EPPLER 657 AIRFOIL (e657-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 657 AIRFOIL (e657-il) Reynolds number: 200,000 Max Cl/Cd: 70.19 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e657-il-200000-n5.txt Download as CSV file: xf-e657-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 657 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 -0.0917 0.09504 0.09033 -0.1178 0.8185 0.0131
-11.500 -0.0878 0.09195 0.08724 -0.1191 0.8157 0.0129
-11.250 -0.0887 0.08779 0.08309 -0.1208 0.8131 0.0128
-11.000 -0.0869 0.08439 0.07967 -0.1223 0.8106 0.0126
-10.750 -0.0925 0.07944 0.07474 -0.1244 0.8081 0.0124
-10.500 -0.1011 0.07404 0.06939 -0.1268 0.8053 0.0121
-10.250 -0.1213 0.06610 0.06151 -0.1306 0.8025 0.0118
-10.000 -0.2434 0.04272 0.03755 -0.1436 0.7973 0.0107
-9.750 -0.2728 0.03876 0.03321 -0.1414 0.7942 0.0105
-9.500 -0.2852 0.03679 0.03102 -0.1385 0.7917 0.0106
-9.250 -0.2912 0.03439 0.02833 -0.1362 0.7889 0.0105
-9.000 -0.2884 0.03245 0.02615 -0.1343 0.7861 0.0106
-8.750 -0.2813 0.03056 0.02396 -0.1327 0.7835 0.0107
-8.500 -0.2695 0.02899 0.02217 -0.1314 0.7813 0.0108
-8.250 -0.2552 0.02744 0.02036 -0.1303 0.7794 0.0110
-8.000 -0.2383 0.02611 0.01878 -0.1293 0.7778 0.0113
-7.750 -0.2193 0.02488 0.01732 -0.1285 0.7763 0.0114
-7.500 -0.1999 0.02376 0.01601 -0.1277 0.7746 0.0118
-7.250 -0.1800 0.02276 0.01487 -0.1269 0.7726 0.0122
-7.000 -0.1594 0.02182 0.01376 -0.1260 0.7703 0.0127
-6.750 -0.1384 0.02098 0.01281 -0.1253 0.7682 0.0133
-6.500 -0.1165 0.02032 0.01210 -0.1247 0.7664 0.0139
-6.250 -0.0934 0.01979 0.01147 -0.1243 0.7647 0.0152
-6.000 -0.0700 0.01925 0.01086 -0.1239 0.7632 0.0167
-5.750 -0.0459 0.01878 0.01032 -0.1236 0.7617 0.0187
-5.500 -0.0217 0.01824 0.00971 -0.1233 0.7603 0.0207
-5.250 0.0025 0.01776 0.00915 -0.1229 0.7588 0.0236
-5.000 0.0251 0.01740 0.00880 -0.1224 0.7566 0.0289
-4.750 0.0485 0.01704 0.00846 -0.1219 0.7546 0.0380
-4.500 0.0724 0.01669 0.00816 -0.1216 0.7527 0.0514
-4.250 0.0966 0.01634 0.00791 -0.1213 0.7508 0.0724
-4.000 0.1213 0.01598 0.00768 -0.1212 0.7488 0.1036
-3.750 0.1466 0.01562 0.00746 -0.1212 0.7471 0.1445
-3.500 0.1724 0.01528 0.00727 -0.1213 0.7457 0.1944
-3.250 0.1986 0.01494 0.00710 -0.1214 0.7444 0.2542
-3.000 0.2252 0.01456 0.00695 -0.1217 0.7431 0.3288
-2.750 0.2481 0.01424 0.00696 -0.1214 0.7408 0.4165
-2.500 0.2702 0.01395 0.00706 -0.1207 0.7384 0.5170
-2.250 0.2924 0.01380 0.00725 -0.1197 0.7361 0.6084
-2.000 0.3150 0.01383 0.00745 -0.1184 0.7339 0.6720
-1.750 0.3397 0.01392 0.00757 -0.1176 0.7319 0.7153
-1.500 0.3643 0.01405 0.00771 -0.1167 0.7302 0.7422
-1.250 0.3896 0.01419 0.00782 -0.1159 0.7286 0.7634
-1.000 0.4164 0.01433 0.00790 -0.1154 0.7271 0.7812
-0.750 0.4412 0.01454 0.00807 -0.1148 0.7250 0.7970
-0.500 0.4620 0.01482 0.00835 -0.1137 0.7216 0.8111
-0.250 0.4858 0.01501 0.00850 -0.1130 0.7187 0.8237
0.000 0.5087 0.01513 0.00860 -0.1119 0.7161 0.8333
0.250 0.5335 0.01519 0.00863 -0.1112 0.7140 0.8430
0.500 0.5605 0.01522 0.00860 -0.1109 0.7121 0.8528
0.750 0.5862 0.01522 0.00856 -0.1102 0.7105 0.8601
1.000 0.6037 0.01547 0.00885 -0.1085 0.7064 0.8697
1.250 0.6208 0.01560 0.00901 -0.1064 0.7024 0.8764
1.500 0.6460 0.01562 0.00901 -0.1060 0.6995 0.8830
1.750 0.6730 0.01556 0.00892 -0.1058 0.6970 0.8881
2.000 0.7013 0.01545 0.00878 -0.1058 0.6950 0.8930
2.250 0.7217 0.01559 0.00894 -0.1047 0.6911 0.8993
2.500 0.7378 0.01572 0.00913 -0.1027 0.6861 0.9051
2.750 0.7625 0.01566 0.00907 -0.1021 0.6828 0.9104
