EPPLER 678 AIRFOIL (e678-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 678 AIRFOIL (e678-il) Reynolds number: 200,000 Max Cl/Cd: 78.13 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e678-il-200000-n5.txt Download as CSV file: xf-e678-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.0939 0.09179 0.08777 -0.1243 0.9309 0.0166
-10.000 -0.0983 0.08705 0.08306 -0.1261 0.9279 0.0168
-9.750 -0.0976 0.08202 0.07804 -0.1294 0.9257 0.0167
-9.500 -0.0945 0.07657 0.07261 -0.1337 0.9238 0.0165
-9.250 -0.1108 0.07156 0.06764 -0.1345 0.9185 0.0165
-9.000 -0.1302 0.06499 0.06111 -0.1370 0.9130 0.0161
-8.750 -0.1728 0.05159 0.04748 -0.1483 0.9081 0.0154
-8.500 -0.2149 0.04897 0.04478 -0.1427 0.8962 0.0150
-8.250 -0.2313 0.04503 0.04060 -0.1418 0.8894 0.0151
-8.000 -0.2417 0.04122 0.03646 -0.1403 0.8820 0.0152
-7.750 -0.2328 0.03581 0.03045 -0.1423 0.8791 0.0151
-7.500 -0.2370 0.03347 0.02779 -0.1386 0.8696 0.0151
-7.250 -0.2156 0.03035 0.02419 -0.1396 0.8663 0.0151
-7.000 -0.1872 0.02782 0.02124 -0.1411 0.8644 0.0153
-6.750 -0.1754 0.02643 0.01960 -0.1389 0.8567 0.0155
-6.500 -0.1512 0.02486 0.01776 -0.1389 0.8523 0.0159
-6.250 -0.1207 0.02334 0.01600 -0.1400 0.8499 0.0163
-5.750 -0.0793 0.02144 0.01378 -0.1380 0.8365 0.0172
-5.250 -0.0357 0.02004 0.01230 -0.1367 0.8208 0.0189
-5.000 -0.0181 0.01968 0.01187 -0.1352 0.8085 0.0204
-4.750 0.0080 0.01903 0.01111 -0.1352 0.8006 0.0214
-4.500 0.0361 0.01835 0.01040 -0.1358 0.7929 0.0226
-4.250 0.0672 0.01772 0.00970 -0.1368 0.7870 0.0246
-4.000 0.0997 0.01710 0.00899 -0.1380 0.7812 0.0275
-3.750 0.1358 0.01641 0.00827 -0.1399 0.7774 0.0356
-3.500 0.1715 0.01573 0.00763 -0.1418 0.7725 0.0568
-3.250 0.2089 0.01508 0.00707 -0.1441 0.7680 0.0910
-3.000 0.2500 0.01418 0.00654 -0.1475 0.7643 0.1843
-2.750 0.2924 0.01329 0.00607 -0.1513 0.7605 0.3146
-2.500 0.3332 0.01263 0.00574 -0.1545 0.7562 0.4330
-2.250 0.3722 0.01218 0.00554 -0.1570 0.7522 0.5332
-2.000 0.4088 0.01195 0.00549 -0.1586 0.7485 0.6135
-1.750 0.4417 0.01196 0.00547 -0.1594 0.7441 0.6570
-1.500 0.4758 0.01200 0.00543 -0.1606 0.7400 0.6841
-1.250 0.5122 0.01206 0.00536 -0.1624 0.7362 0.7048
-0.750 0.5782 0.01231 0.00543 -0.1645 0.7286 0.7356
-0.500 0.6075 0.01246 0.00553 -0.1648 0.7250 0.7464
-0.250 0.6407 0.01259 0.00556 -0.1661 0.7218 0.7562
0.000 0.6733 0.01273 0.00563 -0.1671 0.7190 0.7634
0.250 0.7091 0.01286 0.00565 -0.1690 0.7163 0.7715
0.500 0.7319 0.01301 0.00581 -0.1681 0.7127 0.7776
0.750 0.7596 0.01316 0.00593 -0.1683 0.7094 0.7848
1.000 0.7876 0.01329 0.00605 -0.1686 0.7065 0.7901
1.250 0.8176 0.01343 0.00616 -0.1692 0.7037 0.7951
1.500 0.8518 0.01359 0.00625 -0.1709 0.7011 0.8005
1.750 0.8798 0.01374 0.00640 -0.1712 0.6982 0.8050
2.000 0.9024 0.01389 0.00660 -0.1703 0.6948 0.8093
2.250 0.9284 0.01405 0.00677 -0.1702 0.6911 0.8142
2.500 0.9581 0.01422 0.00691 -0.1710 0.6874 0.8189
2.750 0.9898 0.01437 0.00704 -0.1720 0.6838 0.8223
3.000 1.0100 0.01453 0.00727 -0.1707 0.6794 0.8268
3.250 1.0332 0.01470 0.00748 -0.1700 0.6748 0.8318
