EPPLER 657 AIRFOIL (e657-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 657 AIRFOIL (e657-il) Reynolds number: 1,000,000 Max Cl/Cd: 145.03 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e657-il-1000000-n5.txt Download as CSV file: xf-e657-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.2629 0.08645 0.08331 -0.1164 0.7510 0.0041
-13.500 -0.3516 0.06706 0.06378 -0.1254 0.7499 0.0040
-13.250 -0.4117 0.05204 0.04858 -0.1341 0.7480 0.0039
-13.000 -0.4607 0.04009 0.03635 -0.1429 0.7455 0.0038
-12.500 -0.4764 0.03361 0.02963 -0.1455 0.7412 0.0038
-12.250 -0.4955 0.03023 0.02607 -0.1448 0.7390 0.0038
-12.000 -0.4955 0.02861 0.02434 -0.1437 0.7371 0.0039
-11.750 -0.5040 0.02656 0.02213 -0.1415 0.7351 0.0039
-11.500 -0.4978 0.02558 0.02106 -0.1399 0.7333 0.0039
-11.250 -0.5025 0.02411 0.01945 -0.1368 0.7313 0.0039
-11.000 -0.4972 0.02341 0.01865 -0.1342 0.7296 0.0039
-10.750 -0.4899 0.02224 0.01732 -0.1322 0.7279 0.0039
-10.250 -0.4613 0.02050 0.01535 -0.1297 0.7252 0.0040
-10.000 -0.4455 0.01956 0.01429 -0.1285 0.7239 0.0040
-9.750 -0.4278 0.01872 0.01333 -0.1276 0.7225 0.0040
-9.500 -0.4088 0.01793 0.01243 -0.1268 0.7211 0.0040
-9.250 -0.3891 0.01714 0.01154 -0.1260 0.7197 0.0040
-9.000 -0.3699 0.01624 0.01052 -0.1252 0.7184 0.0041
-8.750 -0.3486 0.01553 0.00971 -0.1246 0.7171 0.0041
-8.500 -0.3273 0.01477 0.00884 -0.1239 0.7159 0.0042
-8.250 -0.3041 0.01420 0.00819 -0.1235 0.7146 0.0042
-8.000 -0.2810 0.01361 0.00751 -0.1231 0.7134 0.0043
-7.750 -0.2564 0.01317 0.00700 -0.1229 0.7120 0.0043
-7.500 -0.2315 0.01274 0.00650 -0.1227 0.7105 0.0044
-7.250 -0.2058 0.01236 0.00608 -0.1226 0.7093 0.0045
-7.000 -0.1798 0.01199 0.00568 -0.1226 0.7084 0.0046
-6.750 -0.1534 0.01166 0.00532 -0.1226 0.7075 0.0048
-6.500 -0.1268 0.01136 0.00498 -0.1226 0.7064 0.0049
-6.250 -0.0999 0.01107 0.00467 -0.1226 0.7053 0.0052
-6.000 -0.0728 0.01082 0.00438 -0.1227 0.7041 0.0054
-5.750 -0.0454 0.01058 0.00411 -0.1228 0.7028 0.0058
-5.500 -0.0181 0.01033 0.00384 -0.1229 0.7015 0.0063
-5.250 0.0094 0.01010 0.00360 -0.1231 0.7003 0.0070
-5.000 0.0371 0.00992 0.00339 -0.1233 0.6992 0.0078
-4.750 0.0649 0.00973 0.00319 -0.1235 0.6979 0.0094
-4.500 0.0927 0.00955 0.00301 -0.1237 0.6965 0.0122
-4.250 0.1206 0.00938 0.00284 -0.1239 0.6952 0.0175
-4.000 0.1487 0.00922 0.00271 -0.1242 0.6938 0.0250
-3.750 0.1768 0.00903 0.00257 -0.1244 0.6929 0.0357
-3.500 0.2050 0.00884 0.00245 -0.1248 0.6918 0.0509
-3.250 0.2330 0.00860 0.00233 -0.1251 0.6906 0.0761
-3.000 0.2611 0.00837 0.00223 -0.1255 0.6893 0.1101
-2.750 0.2893 0.00813 0.00213 -0.1258 0.6879 0.1502
-2.500 0.3178 0.00795 0.00205 -0.1262 0.6864 0.1835
-2.250 0.3463 0.00778 0.00198 -0.1267 0.6849 0.2199
-2.000 0.3749 0.00760 0.00192 -0.1271 0.6834 0.2606
-1.750 0.4033 0.00736 0.00186 -0.1276 0.6817 0.3229
-1.500 0.4319 0.00715 0.00181 -0.1281 0.6798 0.3840
-1.250 0.4606 0.00695 0.00177 -0.1286 0.6778 0.4478
-0.750 0.5187 0.00653 0.00174 -0.1297 0.6741 0.5767
-0.500 0.5478 0.00639 0.00174 -0.1302 0.6718 0.6262
-0.250 0.5767 0.00629 0.00175 -0.1306 0.6693 0.6698
0.000 0.6055 0.00626 0.00177 -0.1309 0.6667 0.7005
0.250 0.6342 0.00626 0.00178 -0.1313 0.6641 0.7190
0.500 0.6629 0.00627 0.00180 -0.1316 0.6616 0.7332
0.750 0.6917 0.00625 0.00185 -0.1319 0.6589 0.7460
1.000 0.7202 0.00625 0.00190 -0.1322 0.6556 0.7588
1.250 0.7483 0.00628 0.00196 -0.1323 0.6519 0.7723
1.500 0.7762 0.00634 0.00202 -0.1324 0.6482 0.7849
