EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 68 AIRFOIL (e68-il) Reynolds number: 500,000 Max Cl/Cd: 114.89 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e68-il-500000.txt Download as CSV file: xf-e68-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 68 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3938 0.11774 0.11547 -0.0435 1.0000 0.0267
-11.500 -0.4996 0.08585 0.08363 -0.0546 1.0000 0.0181
-11.250 -0.6656 0.04506 0.04199 -0.0913 0.9930 0.0145
-11.000 -0.6678 0.04025 0.03690 -0.0977 0.9864 0.0145
-10.750 -0.6665 0.03630 0.03261 -0.1006 0.9793 0.0145
-10.500 -0.6536 0.03281 0.02880 -0.1031 0.9742 0.0145
-10.250 -0.6287 0.03090 0.02676 -0.1057 0.9722 0.0151
-10.000 -0.6166 0.02853 0.02413 -0.1054 0.9657 0.0151
-9.750 -0.5944 0.02620 0.02154 -0.1066 0.9623 0.0153
-9.500 -0.5673 0.02412 0.01922 -0.1083 0.9603 0.0155
-9.250 -0.5371 0.02239 0.01728 -0.1102 0.9590 0.0158
-9.000 -0.5172 0.02116 0.01591 -0.1096 0.9535 0.0161
-8.750 -0.4893 0.01989 0.01448 -0.1105 0.9505 0.0165
-8.500 -0.4579 0.01869 0.01315 -0.1120 0.9487 0.0169
-8.250 -0.4260 0.01760 0.01194 -0.1135 0.9470 0.0174
-8.000 -0.3932 0.01666 0.01089 -0.1151 0.9455 0.0178
-7.750 -0.3694 0.01602 0.01016 -0.1146 0.9403 0.0182
-7.500 -0.3457 0.01474 0.00878 -0.1146 0.9358 0.0192
-7.250 -0.3145 0.01403 0.00803 -0.1158 0.9331 0.0207
-7.000 -0.2822 0.01340 0.00734 -0.1170 0.9308 0.0221
-6.750 -0.2599 0.01298 0.00684 -0.1160 0.9243 0.0234
-6.500 -0.2322 0.01224 0.00605 -0.1163 0.9200 0.0265
-6.250 -0.2017 0.01165 0.00543 -0.1171 0.9167 0.0336
-6.000 -0.1790 0.01110 0.00499 -0.1163 0.9103 0.0553
-5.750 -0.1510 0.01073 0.00466 -0.1166 0.9055 0.0744
-5.500 -0.1209 0.01036 0.00433 -0.1173 0.9017 0.0940
-5.250 -0.0967 0.01011 0.00412 -0.1167 0.8952 0.1123
-5.000 -0.0689 0.00980 0.00387 -0.1168 0.8901 0.1346
-4.750 -0.0402 0.00951 0.00364 -0.1172 0.8856 0.1624
-4.500 -0.0155 0.00925 0.00347 -0.1167 0.8791 0.1935
-4.250 0.0125 0.00897 0.00328 -0.1169 0.8741 0.2298
-4.000 0.0391 0.00872 0.00313 -0.1168 0.8685 0.2646
-3.750 0.0655 0.00850 0.00299 -0.1167 0.8624 0.3002
-3.500 0.0945 0.00830 0.00284 -0.1170 0.8576 0.3357
-3.250 0.1198 0.00811 0.00276 -0.1166 0.8510 0.3712
-3.000 0.1474 0.00794 0.00266 -0.1166 0.8453 0.4108
-2.750 0.1748 0.00780 0.00258 -0.1165 0.8396 0.4454
-2.500 0.2014 0.00767 0.00252 -0.1163 0.8329 0.4770
-2.250 0.2304 0.00758 0.00245 -0.1165 0.8277 0.5072
-1.750 0.2842 0.00741 0.00237 -0.1161 0.8146 0.5610
-1.500 0.3108 0.00735 0.00235 -0.1158 0.8077 0.5862
-1.250 0.3382 0.00729 0.00232 -0.1157 0.8011 0.6113
-1.000 0.3653 0.00725 0.00232 -0.1155 0.7945 0.6354
-0.750 0.3922 0.00721 0.00231 -0.1152 0.7874 0.6592
-0.500 0.4195 0.00718 0.00232 -0.1150 0.7807 0.6822
-0.250 0.4461 0.00716 0.00233 -0.1147 0.7732 0.7042
0.000 0.4731 0.00716 0.00236 -0.1144 0.7662 0.7252
0.250 0.4994 0.00715 0.00238 -0.1140 0.7583 0.7460
0.500 0.5261 0.00717 0.00242 -0.1137 0.7509 0.7654
0.750 0.5520 0.00717 0.00245 -0.1131 0.7426 0.7840
1.000 0.5777 0.00719 0.00251 -0.1126 0.7343 0.8024
1.250 0.6036 0.00723 0.00254 -0.1120 0.7259 0.8203
1.500 0.6283 0.00725 0.00260 -0.1113 0.7166 0.8378
1.750 0.6535 0.00730 0.00266 -0.1106 0.7080 0.8548
2.000 0.6774 0.00733 0.00272 -0.1096 0.6984 0.8710
2.250 0.7006 0.00737 0.00278 -0.1085 0.6886 0.8873
2.500 0.7232 0.00742 0.00284 -0.1072 0.6789 0.9037
2.750 0.7444 0.00746 0.00289 -0.1056 0.6683 0.9213