3.500 1.0599 0.01485 0.00765 -0.1700 0.6706 0.8359
3.750 1.0908 0.01500 0.00779 -0.1709 0.6670 0.8397
4.000 1.1069 0.01517 0.00806 -0.1688 0.6620 0.8448
4.250 1.1296 0.01534 0.00828 -0.1681 0.6569 0.8496
4.500 1.1553 0.01545 0.00843 -0.1678 0.6524 0.8531
4.750 1.1747 0.01560 0.00866 -0.1664 0.6472 0.8576
5.000 1.1917 0.01575 0.00889 -0.1645 0.6415 0.8625
5.250 1.2161 0.01586 0.00905 -0.1640 0.6363 0.8663
5.500 1.2305 0.01600 0.00929 -0.1616 0.6304 0.8709
5.750 1.2462 0.01617 0.00954 -0.1594 0.6237 0.8763
6.000 1.2682 0.01629 0.00970 -0.1585 0.6173 0.8807
6.250 1.2777 0.01651 0.01005 -0.1551 0.6094 0.8863
6.500 1.2985 0.01662 0.01021 -0.1540 0.6023 0.8920
6.750 1.3077 0.01689 0.01061 -0.1507 0.5932 0.8988
7.000 1.3230 0.01708 0.01087 -0.1485 0.5843 0.9057
7.250 1.3351 0.01731 0.01120 -0.1458 0.5739 0.9138
7.500 1.3447 0.01761 0.01160 -0.1426 0.5620 0.9254
7.750 1.3542 0.01788 0.01196 -0.1395 0.5483 0.9456
8.000 1.3655 0.01819 0.01232 -0.1369 0.5312 1.0000
8.250 1.3785 0.01872 0.01283 -0.1348 0.5094 1.0000
8.500 1.3885 0.01940 0.01342 -0.1322 0.4818 1.0000
8.750 1.3957 0.02029 0.01417 -0.1293 0.4524 1.0000
9.000 1.3992 0.02144 0.01517 -0.1259 0.4214 1.0000
9.250 1.3996 0.02284 0.01639 -0.1222 0.3893 1.0000
9.500 1.3989 0.02440 0.01780 -0.1186 0.3576 1.0000
10.250 1.3935 0.02990 0.02287 -0.1086 0.2668 1.0000
10.500 1.3932 0.03186 0.02473 -0.1058 0.2405 1.0000
10.750 1.3938 0.03387 0.02664 -0.1034 0.2180 1.0000
11.000 1.3958 0.03588 0.02858 -0.1013 0.1952 1.0000
11.500 1.3986 0.04026 0.03281 -0.0974 0.1521 1.0000
11.750 1.3996 0.04264 0.03509 -0.0958 0.1315 1.0000
12.000 1.4021 0.04495 0.03733 -0.0943 0.1118 1.0000
12.250 1.4047 0.04733 0.03965 -0.0930 0.0948 1.0000
12.500 1.4079 0.04970 0.04198 -0.0919 0.0804 1.0000
12.750 1.4116 0.05209 0.04436 -0.0908 0.0669 1.0000
13.000 1.4143 0.05461 0.04686 -0.0898 0.0540 1.0000
13.250 1.4157 0.05732 0.04954 -0.0889 0.0422 1.0000
13.500 1.4171 0.06010 0.05231 -0.0880 0.0334 1.0000
14.000 1.4207 0.06574 0.05804 -0.0865 0.0226 1.0000
14.250 1.4230 0.06858 0.06095 -0.0860 0.0200 1.0000
14.500 1.4250 0.07149 0.06395 -0.0855 0.0182 1.0000
14.750 1.4263 0.07455 0.06712 -0.0852 0.0170 1.0000
15.000 1.4284 0.07758 0.07027 -0.0849 0.0162 1.0000
15.250 1.4295 0.08078 0.07360 -0.0848 0.0155 1.0000
15.500 1.4296 0.08418 0.07712 -0.0848 0.0149 1.0000
15.750 1.4283 0.08779 0.08085 -0.0849 0.0145 1.0000
16.250 1.4243 0.09547 0.08879 -0.0856 0.0138 1.0000
16.500 1.4227 0.09934 0.09281 -0.0862 0.0135 1.0000
16.750 1.4209 0.10329 0.09690 -0.0869 0.0132 1.0000
17.000 1.4190 0.10729 0.10106 -0.0878 0.0129 1.0000
17.250 1.4171 0.11133 0.10522 -0.0888 0.0126 1.0000
17.500 1.4151 0.11540 0.10942 -0.0899 0.0123 1.0000
17.750 1.4131 0.11952 0.11365 -0.0912 0.0120 1.0000
18.000 1.4112 0.12366 0.11790 -0.0926 0.0118 1.0000
18.250 1.4089 0.12787 0.12221 -0.0942 0.0115 1.0000
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Polar data table (+)
Polar graphs
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