EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 66 AIRFOIL (e66-il) Reynolds number: 1,000,000 Max Cl/Cd: 153.17 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e66-il-1000000.txt Download as CSV file: xf-e66-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 66 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3599 0.11177 0.11013 -0.0411 0.9970 0.0108
-10.250 -0.3517 0.10517 0.10354 -0.0464 0.9959 0.0119
-9.250 -0.4682 0.02535 0.02249 -0.1245 0.9726 0.0070
-9.000 -0.4531 0.02262 0.01944 -0.1251 0.9668 0.0070
-8.750 -0.4273 0.02009 0.01658 -0.1271 0.9642 0.0071
-8.500 -0.3974 0.01836 0.01463 -0.1291 0.9627 0.0073
-8.250 -0.3654 0.01723 0.01332 -0.1309 0.9617 0.0077
-8.000 -0.3329 0.01592 0.01182 -0.1328 0.9609 0.0080
-7.750 -0.2998 0.01467 0.01038 -0.1346 0.9602 0.0083
-7.500 -0.2656 0.01377 0.00934 -0.1365 0.9596 0.0085
-7.250 -0.2456 0.01235 0.00772 -0.1355 0.9540 0.0090
-7.000 -0.2145 0.01162 0.00692 -0.1366 0.9518 0.0097
-6.750 -0.1817 0.01109 0.00634 -0.1379 0.9501 0.0104
-6.500 -0.1485 0.01057 0.00575 -0.1393 0.9484 0.0111
-6.250 -0.1146 0.01015 0.00527 -0.1407 0.9469 0.0118
-6.000 -0.0863 0.00941 0.00445 -0.1411 0.9428 0.0134
-5.750 -0.0571 0.00910 0.00410 -0.1415 0.9386 0.0150
-5.500 -0.0250 0.00871 0.00365 -0.1425 0.9354 0.0173
-5.250 0.0091 0.00833 0.00325 -0.1440 0.9326 0.0207
-5.000 0.0356 0.00804 0.00290 -0.1437 0.9266 0.0239
-4.750 0.0662 0.00775 0.00260 -0.1443 0.9218 0.0285
-4.500 0.0977 0.00746 0.00231 -0.1452 0.9173 0.0386
-4.250 0.1245 0.00718 0.00211 -0.1451 0.9107 0.0601
-4.000 0.1552 0.00695 0.00192 -0.1458 0.9055 0.0805
-3.750 0.1827 0.00677 0.00179 -0.1457 0.8990 0.1011
-3.500 0.2116 0.00659 0.00165 -0.1460 0.8928 0.1243
-3.250 0.2400 0.00644 0.00154 -0.1462 0.8864 0.1485
-3.000 0.2680 0.00629 0.00144 -0.1463 0.8795 0.1777
-2.750 0.2963 0.00614 0.00136 -0.1464 0.8730 0.2107
-2.500 0.3240 0.00598 0.00130 -0.1464 0.8656 0.2496
-2.250 0.3520 0.00585 0.00123 -0.1465 0.8586 0.2860
-2.000 0.3797 0.00575 0.00119 -0.1465 0.8507 0.3220
-1.750 0.4074 0.00565 0.00115 -0.1465 0.8429 0.3552
-1.500 0.4350 0.00557 0.00112 -0.1465 0.8344 0.3919
-1.250 0.4624 0.00547 0.00111 -0.1464 0.8256 0.4334
-1.000 0.4899 0.00540 0.00110 -0.1463 0.8169 0.4753
-0.750 0.5171 0.00534 0.00111 -0.1462 0.8073 0.5159
-0.500 0.5443 0.00528 0.00112 -0.1460 0.7978 0.5554
-0.250 0.5713 0.00525 0.00114 -0.1458 0.7878 0.5936
0.000 0.5981 0.00523 0.00117 -0.1456 0.7769 0.6316
0.250 0.6248 0.00520 0.00121 -0.1453 0.7656 0.6693
0.500 0.6512 0.00520 0.00126 -0.1449 0.7537 0.7058
0.750 0.6774 0.00521 0.00131 -0.1445 0.7410 0.7405
1.000 0.7031 0.00523 0.00137 -0.1440 0.7279 0.7741
1.250 0.7284 0.00526 0.00144 -0.1433 0.7141 0.8067
1.500 0.7530 0.00531 0.00151 -0.1425 0.6997 0.8391
1.750 0.7768 0.00536 0.00159 -0.1415 0.6847 0.8718
2.000 0.7988 0.00540 0.00167 -0.1401 0.6688 0.9051
2.250 0.8182 0.00543 0.00171 -0.1381 0.6522 0.9456
2.500 0.8455 0.00552 0.00175 -0.1379 0.6331 1.0000
2.750 0.8710 0.00570 0.00184 -0.1375 0.6133 1.0000
3.000 0.8963 0.00588 0.00195 -0.1370 0.5921 1.0000
3.250 0.9211 0.00609 0.00207 -0.1364 0.5701 1.0000
3.500 0.9457 0.00631 0.00219 -0.1357 0.5463 1.0000
