EPPLER 678 AIRFOIL (e678-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 678 AIRFOIL (e678-il) Reynolds number: 200,000 Max Cl/Cd: 79.34 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e678-il-200000.txt Download as CSV file: xf-e678-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 678 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2006 0.10232 0.09890 -0.0928 0.9490 0.0539
-8.750 -0.2182 0.09673 0.09337 -0.0993 0.9384 0.0547
-8.500 -0.2335 0.09023 0.08689 -0.1067 0.9286 0.0549
-8.250 -0.1998 0.08848 0.08514 -0.1009 0.9286 0.0566
-8.000 -0.1813 0.08562 0.08227 -0.1025 0.9251 0.0583
-7.750 -0.1671 0.08118 0.07781 -0.1077 0.9223 0.0600
-7.500 -0.1773 0.07709 0.07376 -0.1093 0.9107 0.0617
-7.250 -0.1912 0.07085 0.06751 -0.1154 0.8980 0.0626
-7.000 -0.2146 0.06326 0.05917 -0.1266 0.8813 0.0666
-6.750 -0.1958 0.05641 0.05252 -0.1288 0.8798 0.0687
-6.500 -0.1872 0.05429 0.05039 -0.1273 0.8700 0.0703
-6.250 -0.1645 0.05081 0.04676 -0.1301 0.8664 0.0739
-6.000 -0.1537 0.03797 0.03246 -0.1339 0.8590 0.0466
-5.750 -0.1298 0.03763 0.03216 -0.1348 0.8532 0.0573
-5.500 -0.0905 0.03011 0.02326 -0.1367 0.8517 0.0362
-5.250 -0.0541 0.02759 0.02041 -0.1387 0.8504 0.0359
-5.000 -0.0162 0.02574 0.01825 -0.1407 0.8493 0.0362
-4.750 -0.0006 0.02485 0.01721 -0.1386 0.8399 0.0368
-4.500 0.0328 0.02320 0.01557 -0.1399 0.8378 0.0386
-4.250 0.0688 0.02221 0.01456 -0.1416 0.8362 0.0423
-4.000 0.1061 0.02097 0.01329 -0.1436 0.8352 0.0473
-3.750 0.1247 0.02068 0.01300 -0.1424 0.8273 0.0524
-3.500 0.1600 0.01958 0.01198 -0.1444 0.8245 0.0730
-3.250 0.2009 0.01819 0.01108 -0.1479 0.8232 0.1749
-3.000 0.2447 0.01667 0.01061 -0.1526 0.8224 0.4292
-2.750 0.2804 0.01599 0.01053 -0.1540 0.8211 0.5959
-2.500 0.3150 0.01578 0.01037 -0.1546 0.8199 0.6608
-2.250 0.3240 0.01637 0.01094 -0.1511 0.8105 0.6905
-2.000 0.3540 0.01636 0.01087 -0.1509 0.8084 0.7187
-1.750 0.3853 0.01632 0.01076 -0.1508 0.8068 0.7420
-1.500 0.4170 0.01622 0.01060 -0.1508 0.8055 0.7602
-1.250 0.4218 0.01688 0.01124 -0.1465 0.7968 0.7740
-1.000 0.4507 0.01676 0.01105 -0.1462 0.7946 0.7890
-0.750 0.4824 0.01658 0.01080 -0.1464 0.7930 0.8032
-0.500 0.5128 0.01638 0.01055 -0.1463 0.7917 0.8163
-0.250 0.5129 0.01703 0.01121 -0.1410 0.7840 0.8276
0.000 0.5399 0.01685 0.01099 -0.1405 0.7816 0.8393
0.250 0.5740 0.01658 0.01065 -0.1416 0.7799 0.8500
0.500 0.6065 0.01627 0.01028 -0.1422 0.7785 0.8588
0.750 0.6211 0.01655 0.01055 -0.1399 0.7736 0.8680
1.000 0.6434 0.01665 0.01063 -0.1391 0.7695 0.8776
1.250 0.6722 0.01640 0.01035 -0.1391 0.7672 0.8853
1.500 0.7114 0.01614 0.01003 -0.1415 0.7655 0.8927
1.750 0.7503 0.01577 0.00962 -0.1436 0.7639 0.8986
2.000 0.7589 0.01625 0.01012 -0.1405 0.7578 0.9073
2.250 0.7848 0.01614 0.01000 -0.1402 0.7542 0.9138
2.500 0.8257 0.01588 0.00970 -0.1429 0.7518 0.9196
2.750 0.8732 0.01560 0.00939 -0.1469 0.7497 0.9241
