EPPLER 657 AIRFOIL (e657-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 657 AIRFOIL (e657-il) Reynolds number: 1,000,000 Max Cl/Cd: 160.62 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e657-il-1000000.txt Download as CSV file: xf-e657-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.0376 0.09023 0.08744 -0.1102 0.7604 0.0130
-11.750 -0.0391 0.08512 0.08233 -0.1121 0.7590 0.0131
-10.000 -0.3588 0.02902 0.02496 -0.1385 0.7526 0.0083
-9.750 -0.3521 0.02785 0.02362 -0.1366 0.7509 0.0082
-9.500 -0.3448 0.02589 0.02158 -0.1349 0.7493 0.0078
-9.250 -0.3389 0.02393 0.01938 -0.1330 0.7476 0.0078
-9.000 -0.3299 0.02192 0.01709 -0.1312 0.7459 0.0077
-8.750 -0.3138 0.02065 0.01562 -0.1301 0.7441 0.0077
-8.500 -0.2970 0.01922 0.01398 -0.1291 0.7424 0.0077
-8.250 -0.2765 0.01824 0.01285 -0.1284 0.7414 0.0077
-8.000 -0.2563 0.01702 0.01149 -0.1276 0.7402 0.0077
-7.750 -0.2345 0.01605 0.01040 -0.1270 0.7389 0.0076
-7.500 -0.2120 0.01517 0.00941 -0.1265 0.7376 0.0076
-7.250 -0.1886 0.01443 0.00859 -0.1261 0.7364 0.0076
-7.000 -0.1647 0.01376 0.00784 -0.1257 0.7351 0.0076
-6.750 -0.1404 0.01315 0.00716 -0.1253 0.7337 0.0077
-6.500 -0.1154 0.01264 0.00658 -0.1251 0.7324 0.0077
-6.250 -0.0900 0.01217 0.00605 -0.1249 0.7310 0.0079
-6.000 -0.0639 0.01179 0.00561 -0.1248 0.7297 0.0080
-5.750 -0.0384 0.01130 0.00505 -0.1247 0.7283 0.0083
-5.500 -0.0120 0.01095 0.00466 -0.1248 0.7265 0.0089
-5.250 0.0153 0.01067 0.00437 -0.1248 0.7256 0.0098
-5.000 0.0424 0.01035 0.00403 -0.1249 0.7245 0.0111
-4.750 0.0698 0.01007 0.00375 -0.1250 0.7234 0.0140
-4.500 0.0970 0.00975 0.00348 -0.1251 0.7222 0.0246
-4.250 0.1246 0.00949 0.00331 -0.1254 0.7209 0.0401
-4.000 0.1525 0.00928 0.00316 -0.1256 0.7196 0.0557
-3.750 0.1804 0.00905 0.00302 -0.1259 0.7182 0.0795
-3.500 0.2084 0.00879 0.00289 -0.1263 0.7168 0.1135
-3.250 0.2363 0.00850 0.00277 -0.1267 0.7155 0.1628
-3.000 0.2642 0.00819 0.00267 -0.1271 0.7142 0.2268
-2.750 0.2922 0.00788 0.00259 -0.1276 0.7127 0.2995
-2.500 0.3208 0.00766 0.00255 -0.1281 0.7110 0.3688
-2.250 0.3493 0.00741 0.00253 -0.1287 0.7095 0.4456
-2.000 0.3777 0.00710 0.00247 -0.1292 0.7083 0.5305
-1.750 0.4063 0.00682 0.00245 -0.1297 0.7068 0.6176
-1.500 0.4350 0.00666 0.00246 -0.1300 0.7051 0.6737
-1.250 0.4640 0.00661 0.00247 -0.1303 0.7033 0.7089
-1.000 0.4932 0.00659 0.00246 -0.1307 0.7014 0.7302
-0.750 0.5222 0.00656 0.00245 -0.1310 0.6995 0.7472
-0.500 0.5510 0.00656 0.00247 -0.1313 0.6976 0.7622
-0.250 0.5799 0.00663 0.00255 -0.1315 0.6954 0.7762
0.000 0.6088 0.00673 0.00264 -0.1318 0.6932 0.7873
0.250 0.6374 0.00675 0.00268 -0.1321 0.6914 0.7970
0.500 0.6661 0.00679 0.00272 -0.1323 0.6892 0.8050
0.750 0.6949 0.00682 0.00274 -0.1326 0.6868 0.8114
1.000 0.7235 0.00685 0.00277 -0.1328 0.6843 0.8171
1.250 0.7526 0.00690 0.00278 -0.1332 0.6818 0.8233
1.500 0.7808 0.00695 0.00283 -0.1333 0.6790 0.8279
1.750 0.8087 0.00699 0.00289 -0.1334 0.6765 0.8328
2.000 0.8369 0.00702 0.00293 -0.1337 0.6738 0.8378
2.250 0.8642 0.00700 0.00294 -0.1336 0.6706 0.8423
2.500 0.8916 0.00700 0.00296 -0.1336 0.6673 0.8466
2.750 0.9199 0.00704 0.00298 -0.1339 0.6637 0.8506
3.000 0.9479 0.00707 0.00302 -0.1341 0.6601 0.8539
3.250 0.9748 0.00703 0.00303 -0.1340 0.6559 0.8572
3.500 1.0017 0.00704 0.00305 -0.1340 0.6516 0.8603
3.750 1.0289 0.00709 0.00308 -0.1340 0.6470 0.8637
