EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 67 AIRFOIL (e67-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.89 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e67-il-1000000-n5.txt Download as CSV file: xf-e67-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 67 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6824 0.07545 0.07339 -0.0650 0.9989 0.0048
-13.250 -0.7277 0.06086 0.05864 -0.0766 0.9970 0.0047
-13.000 -0.7626 0.04626 0.04378 -0.0912 0.9945 0.0047
-12.750 -0.7818 0.03508 0.03228 -0.1054 0.9895 0.0046
-12.500 -0.7758 0.03000 0.02697 -0.1140 0.9850 0.0046
-12.250 -0.7655 0.02773 0.02456 -0.1163 0.9799 0.0048
-12.000 -0.7504 0.02562 0.02226 -0.1180 0.9754 0.0048
-11.750 -0.7284 0.02391 0.02039 -0.1199 0.9730 0.0049
-11.500 -0.7032 0.02250 0.01885 -0.1218 0.9715 0.0051
-11.250 -0.6896 0.02131 0.01752 -0.1208 0.9648 0.0051
-11.000 -0.6655 0.02011 0.01618 -0.1217 0.9617 0.0053
-10.750 -0.6379 0.01898 0.01491 -0.1232 0.9598 0.0054
-10.500 -0.6109 0.01803 0.01384 -0.1243 0.9569 0.0055
-10.250 -0.5881 0.01714 0.01283 -0.1243 0.9516 0.0056
-10.000 -0.5592 0.01635 0.01192 -0.1255 0.9485 0.0057
-9.750 -0.5287 0.01555 0.01101 -0.1269 0.9459 0.0058
-9.500 -0.5021 0.01490 0.01027 -0.1273 0.9412 0.0059
-9.250 -0.4740 0.01425 0.00951 -0.1280 0.9364 0.0060
-9.000 -0.4441 0.01365 0.00881 -0.1290 0.9324 0.0060
-8.750 -0.4175 0.01306 0.00814 -0.1293 0.9269 0.0061
-8.500 -0.3914 0.01227 0.00721 -0.1296 0.9210 0.0064
-8.250 -0.3639 0.01173 0.00658 -0.1299 0.9158 0.0067
-8.000 -0.3378 0.01129 0.00607 -0.1299 0.9096 0.0070
-7.750 -0.3102 0.01091 0.00562 -0.1302 0.9039 0.0073
-7.500 -0.2837 0.01059 0.00525 -0.1301 0.8979 0.0078
-7.250 -0.2567 0.01029 0.00487 -0.1301 0.8918 0.0082
-7.000 -0.2297 0.01000 0.00451 -0.1301 0.8862 0.0085
-6.750 -0.2029 0.00974 0.00419 -0.1301 0.8799 0.0088
-6.500 -0.1757 0.00947 0.00385 -0.1301 0.8742 0.0093
-6.250 -0.1491 0.00919 0.00353 -0.1299 0.8679 0.0103
-6.000 -0.1219 0.00897 0.00326 -0.1299 0.8618 0.0113
-5.750 -0.0948 0.00876 0.00302 -0.1298 0.8559 0.0131
-5.500 -0.0678 0.00854 0.00278 -0.1298 0.8493 0.0175
-5.250 -0.0408 0.00832 0.00256 -0.1297 0.8433 0.0245
-5.000 -0.0137 0.00811 0.00237 -0.1297 0.8367 0.0329
-4.750 0.0135 0.00794 0.00220 -0.1297 0.8304 0.0420
-4.500 0.0408 0.00777 0.00204 -0.1296 0.8237 0.0515
-4.250 0.0679 0.00762 0.00190 -0.1296 0.8169 0.0634
-4.000 0.0953 0.00746 0.00176 -0.1296 0.8097 0.0779
-3.750 0.1223 0.00730 0.00164 -0.1295 0.8026 0.0971