3.750 0.9702 0.00655 0.00234 -0.1351 0.5218 1.0000
4.000 0.9939 0.00683 0.00251 -0.1343 0.4940 1.0000
4.250 1.0170 0.00715 0.00269 -0.1335 0.4615 1.0000
4.500 1.0400 0.00749 0.00290 -0.1326 0.4297 1.0000
4.750 1.0625 0.00787 0.00313 -0.1316 0.3961 1.0000
5.000 1.0853 0.00823 0.00336 -0.1308 0.3649 1.0000
5.250 1.1076 0.00864 0.00362 -0.1298 0.3317 1.0000
5.500 1.1283 0.00915 0.00393 -0.1286 0.2912 1.0000
5.750 1.1486 0.00969 0.00428 -0.1273 0.2506 1.0000
6.000 1.1690 0.01022 0.00462 -0.1261 0.2143 1.0000
6.250 1.1894 0.01074 0.00499 -0.1248 0.1830 1.0000
6.500 1.2103 0.01122 0.00534 -0.1237 0.1572 1.0000
6.750 1.2309 0.01170 0.00572 -0.1225 0.1336 1.0000
7.000 1.2507 0.01223 0.00612 -0.1211 0.1110 1.0000
7.250 1.2703 0.01276 0.00655 -0.1198 0.0908 1.0000
7.500 1.2897 0.01327 0.00697 -0.1184 0.0743 1.0000
7.750 1.3081 0.01378 0.00741 -0.1167 0.0597 1.0000
8.000 1.3255 0.01431 0.00787 -0.1150 0.0469 1.0000
8.250 1.3416 0.01491 0.00841 -0.1129 0.0345 1.0000
8.500 1.3566 0.01558 0.00901 -0.1108 0.0237 1.0000
8.750 1.3730 0.01617 0.00957 -0.1089 0.0191 1.0000
9.000 1.3893 0.01675 0.01019 -0.1069 0.0164 1.0000
9.250 1.4061 0.01729 0.01075 -0.1051 0.0147 1.0000
9.500 1.4200 0.01804 0.01152 -0.1029 0.0126 1.0000
9.750 1.4361 0.01861 0.01217 -0.1010 0.0118 1.0000
10.000 1.4521 0.01920 0.01280 -0.0992 0.0110 1.0000
10.250 1.4668 0.01987 0.01352 -0.0973 0.0101 1.0000
10.500 1.4763 0.02092 0.01463 -0.0946 0.0090 1.0000
10.750 1.4889 0.02174 0.01552 -0.0924 0.0085 1.0000
11.000 1.5030 0.02246 0.01631 -0.0906 0.0079 1.0000
11.250 1.5159 0.02327 0.01717 -0.0886 0.0074 1.0000
11.500 1.5275 0.02418 0.01814 -0.0866 0.0069 1.0000
11.750 1.5345 0.02546 0.01950 -0.0840 0.0064 1.0000
12.000 1.5346 0.02730 0.02147 -0.0808 0.0060 1.0000
12.250 1.5463 0.02828 0.02252 -0.0791 0.0058 1.0000
12.500 1.5571 0.02935 0.02367 -0.0773 0.0055 1.0000
12.750 1.5660 0.03060 0.02500 -0.0755 0.0052 1.0000
13.000 1.5748 0.03189 0.02636 -0.0738 0.0050 1.0000
13.250 1.5830 0.03327 0.02780 -0.0722 0.0047 1.0000
13.500 1.5887 0.03490 0.02951 -0.0705 0.0046 1.0000
13.750 1.5908 0.03693 0.03163 -0.0687 0.0044 1.0000
14.000 1.5829 0.04002 0.03487 -0.0665 0.0041 1.0000
14.250 1.5708 0.04375 0.03876 -0.0645 0.0040 1.0000
14.500 1.5733 0.04609 0.04123 -0.0636 0.0039 1.0000
14.750 1.5735 0.04880 0.04406 -0.0627 0.0039 1.0000
15.000 1.5739 0.05159 0.04696 -0.0621 0.0038 1.0000
15.250 1.5723 0.05476 0.05025 -0.0618 0.0037 1.0000
15.500 1.5681 0.05842 0.05404 -0.0617 0.0037 1.0000
15.750 1.5632 0.06235 0.05810 -0.0619 0.0036 1.0000
16.000 1.5575 0.06657 0.06245 -0.0625 0.0036 1.0000
16.250 1.5501 0.07125 0.06728 -0.0634 0.0035 1.0000
16.500 1.5416 0.07632 0.07248 -0.0648 0.0035 1.0000
16.750 1.5316 0.08183 0.07814 -0.0665 0.0034 1.0000
17.000 1.5212 0.08765 0.08410 -0.0687 0.0034 1.0000
17.250 1.5094 0.09397 0.09056 -0.0713 0.0034 1.0000
17.500 1.4971 0.10058 0.09732 -0.0743 0.0033 1.0000
17.750 1.4826 0.10781 0.10469 -0.0778 0.0033 1.0000
18.000 1.4687 0.11514 0.11217 -0.0815 0.0033 1.0000
18.250 1.4535 0.12292 0.12009 -0.0857 0.0033 1.0000
18.500 1.4386 0.13079 0.12810 -0.0901 0.0033 1.0000
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