4.000 1.0561 0.00710 0.00315 -0.1341 0.6418 0.8670
4.250 1.0832 0.00713 0.00318 -0.1341 0.6356 0.8699
4.500 1.1090 0.00715 0.00322 -0.1339 0.6291 0.8728
4.750 1.1345 0.00719 0.00328 -0.1336 0.6207 0.8756
5.000 1.1597 0.00726 0.00335 -0.1333 0.6112 0.8784
5.250 1.1838 0.00737 0.00344 -0.1327 0.5998 0.8814
5.500 1.2071 0.00752 0.00356 -0.1321 0.5858 0.8841
5.750 1.2286 0.00770 0.00369 -0.1311 0.5687 0.8868
6.000 1.2474 0.00793 0.00388 -0.1295 0.5489 0.8897
6.250 1.2632 0.00825 0.00412 -0.1274 0.5272 0.8932
6.500 1.2767 0.00863 0.00441 -0.1249 0.5037 0.8968
6.750 1.2861 0.00903 0.00472 -0.1215 0.4806 0.9002
7.000 1.2917 0.00946 0.00508 -0.1175 0.4587 0.9037
7.250 1.2990 0.00993 0.00549 -0.1139 0.4380 0.9070
7.500 1.3054 0.01047 0.00596 -0.1103 0.4175 0.9106
7.750 1.3102 0.01112 0.00653 -0.1066 0.3972 0.9144
8.000 1.3160 0.01178 0.00713 -0.1033 0.3775 0.9180
8.250 1.3214 0.01250 0.00781 -0.1000 0.3590 0.9219
8.500 1.3275 0.01330 0.00855 -0.0970 0.3411 0.9260
8.750 1.3325 0.01423 0.00942 -0.0940 0.3216 0.9302
9.000 1.3381 0.01512 0.01029 -0.0911 0.3050 0.9358
9.250 1.3445 0.01605 0.01118 -0.0885 0.2888 0.9429
9.500 1.3499 0.01704 0.01215 -0.0859 0.2715 0.9582
9.750 1.3603 0.01815 0.01320 -0.0846 0.2526 1.0000
10.000 1.3700 0.01925 0.01423 -0.0830 0.2369 1.0000
10.250 1.3793 0.02037 0.01530 -0.0814 0.2211 1.0000
10.500 1.3881 0.02154 0.01640 -0.0798 0.2050 1.0000
10.750 1.3963 0.02277 0.01756 -0.0781 0.1891 1.0000
11.000 1.4055 0.02395 0.01868 -0.0766 0.1754 1.0000
11.250 1.4140 0.02521 0.01989 -0.0751 0.1623 1.0000
11.500 1.4231 0.02644 0.02107 -0.0737 0.1496 1.0000
11.750 1.4323 0.02769 0.02228 -0.0724 0.1380 1.0000
12.000 1.4419 0.02895 0.02350 -0.0711 0.1271 1.0000
12.250 1.4512 0.03025 0.02478 -0.0699 0.1173 1.0000
12.500 1.4587 0.03172 0.02620 -0.0685 0.1061 1.0000
12.750 1.4660 0.03322 0.02764 -0.0673 0.0947 1.0000
13.000 1.4745 0.03468 0.02908 -0.0661 0.0867 1.0000
13.250 1.4833 0.03614 0.03052 -0.0651 0.0783 1.0000
13.500 1.4899 0.03782 0.03217 -0.0640 0.0692 1.0000
13.750 1.4952 0.03963 0.03393 -0.0628 0.0596 1.0000
14.000 1.5025 0.04133 0.03560 -0.0619 0.0537 1.0000
14.250 1.5086 0.04317 0.03743 -0.0610 0.0473 1.0000
14.500 1.5176 0.04479 0.03907 -0.0603 0.0430 1.0000
14.750 1.5231 0.04677 0.04104 -0.0594 0.0384 1.0000
15.000 1.5303 0.04862 0.04291 -0.0588 0.0345 1.0000
15.250 1.5360 0.05065 0.04496 -0.0581 0.0307 1.0000
15.500 1.5414 0.05278 0.04710 -0.0575 0.0275 1.0000
15.750 1.5474 0.05487 0.04923 -0.0571 0.0248 1.0000
16.000 1.5526 0.05710 0.05149 -0.0566 0.0226 1.0000
16.250 1.5572 0.05943 0.05385 -0.0563 0.0204 1.0000
16.500 1.5619 0.06180 0.05627 -0.0560 0.0186 1.0000
16.750 1.5656 0.06433 0.05885 -0.0558 0.0170 1.0000
17.000 1.5695 0.06690 0.06147 -0.0557 0.0156 1.0000
17.250 1.5730 0.06955 0.06418 -0.0556 0.0145 1.0000
17.500 1.5747 0.07247 0.06715 -0.0557 0.0133 1.0000
17.750 1.5775 0.07531 0.07006 -0.0559 0.0124 1.0000
18.000 1.5786 0.07842 0.07324 -0.0561 0.0113 1.0000
18.250 1.5785 0.08177 0.07664 -0.0565 0.0106 1.0000
18.500 1.5802 0.08489 0.07986 -0.0570 0.0099 1.0000
18.750 1.5798 0.08836 0.08341 -0.0576 0.0092 1.0000
19.000 1.5769 0.09225 0.08736 -0.0584 0.0084 1.0000
19.250 1.5772 0.09573 0.09093 -0.0592 0.0079 1.0000
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Polar data table (+)
Polar graphs
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