-3.500 0.1497 0.00715 0.00154 -0.1295 0.7950 0.1176
-3.250 0.1767 0.00701 0.00144 -0.1294 0.7875 0.1411
-3.000 0.2041 0.00691 0.00135 -0.1294 0.7795 0.1586
-2.750 0.2314 0.00682 0.00128 -0.1293 0.7718 0.1778
-2.500 0.2586 0.00671 0.00122 -0.1292 0.7635 0.2037
-2.250 0.2859 0.00661 0.00116 -0.1292 0.7557 0.2298
-2.000 0.3130 0.00653 0.00112 -0.1291 0.7471 0.2550
-1.750 0.3404 0.00645 0.00108 -0.1291 0.7387 0.2808
-1.500 0.3674 0.00639 0.00106 -0.1290 0.7297 0.3090
-1.250 0.3945 0.00634 0.00104 -0.1289 0.7199 0.3355
-1.000 0.4216 0.00628 0.00103 -0.1288 0.7100 0.3654
-0.750 0.4484 0.00625 0.00104 -0.1286 0.6998 0.3951
-0.500 0.4751 0.00623 0.00105 -0.1284 0.6890 0.4243
-0.250 0.5021 0.00621 0.00107 -0.1283 0.6782 0.4510
0.000 0.5289 0.00620 0.00109 -0.1281 0.6675 0.4780
0.250 0.5555 0.00621 0.00113 -0.1279 0.6559 0.5047
0.500 0.5819 0.00624 0.00117 -0.1276 0.6438 0.5313
0.750 0.6083 0.00627 0.00122 -0.1273 0.6307 0.5572
1.000 0.6345 0.00631 0.00129 -0.1270 0.6169 0.5833
1.250 0.6605 0.00637 0.00135 -0.1267 0.6019 0.6085
1.500 0.6863 0.00644 0.00143 -0.1263 0.5868 0.6342
1.750 0.7121 0.00652 0.00152 -0.1259 0.5709 0.6581
2.000 0.7376 0.00661 0.00162 -0.1255 0.5543 0.6824
2.250 0.7630 0.00671 0.00172 -0.1250 0.5368 0.7063
2.500 0.7879 0.00684 0.00184 -0.1244 0.5178 0.7299
2.750 0.8124 0.00699 0.00197 -0.1238 0.4983 0.7530
3.000 0.8368 0.00714 0.00211 -0.1231 0.4770 0.7753
3.250 0.8606 0.00732 0.00226 -0.1223 0.4555 0.7983
3.500 0.8842 0.00750 0.00242 -0.1215 0.4334 0.8208
3.750 0.9069 0.00771 0.00261 -0.1205 0.4101 0.8439
4.000 0.9289 0.00794 0.00279 -0.1194 0.3851 0.8673
4.250 0.9499 0.00817 0.00298 -0.1180 0.3603 0.8916
4.500 0.9688 0.00842 0.00318 -0.1162 0.3334 0.9198
4.750 0.9891 0.00865 0.00337 -0.1146 0.3085 0.9672
5.000 1.0133 0.00901 0.00361 -0.1142 0.2800 1.0000
5.250 1.0348 0.00942 0.00387 -0.1131 0.2501 1.0000
5.500 1.0565 0.00981 0.00414 -0.1121 0.2251 1.0000
5.750 1.0780 0.01020 0.00442 -0.1111 0.2011 1.0000
6.000 1.0980 0.01067 0.00475 -0.1098 0.1733 1.0000
6.250 1.1179 0.01113 0.00509 -0.1085 0.1482 1.0000
6.500 1.1368 0.01161 0.00544 -0.1069 0.1242 1.0000
6.750 1.1549 0.01207 0.00579 -0.1053 0.1044 1.0000
7.000 1.1733 0.01250 0.00614 -0.1036 0.0890 1.0000
7.250 1.1913 0.01294 0.00652 -0.1020 0.0747 1.0000
7.500 1.2094 0.01337 0.00690 -0.1003 0.0632 1.0000
7.750 1.2275 0.01381 0.00730 -0.0987 0.0535 1.0000
8.000 1.2457 0.01424 0.00770 -0.0971 0.0455 1.0000
