EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Reynolds number: 200,000 Max Cl/Cd: 63.04 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ec863914-il-200000-n5.txt Download as CSV file: xf-ec863914-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EC 86(-3)-914 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3517 0.09628 0.09252 -0.0877 0.9662 0.0102
-11.500 -0.3788 0.08542 0.08157 -0.0943 0.9646 0.0100
-11.250 -0.3967 0.07654 0.07255 -0.1014 0.9630 0.0099
-11.000 -0.4118 0.06884 0.06468 -0.1084 0.9617 0.0098
-10.750 -0.4347 0.06504 0.06083 -0.1079 0.9577 0.0099
-10.500 -0.4530 0.06010 0.05573 -0.1106 0.9540 0.0097
-10.250 -0.4655 0.05592 0.05136 -0.1132 0.9514 0.0096
-10.000 -0.4773 0.05181 0.04702 -0.1158 0.9493 0.0095
-9.750 -0.5055 0.05055 0.04573 -0.1101 0.9428 0.0096
-9.500 -0.5199 0.04805 0.04303 -0.1089 0.9386 0.0094
-9.250 -0.5181 0.04453 0.03915 -0.1113 0.9362 0.0092
-9.000 -0.5320 0.04284 0.03730 -0.1076 0.9297 0.0092
-8.750 -0.5215 0.03996 0.03401 -0.1088 0.9265 0.0089
-8.500 -0.5011 0.03760 0.03134 -0.1102 0.9247 0.0088
-8.250 -0.4776 0.03550 0.02902 -0.1118 0.9235 0.0090
-8.000 -0.4646 0.03412 0.02755 -0.1109 0.9201 0.0095
-7.750 -0.4481 0.03280 0.02608 -0.1103 0.9168 0.0098
-7.500 -0.4237 0.03141 0.02452 -0.1109 0.9148 0.0100
-7.250 -0.3966 0.03007 0.02301 -0.1118 0.9133 0.0100
-7.000 -0.3675 0.02881 0.02163 -0.1129 0.9122 0.0099
-6.750 -0.3364 0.02763 0.02035 -0.1144 0.9112 0.0097
-6.500 -0.3093 0.02670 0.01933 -0.1152 0.9093 0.0096
-6.250 -0.2886 0.02590 0.01847 -0.1149 0.9053 0.0096
-6.000 -0.2566 0.02506 0.01754 -0.1168 0.9035 0.0095
-5.750 -0.2215 0.02427 0.01661 -0.1192 0.9021 0.0095
-5.500 -0.1855 0.02362 0.01584 -0.1216 0.9010 0.0095
-5.250 -0.1486 0.02306 0.01514 -0.1241 0.9000 0.0094
-5.000 -0.1117 0.02257 0.01452 -0.1264 0.8992 0.0095
-4.750 -0.0890 0.02233 0.01419 -0.1259 0.8948 0.0095
-4.500 -0.0577 0.02202 0.01378 -0.1270 0.8923 0.0096
-4.250 -0.0236 0.02173 0.01339 -0.1285 0.8905 0.0097
-4.000 0.0119 0.02145 0.01300 -0.1303 0.8891 0.0099
-3.750 0.0482 0.02120 0.01268 -0.1322 0.8880 0.0101
-3.500 0.0730 0.02112 0.01255 -0.1319 0.8837 0.0104
-3.250 0.1031 0.02097 0.01237 -0.1326 0.8804 0.0109
-3.000 0.1483 0.01996 0.01200 -0.1375 0.8796 0.1526
-2.750 0.1841 0.01978 0.01183 -0.1392 0.8779 0.1711
-2.500 0.2215 0.01955 0.01168 -0.1413 0.8766 0.1980
-2.250 0.2465 0.01950 0.01170 -0.1412 0.8711 0.2197
-2.000 0.2838 0.01912 0.01161 -0.1437 0.8683 0.2745
-1.750 0.3271 0.01858 0.01147 -0.1476 0.8667 0.3598
-1.500 0.3714 0.01794 0.01165 -0.1514 0.8655 0.5290
-1.250 0.3892 0.01814 0.01210 -0.1488 0.8589 0.5991
-1.000 0.4216 0.01806 0.01197 -0.1496 0.8551 0.6249
-0.750 0.4582 0.01783 0.01171 -0.1509 0.8527 0.6423
-0.500 0.4813 0.01784 0.01168 -0.1499 0.8439 0.6552
-0.250 0.5167 0.01746 0.01129 -0.1508 0.8403 0.6651
0.000 0.5380 0.01748 0.01130 -0.1494 0.8306 0.6726
0.250 0.5724 0.01712 0.01093 -0.1502 0.8268 0.6806
0.500 0.5922 0.01717 0.01099 -0.1485 0.8154 0.6867
