EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 68 AIRFOIL (e68-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.06 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e68-il-1000000-n5.txt Download as CSV file: xf-e68-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6250 0.11507 0.11303 -0.0509 1.0000 0.0058
-15.750 -0.6838 0.09951 0.09729 -0.0582 1.0000 0.0057
-15.500 -0.7220 0.08901 0.08666 -0.0632 1.0000 0.0057
-15.250 -0.7622 0.07886 0.07640 -0.0682 1.0000 0.0056
-15.000 -0.8021 0.06919 0.06659 -0.0730 1.0000 0.0056
-14.750 -0.8399 0.06022 0.05747 -0.0774 1.0000 0.0055
-14.500 -0.8681 0.05290 0.05003 -0.0810 1.0000 0.0055
-14.250 -0.8787 0.04546 0.04241 -0.0885 0.9989 0.0055
-14.000 -0.8800 0.03943 0.03621 -0.0957 0.9969 0.0056
-13.750 -0.8724 0.03512 0.03176 -0.1016 0.9946 0.0056
-13.500 -0.8671 0.03142 0.02792 -0.1060 0.9912 0.0057
-13.250 -0.8563 0.02863 0.02499 -0.1096 0.9875 0.0057
-13.000 -0.8399 0.02646 0.02269 -0.1128 0.9846 0.0058
-12.750 -0.8290 0.02491 0.02104 -0.1134 0.9787 0.0059
-12.500 -0.8124 0.02362 0.01964 -0.1141 0.9739 0.0060
-12.250 -0.7892 0.02228 0.01819 -0.1157 0.9714 0.0061
-12.000 -0.7743 0.02127 0.01707 -0.1150 0.9638 0.0062
-11.750 -0.7473 0.02034 0.01605 -0.1165 0.9607 0.0064
-11.500 -0.7209 0.01937 0.01497 -0.1178 0.9573 0.0065
-11.250 -0.6985 0.01848 0.01398 -0.1180 0.9507 0.0067
-11.000 -0.6713 0.01761 0.01300 -0.1191 0.9460 0.0068
-10.750 -0.6467 0.01685 0.01214 -0.1195 0.9397 0.0069
-10.500 -0.6207 0.01622 0.01141 -0.1200 0.9333 0.0071
-10.250 -0.5960 0.01563 0.01072 -0.1201 0.9269 0.0072
-10.000 -0.5721 0.01508 0.01008 -0.1199 0.9197 0.0073
-9.750 -0.5480 0.01459 0.00950 -0.1198 0.9133 0.0074
-9.500 -0.5249 0.01410 0.00893 -0.1194 0.9062 0.0074
-9.250 -0.5035 0.01338 0.00808 -0.1188 0.8997 0.0077
-9.000 -0.4807 0.01286 0.00749 -0.1182 0.8930 0.0079
-8.750 -0.4565 0.01242 0.00696 -0.1179 0.8871 0.0082
-8.500 -0.4323 0.01203 0.00652 -0.1175 0.8813 0.0084
-8.250 -0.4076 0.01167 0.00610 -0.1172 0.8753 0.0087
-8.000 -0.3824 0.01135 0.00571 -0.1169 0.8698 0.0090
-7.750 -0.3571 0.01105 0.00536 -0.1166 0.8639 0.0093
-7.500 -0.3315 0.01077 0.00500 -0.1164 0.8582 0.0096
-7.250 -0.3057 0.01050 0.00469 -0.1162 0.8527 0.0100
-7.000 -0.2796 0.01027 0.00441 -0.1160 0.8467 0.0103
-6.750 -0.2539 0.00998 0.00406 -0.1157 0.8411 0.0113
-6.500 -0.2277 0.00973 0.00378 -0.1155 0.8351 0.0121
-6.250 -0.2014 0.00952 0.00352 -0.1153 0.8291 0.0131
-6.000 -0.1749 0.00932 0.00329 -0.1152 0.8234 0.0148
-5.750 -0.1487 0.00907 0.00304 -0.1150 0.8170 0.0197