3.000 0.7924 0.01554 0.00892 -0.1026 0.6801 0.9150
3.250 0.8199 0.01541 0.00879 -0.1025 0.6773 0.9191
3.500 0.8286 0.01566 0.00914 -0.0993 0.6705 0.9264
3.750 0.8537 0.01557 0.00907 -0.0989 0.6665 0.9315
4.000 0.8839 0.01535 0.00883 -0.0993 0.6635 0.9355
4.250 0.8946 0.01557 0.00913 -0.0965 0.6567 0.9436
4.500 0.9164 0.01551 0.00913 -0.0955 0.6514 0.9500
4.750 0.9487 0.01526 0.00888 -0.0963 0.6477 0.9547
5.000 0.9588 0.01554 0.00927 -0.0936 0.6390 0.9652
5.250 0.9905 0.01537 0.00912 -0.0945 0.6335 0.9717
5.500 1.0104 0.01559 0.00942 -0.0938 0.6246 0.9928
5.750 1.0387 0.01546 0.00930 -0.0941 0.6179 1.0000
6.000 1.0515 0.01582 0.00972 -0.0922 0.6075 1.0000
6.250 1.0754 0.01586 0.00978 -0.0918 0.5984 1.0000
6.500 1.0988 0.01593 0.00985 -0.0914 0.5876 1.0000
6.750 1.1176 0.01618 0.01013 -0.0904 0.5747 1.0000
7.000 1.1393 0.01635 0.01029 -0.0898 0.5605 1.0000
7.250 1.1608 0.01656 0.01046 -0.0891 0.5448 1.0000
7.500 1.1813 0.01683 0.01066 -0.0883 0.5269 1.0000
7.750 1.1991 0.01723 0.01100 -0.0871 0.5079 1.0000
8.000 1.2132 0.01784 0.01154 -0.0856 0.4879 1.0000
8.250 1.2252 0.01856 0.01218 -0.0838 0.4672 1.0000
8.500 1.2356 0.01941 0.01295 -0.0819 0.4472 1.0000
8.750 1.2446 0.02036 0.01382 -0.0799 0.4275 1.0000
9.000 1.2525 0.02141 0.01481 -0.0779 0.4074 1.0000
9.250 1.2598 0.02254 0.01588 -0.0759 0.3880 1.0000
9.500 1.2665 0.02374 0.01701 -0.0739 0.3690 1.0000
9.750 1.2726 0.02501 0.01823 -0.0719 0.3506 1.0000
10.250 1.2851 0.02767 0.02079 -0.0683 0.3154 1.0000
10.500 1.2918 0.02904 0.02212 -0.0667 0.2985 1.0000
10.750 1.2981 0.03047 0.02353 -0.0651 0.2819 1.0000
11.000 1.3045 0.03195 0.02497 -0.0636 0.2655 1.0000
11.250 1.3107 0.03347 0.02647 -0.0621 0.2501 1.0000
11.500 1.3171 0.03504 0.02801 -0.0608 0.2352 1.0000
11.750 1.3231 0.03668 0.02963 -0.0595 0.2206 1.0000
12.000 1.3292 0.03837 0.03130 -0.0583 0.2068 1.0000
12.250 1.3352 0.04010 0.03303 -0.0572 0.1932 1.0000
12.500 1.3417 0.04185 0.03477 -0.0562 0.1798 1.0000
12.750 1.3480 0.04367 0.03659 -0.0552 0.1671 1.0000
13.000 1.3541 0.04554 0.03847 -0.0543 0.1553 1.0000
13.250 1.3594 0.04752 0.04046 -0.0535 0.1443 1.0000
13.500 1.3640 0.04963 0.04257 -0.0527 0.1336 1.0000
13.750 1.3688 0.05177 0.04472 -0.0520 0.1229 1.0000
14.000 1.3745 0.05387 0.04686 -0.0514 0.1134 1.0000
14.250 1.3786 0.05618 0.04919 -0.0508 0.1047 1.0000
14.500 1.3819 0.05862 0.05165 -0.0503 0.0967 1.0000
14.750 1.3869 0.06093 0.05404 -0.0499 0.0890 1.0000
15.000 1.3894 0.06359 0.05673 -0.0496 0.0825 1.0000
15.250 1.3930 0.06616 0.05936 -0.0494 0.0758 1.0000
15.500 1.3953 0.06894 0.06220 -0.0493 0.0703 1.0000
15.750 1.3969 0.07187 0.06518 -0.0493 0.0647 1.0000
16.000 1.3988 0.07482 0.06822 -0.0493 0.0599 1.0000
16.250 1.3990 0.07805 0.07151 -0.0495 0.0554 1.0000
16.500 1.3998 0.08127 0.07483 -0.0498 0.0515 1.0000
16.750 1.3993 0.08471 0.07834 -0.0503 0.0476 1.0000
17.000 1.3983 0.08828 0.08201 -0.0508 0.0444 1.0000
17.250 1.3974 0.09192 0.08575 -0.0515 0.0411 1.0000
17.500 1.3939 0.09600 0.08989 -0.0524 0.0387 1.0000
17.750 1.3933 0.09968 0.09371 -0.0534 0.0359 1.0000
18.000 1.3893 0.10392 0.09804 -0.0546 0.0336 1.0000
18.250 1.3865 0.10806 0.10229 -0.0558 0.0317 1.0000
18.500 1.3838 0.11222 0.10659 -0.0573 0.0297 1.0000
18.750 1.3784 0.11687 0.11131 -0.0590 0.0281 1.0000
19.000 1.3750 0.12124 0.11581 -0.0607 0.0265 1.0000
19.250 1.3715 0.12565 0.12035 -0.0626 0.0250 1.0000
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Polar data table (+)
Polar graphs
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