8.250 1.2632 0.01470 0.00813 -0.0955 0.0380 1.0000
8.500 1.2799 0.01522 0.00862 -0.0937 0.0301 1.0000
8.750 1.2957 0.01578 0.00914 -0.0918 0.0230 1.0000
9.000 1.3115 0.01635 0.00968 -0.0899 0.0178 1.0000
9.250 1.3278 0.01688 0.01022 -0.0882 0.0147 1.0000
9.500 1.3434 0.01746 0.01079 -0.0864 0.0121 1.0000
9.750 1.3591 0.01803 0.01138 -0.0847 0.0105 1.0000
10.000 1.3744 0.01863 0.01201 -0.0829 0.0093 1.0000
10.250 1.3903 0.01920 0.01263 -0.0813 0.0087 1.0000
10.500 1.4052 0.01983 0.01330 -0.0796 0.0081 1.0000
10.750 1.4193 0.02053 0.01402 -0.0778 0.0074 1.0000
11.000 1.4324 0.02130 0.01483 -0.0759 0.0067 1.0000
11.250 1.4463 0.02203 0.01561 -0.0742 0.0064 1.0000
11.500 1.4601 0.02278 0.01641 -0.0726 0.0060 1.0000
11.750 1.4729 0.02360 0.01728 -0.0709 0.0056 1.0000
12.000 1.4848 0.02451 0.01825 -0.0692 0.0052 1.0000
12.250 1.4960 0.02549 0.01928 -0.0674 0.0049 1.0000
12.500 1.5055 0.02661 0.02046 -0.0656 0.0044 1.0000
12.750 1.5154 0.02775 0.02165 -0.0639 0.0042 1.0000
13.000 1.5260 0.02884 0.02281 -0.0624 0.0041 1.0000
13.250 1.5353 0.03007 0.02411 -0.0608 0.0039 1.0000
13.500 1.5439 0.03139 0.02550 -0.0593 0.0037 1.0000
13.750 1.5523 0.03277 0.02695 -0.0579 0.0035 1.0000
14.000 1.5594 0.03428 0.02854 -0.0564 0.0034 1.0000
14.250 1.5659 0.03590 0.03022 -0.0551 0.0032 1.0000
14.500 1.5712 0.03769 0.03210 -0.0538 0.0030 1.0000
14.750 1.5754 0.03966 0.03414 -0.0527 0.0029 1.0000
15.000 1.5783 0.04180 0.03637 -0.0516 0.0028 1.0000
15.250 1.5805 0.04412 0.03879 -0.0506 0.0027 1.0000
15.500 1.5807 0.04673 0.04151 -0.0498 0.0026 1.0000
15.750 1.5813 0.04942 0.04429 -0.0492 0.0025 1.0000
16.000 1.5818 0.05219 0.04717 -0.0488 0.0025 1.0000
16.250 1.5821 0.05510 0.05017 -0.0486 0.0025 1.0000
16.500 1.5820 0.05817 0.05334 -0.0485 0.0024 1.0000
16.750 1.5804 0.06155 0.05683 -0.0487 0.0023 1.0000
17.000 1.5769 0.06529 0.06069 -0.0492 0.0023 1.0000
17.250 1.5728 0.06926 0.06477 -0.0499 0.0023 1.0000
17.500 1.5693 0.07327 0.06890 -0.0508 0.0022 1.0000
17.750 1.5618 0.07806 0.07381 -0.0521 0.0022 1.0000
18.000 1.5546 0.08294 0.07883 -0.0536 0.0022 1.0000
18.250 1.5468 0.08806 0.08406 -0.0555 0.0021 1.0000
18.500 1.5366 0.09376 0.08990 -0.0577 0.0021 1.0000
18.750 1.5256 0.09976 0.09603 -0.0603 0.0021 1.0000
19.000 1.5128 0.10624 0.10264 -0.0632 0.0021 1.0000
19.250 1.5001 0.11285 0.10939 -0.0665 0.0021 1.0000
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Polar data table (+)
Polar graphs
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