-5.500 -0.1226 0.00881 0.00280 -0.1148 0.8113 0.0303
-5.250 -0.0959 0.00860 0.00261 -0.1147 0.8051 0.0394
-5.000 -0.0694 0.00842 0.00243 -0.1146 0.7989 0.0485
-4.750 -0.0426 0.00822 0.00227 -0.1145 0.7928 0.0609
-4.500 -0.0161 0.00802 0.00211 -0.1144 0.7862 0.0781
-4.250 0.0108 0.00785 0.00198 -0.1143 0.7800 0.0939
-4.000 0.0377 0.00769 0.00185 -0.1142 0.7732 0.1117
-3.750 0.0646 0.00754 0.00173 -0.1142 0.7669 0.1300
-3.500 0.0916 0.00739 0.00163 -0.1141 0.7596 0.1509
-3.250 0.1182 0.00722 0.00153 -0.1140 0.7530 0.1804
-2.750 0.1723 0.00700 0.00138 -0.1139 0.7386 0.2232
-2.500 0.1995 0.00686 0.00132 -0.1138 0.7313 0.2545
-2.250 0.2264 0.00677 0.00127 -0.1137 0.7240 0.2787
-2.000 0.2537 0.00667 0.00122 -0.1137 0.7165 0.3058
-1.750 0.2806 0.00660 0.00119 -0.1136 0.7090 0.3326
-1.500 0.3079 0.00652 0.00116 -0.1136 0.7012 0.3574
-1.250 0.3349 0.00647 0.00114 -0.1135 0.6935 0.3838
-1.000 0.3621 0.00641 0.00114 -0.1134 0.6853 0.4104
-0.750 0.3891 0.00637 0.00114 -0.1133 0.6774 0.4358
-0.500 0.4161 0.00635 0.00114 -0.1132 0.6687 0.4595
-0.250 0.4432 0.00632 0.00116 -0.1131 0.6602 0.4836
0.000 0.4698 0.00633 0.00118 -0.1129 0.6508 0.5061
0.250 0.4967 0.00632 0.00121 -0.1127 0.6405 0.5280
0.500 0.5234 0.00634 0.00124 -0.1125 0.6303 0.5489
0.750 0.5498 0.00637 0.00128 -0.1123 0.6197 0.5693
1.000 0.5762 0.00640 0.00133 -0.1120 0.6085 0.5898
1.250 0.6027 0.00643 0.00139 -0.1118 0.5977 0.6112
1.500 0.6288 0.00648 0.00145 -0.1115 0.5857 0.6320
1.750 0.6546 0.00654 0.00153 -0.1111 0.5729 0.6532
2.000 0.6802 0.00662 0.00161 -0.1107 0.5594 0.6744
2.250 0.7057 0.00669 0.00170 -0.1103 0.5465 0.6950
2.500 0.7311 0.00679 0.00181 -0.1098 0.5328 0.7149
3.000 0.7810 0.00702 0.00203 -0.1088 0.5025 0.7511
3.250 0.8054 0.00715 0.00215 -0.1081 0.4850 0.7681
3.500 0.8295 0.00730 0.00229 -0.1074 0.4674 0.7853
3.750 0.8531 0.00748 0.00244 -0.1066 0.4484 0.8016
4.000 0.8760 0.00768 0.00260 -0.1057 0.4288 0.8177
4.250 0.8986 0.00788 0.00277 -0.1047 0.4070 0.8337
4.500 0.9201 0.00814 0.00298 -0.1035 0.3837 0.8497
4.750 0.9413 0.00838 0.00318 -0.1023 0.3602 0.8662
5.000 0.9616 0.00865 0.00339 -0.1009 0.3373 0.8834
5.250 0.9804 0.00894 0.00362 -0.0991 0.3126 0.9024
5.500 0.9976 0.00922 0.00386 -0.0970 0.2875 0.9251
5.750 1.0150 0.00958 0.00413 -0.0951 0.2568 0.9617
6.000 1.0369 0.01006 0.00445 -0.0943 0.2237 1.0000
6.250 1.0535 0.01053 0.00476 -0.0924 0.1955 1.0000
6.500 1.0713 0.01093 0.00507 -0.0907 0.1740 1.0000
6.750 1.0879 0.01140 0.00542 -0.0887 0.1516 1.0000
7.000 1.1042 0.01188 0.00579 -0.0868 0.1294 1.0000
7.250 1.1200 0.01238 0.00618 -0.0848 0.1091 1.0000