3.000 0.8791 0.01594 0.00977 -0.1431 0.7438 0.9329
3.250 0.9056 0.01595 0.00979 -0.1431 0.7394 0.9397
3.500 0.9493 0.01579 0.00961 -0.1464 0.7364 0.9451
3.750 0.9983 0.01566 0.00943 -0.1508 0.7336 0.9495
4.000 0.9965 0.01613 0.01001 -0.1456 0.7264 0.9620
4.250 1.0363 0.01610 0.00999 -0.1482 0.7221 0.9690
4.500 1.0907 0.01599 0.00984 -0.1537 0.7184 0.9730
4.750 1.1067 0.01646 0.01044 -0.1522 0.7111 1.0000
5.000 1.1463 0.01657 0.01057 -0.1550 0.7057 1.0000
5.250 1.1891 0.01672 0.01071 -0.1584 0.7006 1.0000
5.500 1.2059 0.01716 0.01125 -0.1570 0.6929 1.0000
5.750 1.2527 0.01717 0.01125 -0.1610 0.6871 1.0000
6.000 1.2688 0.01761 0.01180 -0.1594 0.6790 1.0000
6.250 1.3075 0.01764 0.01184 -0.1618 0.6719 1.0000
6.500 1.3281 0.01796 0.01227 -0.1610 0.6638 1.0000
6.750 1.3615 0.01799 0.01235 -0.1623 0.6560 1.0000
7.000 1.3803 0.01823 0.01269 -0.1611 0.6472 1.0000
7.250 1.4147 0.01814 0.01262 -0.1625 0.6388 1.0000
7.500 1.4221 0.01838 0.01300 -0.1589 0.6287 1.0000
7.750 1.4469 0.01833 0.01299 -0.1585 0.6193 1.0000
8.000 1.4598 0.01840 0.01313 -0.1558 0.6083 1.0000
8.250 1.4648 0.01867 0.01352 -0.1518 0.5963 1.0000
8.500 1.4729 0.01890 0.01382 -0.1484 0.5832 1.0000
8.750 1.4788 0.01921 0.01419 -0.1446 0.5676 1.0000
9.000 1.4837 0.01957 0.01457 -0.1407 0.5481 1.0000
9.250 1.4854 0.02017 0.01518 -0.1365 0.5244 1.0000
9.500 1.4874 0.02091 0.01582 -0.1324 0.4935 1.0000
9.750 1.4879 0.02192 0.01663 -0.1283 0.4578 1.0000
10.000 1.4861 0.02327 0.01776 -0.1240 0.4232 1.0000
10.250 1.4832 0.02483 0.01916 -0.1199 0.3906 1.0000
10.500 1.4794 0.02658 0.02075 -0.1160 0.3598 1.0000
10.750 1.4750 0.02848 0.02252 -0.1122 0.3310 1.0000
11.000 1.4703 0.03054 0.02446 -0.1087 0.3025 1.0000
11.250 1.4664 0.03270 0.02651 -0.1055 0.2754 1.0000
11.500 1.4625 0.03501 0.02872 -0.1026 0.2497 1.0000
11.750 1.4593 0.03740 0.03103 -0.1000 0.2267 1.0000
12.000 1.4580 0.03978 0.03335 -0.0978 0.2036 1.0000
12.250 1.4558 0.04237 0.03586 -0.0958 0.1827 1.0000
12.500 1.4554 0.04492 0.03835 -0.0942 0.1613 1.0000
12.750 1.4530 0.04775 0.04110 -0.0925 0.1402 1.0000
13.000 1.4513 0.05063 0.04390 -0.0911 0.1170 1.0000
13.250 1.4458 0.05399 0.04711 -0.0897 0.0913 1.0000
13.500 1.4347 0.05806 0.05096 -0.0881 0.0649 1.0000
13.750 1.4237 0.06229 0.05507 -0.0867 0.0473 1.0000
14.000 1.4177 0.06610 0.05889 -0.0856 0.0397 1.0000
14.250 1.4105 0.07011 0.06293 -0.0848 0.0358 1.0000
14.500 1.4104 0.07336 0.06631 -0.0842 0.0330 1.0000
14.750 1.4088 0.07685 0.06987 -0.0838 0.0310 1.0000
15.000 1.4034 0.08085 0.07392 -0.0835 0.0296 1.0000
15.250 1.4028 0.08428 0.07745 -0.0832 0.0285 1.0000
15.500 1.4054 0.08731 0.08061 -0.0829 0.0274 1.0000
15.750 1.4082 0.09033 0.08372 -0.0828 0.0265 1.0000
16.000 1.4118 0.09324 0.08671 -0.0827 0.0255 1.0000
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Polar data table (+)
Polar graphs
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