EPPLER 656 AIRFOIL (e656-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 656 AIRFOIL (e656-il) Reynolds number: 1,000,000 Max Cl/Cd: 161.29 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e656-il-1000000.txt Download as CSV file: xf-e656-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 656 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0791 0.09285 0.08975 -0.1146 0.7209 0.0128
-11.500 -0.0825 0.08749 0.08440 -0.1169 0.7191 0.0129
-11.250 -0.0900 0.08257 0.07950 -0.1188 0.7173 0.0131
-11.000 -0.0860 0.08004 0.07697 -0.1200 0.7154 0.0132
-10.750 -0.0881 0.07587 0.07281 -0.1219 0.7135 0.0132
-9.500 -0.3594 0.02644 0.02184 -0.1277 0.7040 0.0082
-9.250 -0.3444 0.02510 0.02047 -0.1267 0.7024 0.0077
-9.000 -0.3410 0.02244 0.01752 -0.1244 0.7006 0.0074
-8.750 -0.3281 0.02066 0.01551 -0.1229 0.6989 0.0072
-8.500 -0.3129 0.01896 0.01354 -0.1216 0.6970 0.0070
-8.250 -0.2954 0.01742 0.01176 -0.1204 0.6952 0.0067
-8.000 -0.2747 0.01639 0.01057 -0.1196 0.6933 0.0066
-7.750 -0.2525 0.01559 0.00965 -0.1190 0.6913 0.0066
-7.500 -0.2295 0.01485 0.00882 -0.1185 0.6904 0.0066
-7.250 -0.2059 0.01418 0.00808 -0.1181 0.6893 0.0066
-7.000 -0.1816 0.01361 0.00745 -0.1178 0.6880 0.0066
-6.750 -0.1568 0.01309 0.00687 -0.1175 0.6866 0.0067
-6.500 -0.1315 0.01262 0.00635 -0.1173 0.6851 0.0068
-6.250 -0.1057 0.01220 0.00588 -0.1172 0.6836 0.0069
-6.000 -0.0795 0.01180 0.00544 -0.1171 0.6822 0.0071
-5.750 -0.0529 0.01146 0.00505 -0.1171 0.6809 0.0073
-5.500 -0.0259 0.01115 0.00469 -0.1171 0.6796 0.0077
-5.250 0.0014 0.01090 0.00440 -0.1172 0.6781 0.0080
-5.000 0.0282 0.01056 0.00401 -0.1172 0.6764 0.0092
-4.750 0.0558 0.01033 0.00376 -0.1173 0.6742 0.0121
-4.500 0.0830 0.00999 0.00348 -0.1174 0.6732 0.0229
-4.250 0.1108 0.00975 0.00331 -0.1177 0.6723 0.0361
-4.000 0.1388 0.00955 0.00317 -0.1179 0.6712 0.0491
-3.750 0.1669 0.00935 0.00304 -0.1182 0.6700 0.0660
-3.500 0.1949 0.00911 0.00291 -0.1185 0.6686 0.0911
-3.250 0.2230 0.00887 0.00279 -0.1189 0.6671 0.1253
-3.000 0.2508 0.00855 0.00273 -0.1193 0.6657 0.1980
-2.750 0.2797 0.00845 0.00268 -0.1197 0.6644 0.2231
-2.500 0.3086 0.00834 0.00258 -0.1201 0.6630 0.2370
-2.250 0.3375 0.00823 0.00250 -0.1205 0.6616 0.2513
-2.000 0.3660 0.00798 0.00245 -0.1210 0.6600 0.3179
-1.750 0.3948 0.00774 0.00243 -0.1216 0.6582 0.3962
-1.500 0.4237 0.00748 0.00244 -0.1223 0.6565 0.4895
-1.250 0.4526 0.00719 0.00241 -0.1229 0.6554 0.5771
-1.000 0.4816 0.00700 0.00241 -0.1233 0.6541 0.6413
-0.750 0.5104 0.00688 0.00245 -0.1237 0.6526 0.6937
-0.500 0.5393 0.00685 0.00250 -0.1239 0.6508 0.7274
-0.250 0.5684 0.00686 0.00252 -0.1243 0.6489 0.7452
0.000 0.5976 0.00689 0.00254 -0.1246 0.6470 0.7592
0.250 0.6265 0.00692 0.00258 -0.1249 0.6451 0.7714
0.500 0.6558 0.00698 0.00260 -0.1253 0.6432 0.7800
0.750 0.6848 0.00708 0.00269 -0.1256 0.6407 0.7864
1.000 0.7138 0.00713 0.00275 -0.1260 0.6388 0.7926
1.250 0.7427 0.00714 0.00276 -0.1263 0.6370 0.7977
1.500 0.7710 0.00715 0.00279 -0.1265 0.6347 0.8023
1.750 0.7997 0.00716 0.00282 -0.1268 0.6323 0.8068
2.000 0.8285 0.00719 0.00283 -0.1272 0.6298 0.8116
2.250 0.8572 0.00722 0.00285 -0.1275 0.6272 0.8162
2.500 0.8852 0.00730 0.00292 -0.1276 0.6241 0.8216
2.750 0.9131 0.00735 0.00300 -0.1278 0.6216 0.8275
3.000 0.9414 0.00737 0.00305 -0.1280 0.6189 0.8318
3.250 0.9693 0.00737 0.00307 -0.1282 0.6159 0.8353
3.500 0.9970 0.00738 0.00311 -0.1283 0.6128 0.8387
