EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 67 AIRFOIL (e67-il) Reynolds number: 500,000 Max Cl/Cd: 107.47 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e67-il-500000-n5.txt Download as CSV file: xf-e67-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6518 0.05270 0.04991 -0.0810 0.9942 0.0067
-11.500 -0.6636 0.04219 0.03912 -0.0943 0.9886 0.0067
-11.250 -0.6664 0.03515 0.03176 -0.1056 0.9815 0.0067
-11.000 -0.6580 0.03175 0.02811 -0.1094 0.9742 0.0068
-10.750 -0.6384 0.02906 0.02518 -0.1129 0.9714 0.0069
-10.500 -0.6267 0.02734 0.02329 -0.1127 0.9642 0.0071
-10.250 -0.6049 0.02537 0.02109 -0.1144 0.9610 0.0072
-10.000 -0.5790 0.02374 0.01924 -0.1162 0.9590 0.0074
-9.750 -0.5613 0.02240 0.01772 -0.1158 0.9533 0.0075
-9.500 -0.5370 0.02106 0.01620 -0.1166 0.9498 0.0078
-9.250 -0.5093 0.01978 0.01474 -0.1179 0.9476 0.0079
-9.000 -0.4793 0.01860 0.01339 -0.1195 0.9459 0.0082
-8.750 -0.4553 0.01770 0.01235 -0.1195 0.9413 0.0084
-8.500 -0.4284 0.01691 0.01142 -0.1200 0.9373 0.0087
-8.250 -0.3979 0.01626 0.01065 -0.1211 0.9347 0.0090
-8.000 -0.3677 0.01509 0.00935 -0.1226 0.9323 0.0095
-7.750 -0.3414 0.01436 0.00854 -0.1228 0.9277 0.0099
-7.500 -0.3135 0.01375 0.00785 -0.1233 0.9232 0.0104
-7.250 -0.2824 0.01318 0.00719 -0.1243 0.9199 0.0110
-7.000 -0.2511 0.01265 0.00656 -0.1254 0.9167 0.0116
-6.750 -0.2251 0.01223 0.00606 -0.1252 0.9108 0.0122
-6.500 -0.1953 0.01177 0.00551 -0.1259 0.9063 0.0131
-6.250 -0.1651 0.01133 0.00502 -0.1266 0.9022 0.0148
-6.000 -0.1385 0.01102 0.00464 -0.1265 0.8961 0.0168
-5.750 -0.1092 0.01064 0.00425 -0.1270 0.8912 0.0225
-5.500 -0.0811 0.01032 0.00393 -0.1273 0.8859 0.0311
-5.250 -0.0536 0.01004 0.00366 -0.1273 0.8800 0.0400
-5.000 -0.0242 0.00978 0.00338 -0.1278 0.8750 0.0501
-4.750 0.0025 0.00956 0.00317 -0.1277 0.8687 0.0607
-4.250 0.0582 0.00906 0.00277 -0.1280 0.8570 0.1009
-4.000 0.0857 0.00885 0.00259 -0.1281 0.8506 0.1213
-3.750 0.1140 0.00866 0.00243 -0.1283 0.8448 0.1428
-3.500 0.1411 0.00850 0.00230 -0.1282 0.8379 0.1634
-3.000 0.1963 0.00818 0.00206 -0.1283 0.8246 0.2141
-2.750 0.2243 0.00803 0.00195 -0.1284 0.8179 0.2441
-2.500 0.2514 0.00789 0.00188 -0.1283 0.8105 0.2740
-2.250 0.2792 0.00777 0.00179 -0.1284 0.8034 0.3057
-1.750 0.3339 0.00755 0.00169 -0.1283 0.7882 0.3697
-1.500 0.3610 0.00745 0.00167 -0.1282 0.7800 0.4027
-1.250 0.3884 0.00738 0.00164 -0.1282 0.7724 0.4350
-1.000 0.4156 0.00731 0.00163 -0.1281 0.7638 0.4669
-0.750 0.4427 0.00726 0.00163 -0.1279 0.7554 0.4978
-0.500 0.4698 0.00723 0.00163 -0.1278 0.7465 0.5278
-0.250 0.4966 0.00720 0.00165 -0.1276 0.7368 0.5566
0.000 0.5234 0.00719 0.00168 -0.1273 0.7273 0.5845
0.250 0.5499 0.00719 0.00171 -0.1270 0.7172 0.6128
0.500 0.5764 0.00718 0.00176 -0.1267 0.7066 0.6399
0.750 0.6027 0.00720 0.00181 -0.1264 0.6960 0.6667
1.000 0.6286 0.00723 0.00188 -0.1259 0.6849 0.6927
1.250 0.6542 0.00727 0.00194 -0.1254 0.6734 0.7176
1.500 0.6797 0.00732 0.00202 -0.1248 0.6608 0.7423
1.750 0.7047 0.00738 0.00211 -0.1242 0.6477 0.7664
2.000 0.7292 0.00745 0.00221 -0.1234 0.6337 0.7899
2.250 0.7533 0.00753 0.00231 -0.1226 0.6192 0.8137
2.500 0.7765 0.00763 0.00241 -0.1215 0.6041 0.8367
2.750 0.7989 0.00773 0.00253 -0.1203 0.5882 0.8605
