EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 67 AIRFOIL (e67-il) Reynolds number: 1,000,000 Max Cl/Cd: 144.72 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e67-il-1000000.txt Download as CSV file: xf-e67-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2456 0.09724 0.09566 -0.0632 0.9915 0.0148
-11.000 -0.5936 0.04604 0.04403 -0.0907 0.9909 0.0080
-10.750 -0.6015 0.03452 0.03208 -0.1110 0.9842 0.0079
-10.500 -0.5998 0.02952 0.02669 -0.1152 0.9761 0.0079
-10.250 -0.5816 0.02578 0.02257 -0.1189 0.9734 0.0079
-10.000 -0.5558 0.02333 0.01985 -0.1217 0.9720 0.0082
-9.750 -0.5388 0.02162 0.01794 -0.1215 0.9668 0.0083
-9.500 -0.5127 0.02021 0.01634 -0.1226 0.9640 0.0086
-9.250 -0.4838 0.01883 0.01478 -0.1241 0.9624 0.0087
-9.000 -0.4525 0.01777 0.01358 -0.1258 0.9611 0.0089
-8.750 -0.4217 0.01649 0.01213 -0.1275 0.9598 0.0091
-8.500 -0.3993 0.01463 0.01005 -0.1277 0.9560 0.0094
-8.250 -0.3747 0.01360 0.00890 -0.1278 0.9515 0.0097
-8.000 -0.3453 0.01277 0.00798 -0.1287 0.9486 0.0099
-7.750 -0.3137 0.01205 0.00718 -0.1299 0.9462 0.0103
-7.500 -0.2868 0.01151 0.00657 -0.1300 0.9416 0.0106
-7.250 -0.2594 0.01102 0.00601 -0.1302 0.9367 0.0111
-7.000 -0.2283 0.01057 0.00549 -0.1311 0.9332 0.0117
-6.750 -0.2001 0.01020 0.00506 -0.1314 0.9283 0.0123
-6.500 -0.1736 0.00970 0.00446 -0.1313 0.9225 0.0131
-6.250 -0.1437 0.00924 0.00394 -0.1319 0.9181 0.0148
-6.000 -0.1174 0.00897 0.00362 -0.1317 0.9122 0.0162
-5.750 -0.0896 0.00861 0.00322 -0.1317 0.9066 0.0206
-5.500 -0.0616 0.00823 0.00290 -0.1320 0.9013 0.0356
-5.250 -0.0351 0.00799 0.00269 -0.1318 0.8951 0.0472
-5.000 -0.0064 0.00778 0.00248 -0.1321 0.8899 0.0600
-4.750 0.0204 0.00758 0.00232 -0.1320 0.8838 0.0746
-4.500 0.0481 0.00739 0.00216 -0.1320 0.8779 0.0905
-4.250 0.0758 0.00720 0.00201 -0.1321 0.8721 0.1109
-4.000 0.1029 0.00702 0.00188 -0.1320 0.8656 0.1336
-3.750 0.1310 0.00684 0.00175 -0.1322 0.8598 0.1615
-3.500 0.1578 0.00665 0.00165 -0.1321 0.8531 0.1909
-3.250 0.1857 0.00649 0.00155 -0.1322 0.8468 0.2230
-3.000 0.2129 0.00635 0.00147 -0.1321 0.8400 0.2509
-2.750 0.2405 0.00622 0.00140 -0.1321 0.8334 0.2827
-2.500 0.2679 0.00608 0.00134 -0.1321 0.8265 0.3193
-2.250 0.2954 0.00596 0.00129 -0.1321 0.8195 0.3544
-2.000 0.3228 0.00585 0.00125 -0.1321 0.8124 0.3900
-1.750 0.3503 0.00577 0.00122 -0.1320 0.8050 0.4233
-1.500 0.3777 0.00569 0.00120 -0.1319 0.7973 0.4567
-1.250 0.4051 0.00563 0.00118 -0.1319 0.7895 0.4873
-1.000 0.4324 0.00556 0.00118 -0.1318 0.7810 0.5193
-0.750 0.4596 0.00553 0.00118 -0.1316 0.7728 0.5501
-0.500 0.4868 0.00549 0.00120 -0.1315 0.7638 0.5799
-0.250 0.5139 0.00547 0.00122 -0.1313 0.7551 0.6077
0.000 0.5408 0.00547 0.00124 -0.1311 0.7460 0.6351
0.250 0.5678 0.00546 0.00127 -0.1309 0.7363 0.6614
0.500 0.5946 0.00546 0.00131 -0.1307 0.7265 0.6869
0.750 0.6210 0.00549 0.00135 -0.1303 0.7161 0.7117
1.000 0.6474 0.00551 0.00141 -0.1300 0.7049 0.7363
1.250 0.6736 0.00553 0.00147 -0.1296 0.6933 0.7596
1.500 0.6995 0.00558 0.00153 -0.1291 0.6816 0.7831
1.750 0.7250 0.00563 0.00161 -0.1286 0.6693 0.8050
2.000 0.7502 0.00570 0.00168 -0.1280 0.6564 0.8275
2.250 0.7747 0.00576 0.00177 -0.1272 0.6430 0.8490
2.500 0.7989 0.00585 0.00185 -0.1264 0.6287 0.8712
2.750 0.8220 0.00592 0.00195 -0.1252 0.6137 0.8930
3.000 0.8440 0.00601 0.00204 -0.1239 0.5979 0.9165
3.250 0.8638 0.00608 0.00211 -0.1220 0.5819 0.9455
3.500 0.8929 0.00617 0.00218 -0.1223 0.5637 1.0000