3.750 1.0247 0.00743 0.00316 -0.1284 0.6094 0.8424
4.000 1.0524 0.00750 0.00323 -0.1286 0.6058 0.8462
4.250 1.0802 0.00751 0.00328 -0.1288 0.6018 0.8494
4.500 1.1073 0.00751 0.00332 -0.1288 0.5973 0.8527
4.750 1.1336 0.00757 0.00337 -0.1287 0.5925 0.8559
5.000 1.1605 0.00761 0.00345 -0.1287 0.5876 0.8592
5.250 1.1873 0.00765 0.00353 -0.1287 0.5815 0.8624
5.500 1.2131 0.00775 0.00360 -0.1286 0.5752 0.8655
5.750 1.2398 0.00779 0.00369 -0.1286 0.5680 0.8685
6.000 1.2637 0.00790 0.00379 -0.1280 0.5594 0.8715
6.250 1.2887 0.00799 0.00391 -0.1277 0.5491 0.8743
6.500 1.3119 0.00814 0.00405 -0.1271 0.5372 0.8773
6.750 1.3334 0.00836 0.00423 -0.1262 0.5221 0.8804
7.000 1.3532 0.00863 0.00445 -0.1249 0.5045 0.8834
7.250 1.3688 0.00896 0.00472 -0.1229 0.4840 0.8873
7.500 1.3809 0.00937 0.00506 -0.1202 0.4625 0.8914
7.750 1.3890 0.00979 0.00541 -0.1167 0.4411 0.8957
8.000 1.3955 0.01028 0.00583 -0.1130 0.4213 0.9001
8.250 1.4003 0.01080 0.00631 -0.1091 0.4029 0.9055
8.500 1.4034 0.01145 0.00690 -0.1051 0.3837 0.9114
8.750 1.4054 0.01215 0.00756 -0.1011 0.3659 0.9188
9.000 1.4063 0.01298 0.00835 -0.0971 0.3483 0.9272
9.250 1.4059 0.01384 0.00921 -0.0931 0.3323 0.9412
9.500 1.4093 0.01480 0.01018 -0.0902 0.3155 1.0000
9.750 1.4151 0.01600 0.01132 -0.0880 0.2984 1.0000
10.000 1.4199 0.01730 0.01256 -0.0859 0.2814 1.0000
10.250 1.4241 0.01867 0.01387 -0.0837 0.2648 1.0000
10.500 1.4286 0.02007 0.01521 -0.0817 0.2497 1.0000
10.750 1.4327 0.02152 0.01660 -0.0796 0.2349 1.0000
11.000 1.4382 0.02293 0.01797 -0.0778 0.2211 1.0000
11.250 1.4431 0.02439 0.01938 -0.0761 0.2070 1.0000
11.500 1.4478 0.02590 0.02084 -0.0743 0.1929 1.0000
11.750 1.4527 0.02743 0.02233 -0.0727 0.1802 1.0000
12.000 1.4580 0.02898 0.02383 -0.0712 0.1677 1.0000
12.250 1.4633 0.03057 0.02539 -0.0697 0.1568 1.0000
12.500 1.4692 0.03216 0.02694 -0.0684 0.1461 1.0000
12.750 1.4754 0.03378 0.02852 -0.0672 0.1355 1.0000
13.000 1.4828 0.03532 0.03005 -0.0661 0.1260 1.0000
13.250 1.4880 0.03709 0.03179 -0.0650 0.1167 1.0000
13.500 1.4937 0.03885 0.03351 -0.0640 0.1071 1.0000
13.750 1.4997 0.04064 0.03528 -0.0630 0.0981 1.0000
14.000 1.5061 0.04242 0.03705 -0.0622 0.0902 1.0000
14.250 1.5117 0.04430 0.03890 -0.0613 0.0824 1.0000
14.500 1.5152 0.04644 0.04101 -0.0605 0.0742 1.0000
14.750 1.5224 0.04827 0.04284 -0.0599 0.0683 1.0000
15.000 1.5265 0.05044 0.04500 -0.0592 0.0613 1.0000
15.250 1.5313 0.05258 0.04713 -0.0586 0.0555 1.0000
15.500 1.5350 0.05487 0.04941 -0.0581 0.0498 1.0000
15.750 1.5414 0.05695 0.05153 -0.0578 0.0464 1.0000
16.000 1.5447 0.05937 0.05393 -0.0574 0.0407 1.0000
16.250 1.5473 0.06195 0.05652 -0.0571 0.0364 1.0000
16.500 1.5510 0.06441 0.05900 -0.0569 0.0331 1.0000
16.750 1.5549 0.06695 0.06158 -0.0568 0.0304 1.0000
17.000 1.5585 0.06954 0.06420 -0.0567 0.0276 1.0000
17.250 1.5599 0.07246 0.06715 -0.0568 0.0251 1.0000
17.500 1.5637 0.07511 0.06985 -0.0569 0.0231 1.0000
17.750 1.5642 0.07824 0.07303 -0.0571 0.0214 1.0000
18.000 1.5675 0.08105 0.07590 -0.0574 0.0197 1.0000
18.250 1.5668 0.08445 0.07934 -0.0579 0.0181 1.0000
18.500 1.5693 0.08747 0.08243 -0.0584 0.0169 1.0000
18.750 1.5690 0.09089 0.08590 -0.0590 0.0158 1.0000
19.000 1.5688 0.09436 0.08944 -0.0597 0.0147 1.0000
19.250 1.5690 0.09779 0.09294 -0.0605 0.0136 1.0000
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Polar data table (+)
Polar graphs
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