EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 68 AIRFOIL (e68-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.57 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e68-il-1000000.txt Download as CSV file: xf-e68-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6005 0.08552 0.08366 -0.0602 1.0000 0.0095
-13.250 -0.6595 0.07112 0.06910 -0.0677 1.0000 0.0092
-13.000 -0.7031 0.06102 0.05885 -0.0728 1.0000 0.0090
-12.750 -0.7266 0.05235 0.05001 -0.0802 0.9992 0.0090
-12.500 -0.7304 0.04475 0.04220 -0.0902 0.9969 0.0090
-12.250 -0.7313 0.03794 0.03512 -0.1001 0.9942 0.0090
-12.000 -0.7320 0.03297 0.02988 -0.1061 0.9889 0.0090
-11.750 -0.7182 0.03006 0.02678 -0.1104 0.9854 0.0090
-11.500 -0.7085 0.02757 0.02407 -0.1120 0.9800 0.0091
-11.250 -0.6914 0.02523 0.02152 -0.1135 0.9756 0.0092
-11.000 -0.6673 0.02349 0.01961 -0.1154 0.9735 0.0093
-10.750 -0.6409 0.02178 0.01773 -0.1174 0.9721 0.0094
-10.500 -0.6207 0.02053 0.01633 -0.1174 0.9674 0.0096
-10.250 -0.5943 0.01965 0.01534 -0.1183 0.9640 0.0099
-10.000 -0.5662 0.01868 0.01426 -0.1194 0.9613 0.0101
-9.750 -0.5361 0.01787 0.01334 -0.1208 0.9591 0.0103
-9.500 -0.5175 0.01655 0.01188 -0.1201 0.9524 0.0105
-9.250 -0.4963 0.01497 0.01015 -0.1201 0.9471 0.0109
-9.000 -0.4715 0.01410 0.00918 -0.1203 0.9421 0.0112
-8.750 -0.4484 0.01347 0.00848 -0.1199 0.9357 0.0115
-8.500 -0.4208 0.01289 0.00782 -0.1203 0.9311 0.0119
-8.250 -0.3979 0.01240 0.00727 -0.1197 0.9246 0.0122
-8.000 -0.3722 0.01193 0.00672 -0.1196 0.9189 0.0125
-7.750 -0.3467 0.01151 0.00621 -0.1194 0.9135 0.0129
-7.500 -0.3223 0.01112 0.00576 -0.1190 0.9072 0.0133
-7.250 -0.2954 0.01077 0.00533 -0.1190 0.9020 0.0137
-7.000 -0.2714 0.01033 0.00481 -0.1184 0.8960 0.0144
-6.750 -0.2460 0.00993 0.00436 -0.1181 0.8902 0.0158
-6.500 -0.2194 0.00966 0.00403 -0.1180 0.8850 0.0171
-6.250 -0.1938 0.00938 0.00371 -0.1176 0.8791 0.0190
-6.000 -0.1677 0.00901 0.00336 -0.1174 0.8736 0.0272
-5.750 -0.1424 0.00862 0.00307 -0.1172 0.8680 0.0481
-5.500 -0.1161 0.00838 0.00286 -0.1170 0.8622 0.0622
-5.250 -0.0890 0.00816 0.00266 -0.1170 0.8570 0.0772
-5.000 -0.0628 0.00794 0.00250 -0.1168 0.8511 0.0935
-4.750 -0.0359 0.00774 0.00233 -0.1167 0.8454 0.1129
-4.500 -0.0092 0.00752 0.00218 -0.1167 0.8398 0.1373
-4.250 0.0175 0.00732 0.00205 -0.1166 0.8337 0.1607
-4.000 0.0447 0.00714 0.00192 -0.1166 0.8281 0.1879
-3.750 0.0715 0.00696 0.00181 -0.1165 0.8220 0.2158
-3.500 0.0985 0.00679 0.00171 -0.1164 0.8157 0.2460
-3.250 0.1254 0.00659 0.00162 -0.1164 0.8097 0.2843
-3.000 0.1525 0.00644 0.00154 -0.1163 0.8031 0.3149
-2.750 0.1797 0.00632 0.00147 -0.1163 0.7970 0.3473
-2.500 0.2068 0.00617 0.00142 -0.1162 0.7903 0.3843
-2.250 0.2341 0.00609 0.00137 -0.1162 0.7839 0.4147
-2.000 0.2615 0.00599 0.00134 -0.1161 0.7770 0.4442
-1.750 0.2888 0.00593 0.00131 -0.1160 0.7703 0.4720
-1.500 0.3163 0.00586 0.00130 -0.1160 0.7634 0.4970
-1.250 0.3436 0.00582 0.00128 -0.1159 0.7563 0.5217
-1.000 0.3710 0.00577 0.00128 -0.1159 0.7492 0.5461
-0.750 0.3982 0.00574 0.00128 -0.1157 0.7418 0.5693
-0.500 0.4256 0.00571 0.00129 -0.1157 0.7344 0.5924
-0.250 0.4526 0.00570 0.00130 -0.1155 0.7266 0.6150
0.000 0.4799 0.00568 0.00132 -0.1154 0.7185 0.6378
0.250 0.5065 0.00570 0.00135 -0.1151 0.7101 0.6595
0.500 0.5336 0.00568 0.00138 -0.1150 0.7012 0.6812
0.750 0.5603 0.00571 0.00142 -0.1147 0.6926 0.7020
1.000 0.5869 0.00572 0.00147 -0.1145 0.6832 0.7216
1.250 0.6135 0.00574 0.00152 -0.1142 0.6740 0.7412
