EPPLER 654 AIRFOIL (e654-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 654 AIRFOIL (e654-il) Reynolds number: 100,000 Max Cl/Cd: 28.31 at α=10.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e654-il-100000-n5.txt Download as CSV file: xf-e654-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 654 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0774 0.09952 0.09371 -0.1152 0.8443 0.0252
-11.500 -0.0787 0.09462 0.08881 -0.1179 0.8394 0.0257
-11.250 -0.0824 0.08951 0.08372 -0.1203 0.8341 0.0255
-10.750 -0.1533 0.06435 0.05845 -0.1351 0.8258 0.0223
-10.500 -0.1873 0.05662 0.05052 -0.1410 0.8202 0.0223
-10.250 -0.2058 0.05242 0.04615 -0.1431 0.8145 0.0222
-10.000 -0.2232 0.04888 0.04239 -0.1438 0.8093 0.0221
-9.750 -0.2404 0.04593 0.03919 -0.1430 0.8043 0.0222
-9.500 -0.2553 0.04388 0.03693 -0.1407 0.7987 0.0222
-9.250 -0.2673 0.04113 0.03373 -0.1387 0.7941 0.0226
-9.000 -0.2632 0.03917 0.03151 -0.1375 0.7907 0.0229
-8.750 -0.2543 0.03758 0.02973 -0.1364 0.7876 0.0234
-8.500 -0.2453 0.03605 0.02801 -0.1350 0.7837 0.0238
-8.250 -0.2332 0.03449 0.02621 -0.1338 0.7801 0.0244
-8.000 -0.2182 0.03290 0.02433 -0.1328 0.7769 0.0252
-7.750 -0.2000 0.03128 0.02239 -0.1319 0.7741 0.0262
-7.500 -0.1797 0.03015 0.02110 -0.1314 0.7718 0.0276
-7.250 -0.1631 0.02944 0.02031 -0.1303 0.7683 0.0297
-7.000 -0.1452 0.02857 0.01930 -0.1292 0.7651 0.0318
-6.750 -0.1263 0.02783 0.01852 -0.1283 0.7621 0.0340
-6.500 -0.1062 0.02693 0.01749 -0.1274 0.7594 0.0367
-6.250 -0.0849 0.02624 0.01677 -0.1268 0.7569 0.0405
-6.000 -0.0624 0.02554 0.01600 -0.1264 0.7548 0.0461
-5.750 -0.0443 0.02505 0.01551 -0.1253 0.7518 0.0528
-5.500 -0.0274 0.02466 0.01514 -0.1241 0.7484 0.0611
-5.250 -0.0081 0.02423 0.01472 -0.1232 0.7455 0.0730
-5.000 0.0130 0.02374 0.01428 -0.1226 0.7427 0.0897
-4.750 0.0363 0.02322 0.01383 -0.1223 0.7404 0.1146
-4.500 0.0607 0.02265 0.01341 -0.1222 0.7383 0.1506
-4.250 0.0861 0.02211 0.01304 -0.1224 0.7367 0.2025
-4.000 0.1000 0.02203 0.01324 -0.1209 0.7328 0.2575
-3.750 0.1179 0.02178 0.01331 -0.1201 0.7293 0.3321
-3.500 0.1387 0.02145 0.01335 -0.1194 0.7264 0.4240
-3.250 0.1600 0.02133 0.01362 -0.1180 0.7240 0.5181
-3.000 0.1827 0.02154 0.01398 -0.1164 0.7220 0.5864
-2.750 0.2090 0.02181 0.01417 -0.1156 0.7204 0.6324
-2.500 0.2279 0.02233 0.01464 -0.1139 0.7175 0.6611
-2.250 0.2399 0.02302 0.01531 -0.1116 0.7126 0.6834
-2.000 0.2596 0.02347 0.01567 -0.1100 0.7093 0.7024
-1.750 0.2820 0.02381 0.01592 -0.1088 0.7069 0.7191
-1.500 0.3049 0.02410 0.01613 -0.1074 0.7049 0.7333
-1.250 0.3302 0.02428 0.01621 -0.1065 0.7033 0.7465
-1.000 0.3384 0.02503 0.01695 -0.1036 0.6984 0.7588
-0.750 0.3471 0.02574 0.01766 -0.1008 0.6934 0.7707
-0.500 0.3652 0.02604 0.01792 -0.0989 0.6904 0.7807
-0.250 0.3912 0.02615 0.01793 -0.0985 0.6883 0.7919
0.000 0.4167 0.02618 0.01788 -0.0977 0.6866 0.8008
0.250 0.4468 0.02616 0.01776 -0.0980 0.6853 0.8095
0.750 0.4486 0.02796 0.01962 -0.0907 0.6723 0.8265
1.000 0.4755 0.02793 0.01953 -0.0903 0.6705 0.8334
1.250 0.5093 0.02783 0.01934 -0.0915 0.6691 0.8404
1.750 0.5069 0.02976 0.02133 -0.0840 0.6551 0.8555