3.750 0.9179 0.00637 0.00230 -0.1218 0.5447 1.0000
4.000 0.9428 0.00657 0.00243 -0.1213 0.5246 1.0000
4.250 0.9670 0.00680 0.00257 -0.1207 0.5026 1.0000
4.500 0.9908 0.00705 0.00273 -0.1200 0.4783 1.0000
4.750 1.0140 0.00733 0.00292 -0.1192 0.4538 1.0000
5.000 1.0364 0.00766 0.00312 -0.1182 0.4248 1.0000
5.250 1.0585 0.00801 0.00335 -0.1172 0.3951 1.0000
5.500 1.0804 0.00837 0.00358 -0.1162 0.3661 1.0000
5.750 1.1009 0.00881 0.00387 -0.1149 0.3309 1.0000
6.000 1.1205 0.00930 0.00418 -0.1135 0.2954 1.0000
6.250 1.1396 0.00981 0.00451 -0.1121 0.2589 1.0000
6.500 1.1579 0.01035 0.00488 -0.1105 0.2240 1.0000
6.750 1.1764 0.01087 0.00524 -0.1089 0.1937 1.0000
7.000 1.1938 0.01137 0.00562 -0.1071 0.1672 1.0000
7.250 1.2103 0.01190 0.00601 -0.1051 0.1423 1.0000
7.500 1.2276 0.01237 0.00640 -0.1033 0.1226 1.0000
7.750 1.2441 0.01288 0.00681 -0.1014 0.1047 1.0000
8.000 1.2608 0.01340 0.00725 -0.0996 0.0885 1.0000
8.250 1.2771 0.01392 0.00770 -0.0976 0.0738 1.0000
8.500 1.2925 0.01449 0.00821 -0.0956 0.0595 1.0000
8.750 1.3078 0.01509 0.00873 -0.0937 0.0474 1.0000
9.000 1.3226 0.01570 0.00929 -0.0916 0.0372 1.0000
9.250 1.3369 0.01635 0.00989 -0.0895 0.0284 1.0000
9.500 1.3500 0.01707 0.01057 -0.0873 0.0209 1.0000
9.750 1.3642 0.01774 0.01125 -0.0853 0.0169 1.0000
10.000 1.3779 0.01844 0.01194 -0.0833 0.0146 1.0000
10.250 1.3909 0.01920 0.01275 -0.0811 0.0128 1.0000
10.500 1.4058 0.01984 0.01344 -0.0794 0.0119 1.0000
10.750 1.4189 0.02060 0.01423 -0.0775 0.0109 1.0000
11.000 1.4283 0.02163 0.01532 -0.0751 0.0097 1.0000
11.250 1.4406 0.02248 0.01623 -0.0732 0.0091 1.0000
11.500 1.4535 0.02329 0.01710 -0.0715 0.0085 1.0000
11.750 1.4652 0.02422 0.01808 -0.0697 0.0079 1.0000
12.000 1.4746 0.02532 0.01924 -0.0677 0.0074 1.0000
12.250 1.4765 0.02704 0.02106 -0.0649 0.0067 1.0000
12.500 1.4846 0.02832 0.02243 -0.0631 0.0064 1.0000
12.750 1.4933 0.02959 0.02377 -0.0613 0.0062 1.0000
13.000 1.5025 0.03084 0.02509 -0.0598 0.0059 1.0000
13.250 1.5093 0.03234 0.02667 -0.0582 0.0056 1.0000
13.500 1.5150 0.03397 0.02839 -0.0566 0.0055 1.0000
13.750 1.5218 0.03555 0.03004 -0.0552 0.0052 1.0000
14.000 1.5256 0.03748 0.03205 -0.0538 0.0050 1.0000
14.250 1.5273 0.03968 0.03433 -0.0524 0.0048 1.0000
14.500 1.5240 0.04246 0.03723 -0.0511 0.0046 1.0000
14.750 1.5144 0.04609 0.04100 -0.0498 0.0044 1.0000
15.000 1.4988 0.05063 0.04572 -0.0488 0.0043 1.0000
15.250 1.4976 0.05369 0.04890 -0.0484 0.0043 1.0000
15.500 1.5004 0.05638 0.05169 -0.0483 0.0042 1.0000
15.750 1.5036 0.05912 0.05452 -0.0484 0.0041 1.0000
16.000 1.4998 0.06289 0.05840 -0.0487 0.0041 1.0000
16.250 1.4959 0.06680 0.06243 -0.0492 0.0040 1.0000
16.500 1.4946 0.07049 0.06623 -0.0500 0.0039 1.0000
16.750 1.4890 0.07496 0.07082 -0.0511 0.0038 1.0000
17.000 1.4815 0.07987 0.07586 -0.0525 0.0038 1.0000
17.250 1.4734 0.08504 0.08116 -0.0542 0.0038 1.0000
17.500 1.4648 0.09048 0.08673 -0.0562 0.0037 1.0000
17.750 1.4538 0.09650 0.09288 -0.0587 0.0037 1.0000
18.000 1.4430 0.10266 0.09918 -0.0614 0.0037 1.0000
18.250 1.4315 0.10907 0.10572 -0.0644 0.0037 1.0000
18.500 1.4193 0.11579 0.11257 -0.0677 0.0037 1.0000
18.750 1.4071 0.12263 0.11954 -0.0713 0.0036 1.0000
19.000 1.3946 0.12965 0.12670 -0.0751 0.0036 1.0000
19.250 1.3825 0.13667 0.13384 -0.0791 0.0036 1.0000
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Polar data table (+)
Polar graphs
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