1.750 0.8048 0.00639 0.00208 -0.1327 0.6447 0.7952
2.000 0.8332 0.00645 0.00215 -0.1330 0.6404 0.8030
2.250 0.8613 0.00651 0.00219 -0.1332 0.6354 0.8102
2.500 0.8887 0.00658 0.00225 -0.1333 0.6300 0.8151
2.750 0.9165 0.00664 0.00232 -0.1334 0.6229 0.8193
3.000 0.9435 0.00673 0.00237 -0.1335 0.6153 0.8229
3.250 0.9703 0.00680 0.00243 -0.1334 0.6060 0.8256
3.500 0.9961 0.00690 0.00252 -0.1332 0.5958 0.8285
3.750 1.0210 0.00704 0.00262 -0.1328 0.5832 0.8315
4.000 1.0448 0.00722 0.00275 -0.1323 0.5674 0.8345
4.250 1.0676 0.00745 0.00290 -0.1315 0.5494 0.8372
4.500 1.0883 0.00772 0.00310 -0.1303 0.5283 0.8396
4.750 1.1070 0.00805 0.00333 -0.1288 0.5061 0.8420
5.000 1.1247 0.00839 0.00359 -0.1271 0.4830 0.8444
5.500 1.1560 0.00914 0.00417 -0.1229 0.4405 0.8497
5.750 1.1676 0.00949 0.00445 -0.1200 0.4214 0.8525
6.000 1.1774 0.00992 0.00480 -0.1168 0.4013 0.8556
6.250 1.1882 0.01034 0.00518 -0.1139 0.3842 0.8585
6.500 1.1963 0.01088 0.00564 -0.1106 0.3646 0.8611
6.750 1.2066 0.01140 0.00610 -0.1079 0.3477 0.8633
7.000 1.2161 0.01198 0.00663 -0.1051 0.3305 0.8656
7.250 1.2245 0.01266 0.00724 -0.1023 0.3125 0.8680
7.750 1.2423 0.01411 0.00859 -0.0971 0.2803 0.8722
8.000 1.2522 0.01487 0.00932 -0.0949 0.2665 0.8744
8.250 1.2614 0.01571 0.01011 -0.0926 0.2514 0.8765
8.500 1.2703 0.01662 0.01096 -0.0904 0.2354 0.8788
8.750 1.2797 0.01754 0.01184 -0.0884 0.2206 0.8811
9.000 1.2902 0.01844 0.01270 -0.0866 0.2083 0.8834
9.250 1.3014 0.01933 0.01356 -0.0849 0.1958 0.8854
9.500 1.3111 0.02030 0.01450 -0.0831 0.1824 0.8882
9.750 1.3210 0.02128 0.01545 -0.0813 0.1704 0.8914
10.000 1.3315 0.02225 0.01640 -0.0797 0.1593 0.8947
10.250 1.3406 0.02334 0.01745 -0.0780 0.1472 0.8983
10.750 1.3589 0.02554 0.01960 -0.0747 0.1238 0.9068
11.000 1.3690 0.02662 0.02066 -0.0732 0.1137 0.9120
11.250 1.3783 0.02775 0.02178 -0.0717 0.1043 0.9184
11.500 1.3865 0.02893 0.02297 -0.0701 0.0952 0.9290
11.750 1.3984 0.02999 0.02408 -0.0691 0.0875 0.9578
12.750 1.4386 0.03533 0.02935 -0.0651 0.0586 1.0000
13.000 1.4486 0.03672 0.03073 -0.0642 0.0535 1.0000
13.250 1.4578 0.03821 0.03222 -0.0633 0.0481 1.0000
13.500 1.4650 0.03989 0.03387 -0.0623 0.0411 1.0000
14.000 1.4785 0.04344 0.03740 -0.0605 0.0297 1.0000
14.250 1.4848 0.04533 0.03927 -0.0596 0.0244 1.0000
14.500 1.4927 0.04710 0.04106 -0.0589 0.0222 1.0000
14.750 1.5005 0.04891 0.04289 -0.0583 0.0197 1.0000
15.000 1.5083 0.05076 0.04478 -0.0578 0.0178 1.0000
15.250 1.5146 0.05280 0.04685 -0.0572 0.0155 1.0000
15.500 1.5215 0.05482 0.04891 -0.0568 0.0138 1.0000
15.750 1.5278 0.05694 0.05106 -0.0564 0.0125 1.0000
16.000 1.5340 0.05909 0.05326 -0.0561 0.0113 1.0000
16.250 1.5391 0.06143 0.05565 -0.0558 0.0103 1.0000
16.500 1.5444 0.06377 0.05805 -0.0556 0.0092 1.0000
16.750 1.5484 0.06632 0.06065 -0.0555 0.0083 1.0000
17.000 1.5531 0.06884 0.06324 -0.0555 0.0076 1.0000
17.250 1.5571 0.07147 0.06593 -0.0555 0.0069 1.0000
17.500 1.5594 0.07437 0.06889 -0.0557 0.0064 1.0000
17.750 1.5627 0.07719 0.07178 -0.0559 0.0058 1.0000
18.000 1.5633 0.08042 0.07508 -0.0563 0.0051 1.0000
18.250 1.5645 0.08364 0.07836 -0.0567 0.0047 1.0000
18.500 1.5654 0.08691 0.08172 -0.0573 0.0043 1.0000
18.750 1.5655 0.09035 0.08523 -0.0580 0.0039 1.0000
19.000 1.5634 0.09417 0.08914 -0.0588 0.0035 1.0000
19.250 1.5623 0.09790 0.09296 -0.0598 0.0032 1.0000
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Polar data table (+)
Polar graphs
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