0.750 0.6143 0.01713 0.01096 -0.1471 0.8041 0.6925
1.000 0.6439 0.01691 0.01072 -0.1472 0.7934 0.6990
1.250 0.6725 0.01658 0.01042 -0.1467 0.7838 0.7039
1.500 0.7026 0.01641 0.01022 -0.1468 0.7708 0.7126
1.750 0.7316 0.01610 0.00995 -0.1462 0.7579 0.7182
2.000 0.7713 0.01559 0.00941 -0.1479 0.7434 0.7255
2.250 0.8160 0.01494 0.00870 -0.1501 0.7243 0.7321
2.500 0.8579 0.01460 0.00827 -0.1521 0.6978 0.7390
2.750 0.8982 0.01451 0.00800 -0.1542 0.6650 0.7446
3.000 0.9261 0.01469 0.00801 -0.1540 0.6268 0.7466
3.250 0.9487 0.01506 0.00816 -0.1530 0.5854 0.7482
3.500 0.9671 0.01555 0.00844 -0.1513 0.5451 0.7502
3.750 0.9846 0.01608 0.00879 -0.1496 0.5077 0.7522
4.000 1.0028 0.01662 0.00916 -0.1481 0.4736 0.7540
4.250 1.0218 0.01718 0.00957 -0.1469 0.4418 0.7561
4.500 1.0417 0.01775 0.00999 -0.1459 0.4121 0.7583
4.750 1.0593 0.01830 0.01045 -0.1443 0.3854 0.7596
5.000 1.0771 0.01887 0.01092 -0.1428 0.3612 0.7607
5.250 1.0960 0.01940 0.01139 -0.1415 0.3395 0.7619
5.500 1.1152 0.01995 0.01188 -0.1403 0.3210 0.7633
5.750 1.1350 0.02048 0.01238 -0.1392 0.3053 0.7649
6.000 1.1556 0.02100 0.01291 -0.1383 0.2914 0.7666
6.250 1.1769 0.02153 0.01343 -0.1375 0.2790 0.7682
6.500 1.1983 0.02207 0.01398 -0.1368 0.2681 0.7697
6.750 1.2191 0.02267 0.01456 -0.1360 0.2579 0.7713
7.000 1.2415 0.02320 0.01514 -0.1355 0.2483 0.7728
7.250 1.2622 0.02379 0.01577 -0.1347 0.2408 0.7742
7.500 1.2823 0.02433 0.01639 -0.1337 0.2338 0.7754
7.750 1.3012 0.02494 0.01704 -0.1325 0.2252 0.7768
8.000 1.3186 0.02564 0.01773 -0.1312 0.2123 0.7783
8.250 1.3361 0.02636 0.01844 -0.1300 0.1993 0.7798
8.500 1.3559 0.02697 0.01916 -0.1291 0.1895 0.7813
8.750 1.3742 0.02768 0.01991 -0.1281 0.1772 0.7828
9.000 1.3904 0.02855 0.02073 -0.1269 0.1588 0.7844
9.250 1.4065 0.02951 0.02162 -0.1257 0.1337 0.7860
9.500 1.4061 0.03201 0.02347 -0.1227 0.0581 0.7875
10.000 1.4128 0.03646 0.02765 -0.1174 0.0099 0.7899
10.250 1.4225 0.03799 0.02930 -0.1155 0.0079 0.7913
10.500 1.4304 0.03971 0.03118 -0.1135 0.0065 0.7928
10.750 1.4399 0.04127 0.03292 -0.1117 0.0060 0.7945
11.000 1.4477 0.04303 0.03490 -0.1099 0.0057 0.7962
11.250 1.4539 0.04499 0.03705 -0.1081 0.0054 0.7978
11.500 1.4588 0.04713 0.03939 -0.1064 0.0052 0.7994
11.750 1.4614 0.04955 0.04199 -0.1047 0.0050 0.8010
12.000 1.4627 0.05221 0.04484 -0.1032 0.0048 0.8026
12.250 1.4616 0.05521 0.04803 -0.1018 0.0046 0.8042
12.500 1.4586 0.05846 0.05147 -0.1004 0.0045 0.8053
12.750 1.4538 0.06209 0.05530 -0.0994 0.0044 0.8066
13.000 1.4484 0.06600 0.05939 -0.0987 0.0043 0.8079
13.250 1.4409 0.07039 0.06397 -0.0984 0.0043 0.8093
13.500 1.4328 0.07511 0.06887 -0.0985 0.0042 0.8107
13.750 1.4224 0.08041 0.07436 -0.0992 0.0041 0.8121
14.000 1.4133 0.08577 0.07990 -0.1002 0.0041 0.8136
14.250 1.4026 0.09157 0.08588 -0.1017 0.0040 0.8151
14.500 1.3942 0.09724 0.09171 -0.1034 0.0040 0.8166
|
Polar data table (+)
Polar graphs
<< Back to EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il)