.0196
-5.750 -0.2119 0.01552 0.00772 -0.0735 0.6566 0.0201
-5.500 -0.1923 0.01500 0.00721 -0.0722 0.6552 0.0207
-5.250 -0.1718 0.01459 0.00679 -0.0712 0.6537 0.0216
-5.000 -0.1506 0.01422 0.00640 -0.0702 0.6521 0.0224
-4.750 -0.1284 0.01392 0.00606 -0.0694 0.6504 0.0234
-4.500 -0.1072 0.01354 0.00565 -0.0684 0.6487 0.0249
-4.250 -0.0844 0.01325 0.00535 -0.0676 0.6470 0.0275
-4.000 -0.0616 0.01297 0.00506 -0.0669 0.6454 0.0336
-3.750 -0.0457 0.01223 0.00469 -0.0651 0.6440 0.1097
-3.500 -0.0320 0.01142 0.00442 -0.0632 0.6426 0.2417
-3.250 -0.0217 0.01049 0.00415 -0.0608 0.6411 0.4129
-3.000 -0.0149 0.00940 0.00388 -0.0573 0.6400 0.6062
-2.750 0.0053 0.00937 0.00425 -0.0555 0.6386 0.7235
-2.500 0.0323 0.00961 0.00450 -0.0551 0.6370 0.7496
-2.250 0.0599 0.00988 0.00474 -0.0549 0.6354 0.7644
-2.000 0.0879 0.01031 0.00516 -0.0545 0.6340 0.7781
-1.750 0.1160 0.01084 0.00570 -0.0540 0.6326 0.7904
-1.500 0.1440 0.01119 0.00600 -0.0538 0.6312 0.7989
-1.250 0.1723 0.01159 0.00640 -0.0535 0.6298 0.8051
-1.000 0.2008 0.01198 0.00676 -0.0532 0.6283 0.8107
-0.750 0.2283 0.01214 0.00683 -0.0533 0.6269 0.8173
-0.500 0.2564 0.01237 0.00704 -0.0532 0.6256 0.8196
-0.250 0.2839 0.01255 0.00721 -0.0531 0.6244 0.8220
0.000 0.3109 0.01263 0.00729 -0.0531 0.6230 0.8245
0.250 0.3378 0.01265 0.00731 -0.0531 0.6214 0.8272
0.500 0.3649 0.01265 0.00729 -0.0534 0.6198 0.8304
0.750 0.3922 0.01263 0.00725 -0.0538 0.6184 0.8332
1.000 0.4191 0.01264 0.00725 -0.0538 0.6168 0.8345
1.250 0.4465 0.01266 0.00726 -0.0539 0.6152 0.8359
1.500 0.4743 0.01269 0.00728 -0.0541 0.6137 0.8373
1.750 0.5024 0.01273 0.00731 -0.0544 0.6123 0.8387
2.000 0.5308 0.01279 0.00734 -0.0549 0.6109 0.8403
2.250 0.5593 0.01295 0.00747 -0.0554 0.6092 0.8419
2.500 0.5857 0.01293 0.00749 -0.0555 0.6077 0.8439
2.750 0.6123 0.01293 0.00752 -0.0557 0.6059 0.8457
3.000 0.6395 0.01293 0.00754 -0.0561 0.6038 0.8474
3.250 0.6663 0.01291 0.00754 -0.0563 0.6017 0.8489
3.500 0.6933 0.01287 0.00752 -0.0564 0.5995 0.8499
3.750 0.7213 0.01283 0.00748 -0.0567 0.5973 0.8509
4.000 0.7503 0.01284 0.00747 -0.0572 0.5952 0.8518
4.250 0.7780 0.01293 0.00757 -0.0575 0.5928 0.8529
4.500 0.8022 0.01290 0.00762 -0.0571 0.5900 0.8544
4.750 0.8277 0.01286 0.00764 -0.0569 0.5868 0.8559
5.000 0.8549 0.01280 0.00760 -0.0571 0.5838 0.8573
5.250 0.8836 0.01274 0.00754 -0.0576 0.5811 0.8585
5.500 0.9136 0.01275 0.00753 -0.0584 0.5785 0.8597
5.750 0.9372 0.01271 0.00758 -0.0579 0.5748 0.8613
6.000 0.9622 0.01262 0.00755 -0.0578 0.5705 0.8627