3.000 0.7653 0.00748 0.00293 -0.1039 0.6577 0.9408
3.250 0.7908 0.00753 0.00298 -0.1033 0.6472 0.9611
3.500 0.8254 0.00762 0.00305 -0.1048 0.6352 0.9792
3.750 0.8625 0.00773 0.00312 -0.1070 0.6219 1.0000
4.000 0.8858 0.00785 0.00321 -0.1063 0.6085 1.0000
4.250 0.9098 0.00799 0.00333 -0.1056 0.5948 1.0000
4.500 0.9337 0.00815 0.00345 -0.1050 0.5806 1.0000
4.750 0.9570 0.00833 0.00359 -0.1042 0.5652 1.0000
5.000 0.9799 0.00853 0.00374 -0.1033 0.5490 1.0000
5.250 1.0022 0.00874 0.00391 -0.1023 0.5317 1.0000
5.500 1.0243 0.00896 0.00410 -0.1012 0.5135 1.0000
5.750 1.0455 0.00922 0.00430 -0.1000 0.4938 1.0000
6.000 1.0651 0.00952 0.00452 -0.0985 0.4718 1.0000
6.250 1.0836 0.00986 0.00478 -0.0969 0.4464 1.0000
6.500 1.1015 0.01023 0.00506 -0.0951 0.4203 1.0000
6.750 1.1160 0.01066 0.00537 -0.0926 0.3902 1.0000
7.000 1.1294 0.01114 0.00572 -0.0901 0.3593 1.0000
7.250 1.1422 0.01170 0.00612 -0.0875 0.3273 1.0000
7.500 1.1546 0.01230 0.00658 -0.0849 0.2947 1.0000
7.750 1.1661 0.01299 0.00709 -0.0822 0.2594 1.0000
8.000 1.1776 0.01370 0.00764 -0.0796 0.2274 1.0000
8.500 1.2005 0.01520 0.00884 -0.0747 0.1696 1.0000
8.750 1.2132 0.01591 0.00945 -0.0725 0.1480 1.0000
9.000 1.2248 0.01670 0.01015 -0.0702 0.1273 1.0000
9.250 1.2369 0.01747 0.01084 -0.0681 0.1098 1.0000
9.500 1.2487 0.01827 0.01158 -0.0659 0.0934 1.0000
9.750 1.2597 0.01914 0.01238 -0.0638 0.0786 1.0000
10.000 1.2698 0.02009 0.01326 -0.0616 0.0648 1.0000
10.250 1.2789 0.02113 0.01423 -0.0594 0.0514 1.0000
10.500 1.2870 0.02226 0.01531 -0.0571 0.0385 1.0000
10.750 1.2914 0.02370 0.01668 -0.0545 0.0273 1.0000
11.000 1.2988 0.02497 0.01798 -0.0524 0.0227 1.0000
11.250 1.3043 0.02642 0.01945 -0.0501 0.0199 1.0000
11.500 1.3121 0.02774 0.02086 -0.0482 0.0185 1.0000
11.750 1.3204 0.02906 0.02225 -0.0465 0.0175 1.0000
12.000 1.3279 0.03047 0.02372 -0.0449 0.0164 1.0000
12.250 1.3324 0.03217 0.02547 -0.0432 0.0155 1.0000
12.500 1.3298 0.03452 0.02793 -0.0411 0.0147 1.0000
12.750 1.3359 0.03622 0.02972 -0.0397 0.0143 1.0000
13.000 1.3414 0.03802 0.03163 -0.0385 0.0138 1.0000
13.250 1.3453 0.04004 0.03375 -0.0373 0.0134 1.0000
13.500 1.3481 0.04223 0.03604 -0.0362 0.0131 1.0000
13.750 1.3512 0.04447 0.03837 -0.0353 0.0127 1.0000
14.000 1.3522 0.04700 0.04099 -0.0345 0.0124 1.0000
14.250 1.3538 0.04957 0.04364 -0.0339 0.0121 1.0000
14.500 1.3532 0.05245 0.04661 -0.0334 0.0118 1.0000
14.750 1.3501 0.05571 0.04996 -0.0331 0.0115 1.0000
15.000 1.3453 0.05929 0.05364 -0.0328 0.0112 1.0000
15.250 1.3389 0.06318 0.05764 -0.0325 0.0110 1.0000
15.500 1.3426 0.06595 0.06055 -0.0329 0.0108 1.0000
15.750 1.3432 0.06919 0.06390 -0.0332 0.0106 1.0000
16.000 1.3446 0.07242 0.06727 -0.0337 0.0103 1.0000
16.250 1.3437 0.07602 0.07099 -0.0344 0.0101 1.0000
16.500 1.3421 0.07979 0.07488 -0.0352 0.0100 1.0000
16.750 1.3392 0.08381 0.07903 -0.0360 0.0099 1.0000
17.000 1.3369 0.08789 0.08323 -0.0373 0.0096 1.0000
17.250 1.3335 0.09219 0.08766 -0.0386 0.0095 1.0000
17.500 1.3295 0.09670 0.09230 -0.0402 0.0094 1.0000
17.750 1.3246 0.10141 0.09714 -0.0420 0.0093 1.0000
18.000 1.3198 0.10624 0.10209 -0.0440 0.0092 1.0000
18.250 1.3142 0.11128 0.10725 -0.0463 0.0090 1.0000
18.500 1.3081 0.11650 0.11260 -0.0487 0.0089 1.0000
18.750 1.3016 0.12184 0.11807 -0.0514 0.0089 1.0000
19.000 1.2942 0.12745 0.12381 -0.0544 0.0088 1.0000
19.250 1.2863 0.13326 0.12975 -0.0576 0.0087 1.0000
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