1.500 0.6396 0.00579 0.00158 -0.1138 0.6642 0.7598
1.750 0.6658 0.00584 0.00164 -0.1134 0.6536 0.7776
2.000 0.6918 0.00589 0.00171 -0.1131 0.6429 0.7949
2.250 0.7174 0.00595 0.00178 -0.1126 0.6326 0.8114
2.500 0.7425 0.00603 0.00187 -0.1120 0.6214 0.8274
2.750 0.7678 0.00610 0.00195 -0.1114 0.6096 0.8430
3.000 0.7926 0.00618 0.00205 -0.1107 0.5971 0.8583
3.250 0.8167 0.00627 0.00214 -0.1099 0.5839 0.8735
3.500 0.8402 0.00637 0.00225 -0.1090 0.5707 0.8891
3.750 0.8629 0.00648 0.00236 -0.1079 0.5566 0.9049
4.000 0.8845 0.00659 0.00246 -0.1065 0.5420 0.9221
4.250 0.9047 0.00670 0.00257 -0.1049 0.5262 0.9423
4.500 0.9277 0.00682 0.00268 -0.1039 0.5089 0.9685
4.750 0.9601 0.00703 0.00282 -0.1051 0.4892 1.0000
5.000 0.9840 0.00725 0.00297 -0.1045 0.4702 1.0000
5.250 1.0071 0.00750 0.00315 -0.1037 0.4488 1.0000
5.500 1.0288 0.00780 0.00335 -0.1026 0.4235 1.0000
5.750 1.0493 0.00816 0.00357 -0.1014 0.3942 1.0000
6.000 1.0680 0.00860 0.00384 -0.0998 0.3589 1.0000
6.250 1.0865 0.00904 0.00413 -0.0982 0.3272 1.0000
6.500 1.1041 0.00946 0.00443 -0.0964 0.2979 1.0000
6.750 1.1194 0.00996 0.00476 -0.0942 0.2647 1.0000
7.000 1.1339 0.01050 0.00513 -0.0919 0.2317 1.0000
7.250 1.1493 0.01101 0.00550 -0.0898 0.2046 1.0000
7.500 1.1642 0.01154 0.00591 -0.0876 0.1790 1.0000
7.750 1.1783 0.01211 0.00634 -0.0853 0.1534 1.0000
8.000 1.1938 0.01263 0.00676 -0.0833 0.1328 1.0000
8.250 1.2081 0.01320 0.00723 -0.0812 0.1138 1.0000
8.500 1.2229 0.01376 0.00771 -0.0791 0.0967 1.0000
8.750 1.2370 0.01436 0.00822 -0.0770 0.0812 1.0000
9.000 1.2512 0.01496 0.00876 -0.0750 0.0682 1.0000
9.250 1.2651 0.01557 0.00933 -0.0730 0.0570 1.0000
9.500 1.2785 0.01623 0.00993 -0.0709 0.0467 1.0000
9.750 1.2905 0.01698 0.01062 -0.0687 0.0363 1.0000
10.000 1.3000 0.01788 0.01145 -0.0662 0.0251 1.0000
10.250 1.3097 0.01881 0.01233 -0.0639 0.0174 1.0000
10.500 1.3206 0.01968 0.01322 -0.0617 0.0144 1.0000
10.750 1.3335 0.02046 0.01404 -0.0599 0.0131 1.0000
11.000 1.3448 0.02136 0.01496 -0.0580 0.0119 1.0000
11.250 1.3540 0.02242 0.01608 -0.0558 0.0110 1.0000
11.500 1.3665 0.02328 0.01700 -0.0542 0.0106 1.0000
11.750 1.3781 0.02423 0.01801 -0.0526 0.0103 1.0000
12.000 1.3888 0.02526 0.01909 -0.0509 0.0098 1.0000
12.250 1.3988 0.02637 0.02026 -0.0493 0.0095 1.0000
12.500 1.4079 0.02757 0.02152 -0.0477 0.0092 1.0000
12.750 1.4149 0.02897 0.02298 -0.0459 0.0088 1.0000
13.000 1.4166 0.03083 0.02493 -0.0439 0.0084 1.0000
13.250 1.4178 0.03281 0.02701 -0.0420 0.0080 1.0000
13.500 1.4257 0.03429 0.02856 -0.0408 0.0079 1.0000
13.750 1.4332 0.03583 0.03018 -0.0396 0.0077 1.0000
14.000 1.4379 0.03770 0.03213 -0.0384 0.0076 1.0000
14.250 1.4431 0.03959 0.03410 -0.0374 0.0074 1.0000
14.500 1.4466 0.04170 0.03630 -0.0365 0.0072 1.0000
14.750 1.4497 0.04392 0.03861 -0.0356 0.0070 1.0000
15.000 1.4527 0.04623 0.04100 -0.0350 0.0069 1.0000
15.250 1.4530 0.04892 0.04379 -0.0344 0.0068 1.0000
15.500 1.4556 0.05145 0.04638 -0.0341 0.0066 1.0000
15.750 1.4543 0.05451 0.04955 -0.0339 0.0065 1.0000
16.000 1.4541 0.05754 0.05265 -0.0339 0.0063 1.0000
16.250 1.4504 0.06115 0.05635 -0.0341 0.0062 1.0000
16.500 1.4445 0.06515 0.06047 -0.0345 0.0061 1.0000
16.750 1.4362 0.06964 0.06507 -0.0352 0.0061 1.0000
17.000 1.4204 0.07535 0.07093 -0.0365 0.0058 1.0000
17.250 1.4115 0.08030 0.07600 -0.0378 0.0058 1.0000
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Polar data table (+)
Polar graphs
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