6.250 0.9892 0.01249 0.00744 -0.0579 0.5667 0.8640
6.500 1.0171 0.01242 0.00737 -0.0581 0.5634 0.8651
6.750 1.0385 0.01235 0.00742 -0.0571 0.5587 0.8664
7.000 1.0619 0.01224 0.00738 -0.0565 0.5536 0.8676
7.250 1.0876 0.01211 0.00726 -0.0563 0.5487 0.8689
7.500 1.1079 0.01204 0.00730 -0.0551 0.5422 0.8704
7.750 1.1292 0.01187 0.00714 -0.0540 0.5337 0.8720
8.000 1.1472 0.01179 0.00716 -0.0523 0.5233 0.8738
8.250 1.1639 0.01172 0.00712 -0.0504 0.5089 0.8758
8.500 1.1792 0.01175 0.00716 -0.0482 0.4929 0.8779
8.750 1.1866 0.01182 0.00719 -0.0445 0.4728 0.8798
9.000 1.1879 0.01208 0.00740 -0.0397 0.4482 0.8820
9.250 1.1841 0.01265 0.00785 -0.0342 0.4191 0.8846
9.500 1.1775 0.01343 0.00851 -0.0286 0.3899 0.8876
9.750 1.1675 0.01446 0.00941 -0.0229 0.3606 0.8909
10.000 1.1552 0.01575 0.01058 -0.0175 0.3331 0.8943
10.250 1.1444 0.01715 0.01192 -0.0126 0.3107 0.8977
10.500 1.1345 0.01881 0.01352 -0.0086 0.2868 0.9011
10.750 1.1244 0.02075 0.01537 -0.0050 0.2645 0.9046
11.000 1.1159 0.02280 0.01733 -0.0020 0.2401 0.9079
11.250 1.1070 0.02490 0.01934 0.0009 0.2168 0.9111
11.500 1.0991 0.02705 0.02139 0.0034 0.1931 0.9147
11.750 1.0967 0.02895 0.02322 0.0053 0.1749 0.9184
12.000 1.0947 0.03087 0.02507 0.0071 0.1559 0.9221
12.250 1.0909 0.03302 0.02713 0.0087 0.1341 0.9260
12.500 1.0935 0.03484 0.02890 0.0098 0.1176 0.9299
12.750 1.0933 0.03692 0.03089 0.0108 0.0985 0.9340
13.000 1.0963 0.03923 0.03311 0.0108 0.0778 0.9378
13.250 1.0996 0.04179 0.03555 0.0104 0.0557 0.9418
13.500 1.1007 0.04483 0.03843 0.0097 0.0340 0.9458
13.750 1.1091 0.04762 0.04118 0.0081 0.0229 0.9497
14.000 1.1200 0.05048 0.04406 0.0060 0.0180 0.9534
14.250 1.1366 0.05291 0.04659 0.0035 0.0168 0.9568
14.750 1.1563 0.05787 0.05171 0.0011 0.0148 1.0000
15.000 1.1552 0.06085 0.05475 0.0011 0.0140 1.0000
15.250 1.1579 0.06348 0.05746 0.0010 0.0138 1.0000
15.500 1.1645 0.06576 0.05981 0.0008 0.0133 1.0000
15.750 1.1679 0.06839 0.06252 0.0005 0.0131 1.0000
16.000 1.1690 0.07132 0.06553 0.0003 0.0125 1.0000
16.250 1.1733 0.07388 0.06817 -0.0001 0.0123 1.0000
16.500 1.1739 0.07693 0.07129 -0.0004 0.0122 1.0000
16.750 1.1736 0.08012 0.07454 -0.0008 0.0119 1.0000
17.000 1.1738 0.08326 0.07775 -0.0013 0.0117 1.0000
17.250 1.1715 0.08674 0.08130 -0.0019 0.0114 1.0000
17.500 1.1710 0.08998 0.08460 -0.0024 0.0113 1.0000
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Polar data table (+)
Polar graphs
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