7.500 1.1373 0.01282 0.00656 -0.0831 0.0947 1.0000
7.750 1.1533 0.01332 0.00698 -0.0813 0.0793 1.0000
8.000 1.1692 0.01383 0.00742 -0.0794 0.0663 1.0000
8.250 1.1859 0.01431 0.00785 -0.0777 0.0564 1.0000
8.500 1.2017 0.01483 0.00833 -0.0759 0.0470 1.0000
8.750 1.2169 0.01538 0.00884 -0.0740 0.0383 1.0000
9.000 1.2321 0.01594 0.00938 -0.0722 0.0316 1.0000
9.250 1.2467 0.01655 0.00995 -0.0703 0.0253 1.0000
9.500 1.2609 0.01718 0.01056 -0.0685 0.0197 1.0000
9.750 1.2744 0.01787 0.01123 -0.0665 0.0147 1.0000
10.000 1.2885 0.01853 0.01190 -0.0647 0.0120 1.0000
10.250 1.3027 0.01920 0.01259 -0.0630 0.0105 1.0000
10.500 1.3173 0.01986 0.01329 -0.0614 0.0097 1.0000
10.750 1.3305 0.02062 0.01407 -0.0597 0.0088 1.0000
11.000 1.3433 0.02143 0.01491 -0.0580 0.0081 1.0000
11.250 1.3570 0.02218 0.01571 -0.0565 0.0078 1.0000
11.500 1.3701 0.02299 0.01656 -0.0549 0.0074 1.0000
11.750 1.3828 0.02385 0.01747 -0.0534 0.0072 1.0000
12.000 1.3945 0.02480 0.01847 -0.0518 0.0069 1.0000
12.250 1.4058 0.02579 0.01952 -0.0503 0.0066 1.0000
12.500 1.4160 0.02689 0.02066 -0.0488 0.0064 1.0000
12.750 1.4253 0.02810 0.02192 -0.0472 0.0061 1.0000
13.000 1.4325 0.02949 0.02339 -0.0455 0.0058 1.0000
13.250 1.4416 0.03077 0.02472 -0.0442 0.0056 1.0000
13.500 1.4512 0.03204 0.02605 -0.0429 0.0055 1.0000
13.750 1.4603 0.03339 0.02746 -0.0418 0.0054 1.0000
14.000 1.4682 0.03488 0.02902 -0.0406 0.0052 1.0000
14.250 1.4753 0.03647 0.03068 -0.0395 0.0051 1.0000
14.500 1.4820 0.03816 0.03245 -0.0385 0.0050 1.0000
14.750 1.4881 0.03996 0.03433 -0.0376 0.0048 1.0000
15.000 1.4935 0.04188 0.03632 -0.0367 0.0048 1.0000
15.250 1.4975 0.04400 0.03852 -0.0360 0.0047 1.0000
15.500 1.5022 0.04612 0.04071 -0.0354 0.0045 1.0000
15.750 1.5048 0.04854 0.04321 -0.0349 0.0044 1.0000
16.000 1.5078 0.05097 0.04572 -0.0345 0.0043 1.0000
16.250 1.5092 0.05367 0.04850 -0.0343 0.0042 1.0000
16.500 1.5092 0.05663 0.05154 -0.0342 0.0041 1.0000
16.750 1.5067 0.06000 0.05502 -0.0343 0.0041 1.0000
17.000 1.5031 0.06364 0.05876 -0.0346 0.0039 1.0000
17.250 1.4987 0.06750 0.06274 -0.0352 0.0039 1.0000
17.500 1.4912 0.07193 0.06729 -0.0361 0.0038 1.0000
17.750 1.4870 0.07605 0.07151 -0.0371 0.0038 1.0000
18.000 1.4842 0.08006 0.07563 -0.0383 0.0038 1.0000
18.250 1.4806 0.08426 0.07993 -0.0396 0.0037 1.0000
18.500 1.4734 0.08915 0.08494 -0.0413 0.0037 1.0000
18.750 1.4665 0.09413 0.09003 -0.0432 0.0037 1.0000
19.000 1.4576 0.09958 0.09560 -0.0454 0.0036 1.0000
19.250 1.4487 0.10510 0.10124 -0.0478 0.0036 1.0000
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