3.000 0.8203 0.00785 0.00264 -0.1188 0.5719 0.8854
3.250 0.8404 0.00795 0.00275 -0.1170 0.5544 0.9124
3.500 0.8613 0.00806 0.00285 -0.1155 0.5360 0.9470
4.000 0.9135 0.00850 0.00314 -0.1150 0.4927 1.0000
4.250 0.9362 0.00878 0.00333 -0.1141 0.4699 1.0000
4.500 0.9587 0.00908 0.00353 -0.1132 0.4451 1.0000
4.750 0.9807 0.00941 0.00375 -0.1122 0.4198 1.0000
5.000 1.0021 0.00976 0.00401 -0.1111 0.3932 1.0000
5.250 1.0228 0.01016 0.00428 -0.1098 0.3642 1.0000
5.500 1.0431 0.01058 0.00458 -0.1085 0.3354 1.0000
5.750 1.0624 0.01106 0.00491 -0.1071 0.3040 1.0000
6.000 1.0813 0.01155 0.00527 -0.1056 0.2731 1.0000
6.250 1.1000 0.01202 0.00562 -0.1041 0.2468 1.0000
6.500 1.1179 0.01250 0.00600 -0.1024 0.2217 1.0000
6.750 1.1344 0.01306 0.00642 -0.1005 0.1936 1.0000
7.000 1.1504 0.01365 0.00687 -0.0986 0.1660 1.0000
7.250 1.1651 0.01433 0.00739 -0.0965 0.1358 1.0000
7.500 1.1807 0.01495 0.00790 -0.0945 0.1139 1.0000
7.750 1.1976 0.01549 0.00838 -0.0928 0.0987 1.0000
8.000 1.2140 0.01606 0.00890 -0.0911 0.0839 1.0000
8.250 1.2297 0.01667 0.00945 -0.0892 0.0703 1.0000
8.500 1.2452 0.01730 0.01003 -0.0874 0.0587 1.0000
8.750 1.2606 0.01793 0.01066 -0.0856 0.0495 1.0000
9.000 1.2754 0.01861 0.01131 -0.0837 0.0413 1.0000
9.250 1.2894 0.01933 0.01200 -0.0818 0.0337 1.0000
9.500 1.3035 0.02005 0.01273 -0.0799 0.0274 1.0000
9.750 1.3168 0.02084 0.01352 -0.0780 0.0221 1.0000
10.000 1.3290 0.02171 0.01439 -0.0760 0.0180 1.0000
10.250 1.3426 0.02250 0.01522 -0.0742 0.0157 1.0000
10.500 1.3542 0.02344 0.01621 -0.0723 0.0136 1.0000
10.750 1.3666 0.02434 0.01717 -0.0705 0.0124 1.0000
11.000 1.3788 0.02527 0.01817 -0.0688 0.0114 1.0000
11.250 1.3896 0.02632 0.01927 -0.0670 0.0105 1.0000
11.500 1.3984 0.02755 0.02056 -0.0651 0.0095 1.0000
11.750 1.4093 0.02865 0.02173 -0.0634 0.0089 1.0000
12.000 1.4191 0.02985 0.02302 -0.0618 0.0084 1.0000
12.250 1.4283 0.03113 0.02438 -0.0602 0.0078 1.0000
12.500 1.4360 0.03257 0.02589 -0.0587 0.0072 1.0000
12.750 1.4416 0.03425 0.02766 -0.0570 0.0068 1.0000
13.000 1.4464 0.03603 0.02954 -0.0555 0.0065 1.0000
13.250 1.4529 0.03772 0.03133 -0.0542 0.0063 1.0000
13.500 1.4580 0.03959 0.03332 -0.0529 0.0060 1.0000
13.750 1.4628 0.04155 0.03538 -0.0518 0.0057 1.0000
14.000 1.4660 0.04373 0.03767 -0.0508 0.0055 1.0000
14.250 1.4689 0.04602 0.04008 -0.0499 0.0053 1.0000
14.500 1.4709 0.04851 0.04267 -0.0492 0.0051 1.0000
14.750 1.4721 0.05118 0.04544 -0.0487 0.0049 1.0000
15.000 1.4716 0.05414 0.04851 -0.0483 0.0048 1.0000
15.250 1.4696 0.05741 0.05190 -0.0482 0.0047 1.0000
15.500 1.4665 0.06097 0.05560 -0.0483 0.0046 1.0000
15.750 1.4588 0.06528 0.06005 -0.0488 0.0044 1.0000
16.000 1.4512 0.06979 0.06469 -0.0495 0.0043 1.0000
16.250 1.4467 0.07403 0.06907 -0.0505 0.0042 1.0000
16.500 1.4417 0.07848 0.07367 -0.0517 0.0042 1.0000
16.750 1.4354 0.08328 0.07861 -0.0532 0.0041 1.0000
17.000 1.4277 0.08846 0.08393 -0.0550 0.0041 1.0000
17.250 1.4183 0.09411 0.08973 -0.0572 0.0040 1.0000
17.500 1.4089 0.09992 0.09569 -0.0596 0.0040 1.0000
17.750 1.3986 0.10602 0.10194 -0.0624 0.0039 1.0000
18.000 1.3879 0.11237 0.10843 -0.0654 0.0039 1.0000
18.250 1.3770 0.11890 0.11510 -0.0687 0.0039 1.0000
18.500 1.3656 0.12563 0.12198 -0.0723 0.0038 1.0000
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