2.000 0.5371 0.02958 0.02110 -0.0842 0.6535 0.8605
2.250 0.5703 0.02938 0.02085 -0.0850 0.6522 0.8658
2.750 0.5754 0.03156 0.02308 -0.0795 0.6375 0.8807
3.000 0.5911 0.03227 0.02379 -0.0786 0.6324 0.8877
3.250 0.6442 0.03086 0.02231 -0.0811 0.6352 0.8911
3.750 0.6545 0.03303 0.02456 -0.0768 0.6201 0.9074
4.000 0.6886 0.03251 0.02404 -0.0773 0.6190 0.9137
4.500 0.6923 0.03541 0.02705 -0.0732 0.6003 0.9362
5.500 0.7784 0.03776 0.02954 -0.0745 0.5755 1.0000
5.750 0.8143 0.03735 0.02913 -0.0757 0.5736 1.0000
6.000 0.8517 0.03675 0.02855 -0.0770 0.5722 1.0000
6.500 0.8879 0.03835 0.03023 -0.0769 0.5575 1.0000
7.000 0.9252 0.03976 0.03172 -0.0766 0.5429 1.0000
7.250 0.9615 0.03895 0.03094 -0.0774 0.5411 1.0000
7.500 0.9632 0.04100 0.03305 -0.0762 0.5283 1.0000
7.750 0.9991 0.04012 0.03221 -0.0769 0.5261 1.0000
8.750 1.0789 0.04186 0.03418 -0.0756 0.4953 1.0000
9.000 1.0858 0.04346 0.03583 -0.0746 0.4831 1.0000
9.250 1.1230 0.04225 0.03469 -0.0750 0.4792 1.0000
9.500 1.1309 0.04376 0.03625 -0.0741 0.4667 1.0000
9.750 1.1517 0.04406 0.03662 -0.0737 0.4574 1.0000
10.000 1.1794 0.04370 0.03630 -0.0735 0.4492 1.0000
10.250 1.1948 0.04452 0.03718 -0.0729 0.4373 1.0000
10.500 1.2226 0.04414 0.03683 -0.0727 0.4278 1.0000
10.750 1.2472 0.04406 0.03676 -0.0724 0.4165 1.0000
11.000 1.2616 0.04496 0.03769 -0.0717 0.4031 1.0000
11.250 1.2781 0.04568 0.03843 -0.0710 0.3899 1.0000
11.500 1.2950 0.04635 0.03912 -0.0704 0.3765 1.0000
11.750 1.3110 0.04712 0.03988 -0.0697 0.3628 1.0000
12.000 1.3254 0.04805 0.04079 -0.0690 0.3489 1.0000
12.250 1.3375 0.04921 0.04193 -0.0682 0.3348 1.0000
12.500 1.3444 0.05095 0.04371 -0.0674 0.3208 1.0000
12.750 1.3514 0.05273 0.04551 -0.0666 0.3071 1.0000
13.000 1.3581 0.05458 0.04737 -0.0659 0.2936 1.0000
13.250 1.3646 0.05646 0.04926 -0.0652 0.2805 1.0000
13.500 1.3710 0.05839 0.05120 -0.0645 0.2679 1.0000
13.750 1.3767 0.06041 0.05320 -0.0639 0.2555 1.0000
14.000 1.3796 0.06286 0.05571 -0.0635 0.2432 1.0000
14.250 1.3829 0.06531 0.05821 -0.0630 0.2315 1.0000
14.500 1.3863 0.06776 0.06068 -0.0627 0.2203 1.0000
14.750 1.3892 0.07027 0.06318 -0.0623 0.2097 1.0000
15.000 1.3906 0.07314 0.06615 -0.0622 0.1989 1.0000
15.250 1.3924 0.07598 0.06903 -0.0621 0.1889 1.0000
15.500 1.3937 0.07883 0.07188 -0.0621 0.1797 1.0000
15.750 1.3941 0.08200 0.07516 -0.0622 0.1700 1.0000
16.000 1.3947 0.08511 0.07832 -0.0624 0.1615 1.0000
16.250 1.3941 0.08843 0.08167 -0.0627 0.1531 1.0000
16.500 1.3942 0.09177 0.08513 -0.0631 0.1451 1.0000
16.750 1.3931 0.09521 0.08856 -0.0636 0.1379 1.0000
17.000 1.3923 0.09879 0.09230 -0.0643 0.1303 1.0000
17.250 1.3907 0.10239 0.09587 -0.0650 0.1240 1.0000
17.500 1.3895 0.10612 0.09978 -0.0660 0.1171 1.0000
17.750 1.3876 0.10984 0.10347 -0.0669 0.1115 1.0000
18.000 1.3861 0.11371 0.10753 -0.0681 0.1053 1.0000
18.500 1.3822 0.12149 0.11547 -0.0707 0.0949 1.0000
18.750 1.3795 0.12554 0.11959 -0.0723 0.0901 1.0000
19.000 1.3781 0.12941 0.12352 -0.0739 0.0856 1.0000
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Polar data table (+)
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