EPPLER 678 AIRFOIL (e678-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: EPPLER 678 AIRFOIL (e678-il) Reynolds number: 500,000 Max Cl/Cd: 109.59 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e678-il-500000-n5.txt Download as CSV file: xf-e678-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0048 0.08318 0.08026 -0.1614 0.9314 0.0082
-11.500 -0.1397 0.04598 0.04272 -0.1849 0.9236 0.0080
-11.250 -0.1617 0.03898 0.03548 -0.1911 0.9176 0.0080
-11.000 -0.1772 0.03451 0.03077 -0.1940 0.9120 0.0080
-10.750 -0.1865 0.03107 0.02706 -0.1956 0.9076 0.0080
-10.500 -0.1995 0.02919 0.02506 -0.1930 0.9027 0.0079
-10.250 -0.2104 0.02743 0.02310 -0.1902 0.8977 0.0080
-10.000 -0.2094 0.02571 0.02113 -0.1890 0.8943 0.0080
-9.750 -0.2045 0.02428 0.01947 -0.1874 0.8913 0.0081
-9.500 -0.1996 0.02306 0.01808 -0.1850 0.8878 0.0081
-9.250 -0.1895 0.02179 0.01661 -0.1834 0.8845 0.0082
-9.000 -0.1752 0.02032 0.01495 -0.1826 0.8815 0.0083
-8.750 -0.1535 0.01925 0.01373 -0.1828 0.8790 0.0085
-8.500 -0.1353 0.01848 0.01286 -0.1819 0.8758 0.0087
-8.250 -0.1192 0.01793 0.01225 -0.1804 0.8722 0.0089
-8.000 -0.0993 0.01733 0.01156 -0.1796 0.8688 0.0093
-7.750 -0.0759 0.01659 0.01071 -0.1795 0.8658 0.0095
-7.500 -0.0491 0.01583 0.00980 -0.1800 0.8632 0.0099
-7.250 -0.0316 0.01526 0.00917 -0.1784 0.8592 0.0100
-7.000 -0.0133 0.01470 0.00854 -0.1770 0.8543 0.0102
-6.750 0.0116 0.01411 0.00786 -0.1770 0.8499 0.0105
-6.500 0.0334 0.01363 0.00730 -0.1762 0.8443 0.0107
-6.250 0.0518 0.01313 0.00675 -0.1747 0.8366 0.0110
-6.000 0.0727 0.01262 0.00620 -0.1738 0.8284 0.0113
-5.750 0.0920 0.01223 0.00576 -0.1723 0.8153 0.0118
-5.500 0.1168 0.01182 0.00522 -0.1720 0.7828 0.0122
-5.250 0.1398 0.01160 0.00469 -0.1711 0.7452 0.0128
-5.000 0.1595 0.01149 0.00440 -0.1697 0.7306 0.0136
-4.750 0.1828 0.01130 0.00412 -0.1691 0.7221 0.0147
-4.500 0.2078 0.01116 0.00388 -0.1689 0.7158 0.0162
-4.250 0.2341 0.01099 0.00366 -0.1688 0.7108 0.0182
-4.000 0.2608 0.01082 0.00346 -0.1689 0.7061 0.0229
-3.750 0.2886 0.01065 0.00330 -0.1693 0.7018 0.0386
-3.500 0.3167 0.01048 0.00317 -0.1698 0.6984 0.0570
-3.250 0.3447 0.01027 0.00305 -0.1703 0.6954 0.0855
-3.000 0.3734 0.01003 0.00296 -0.1710 0.6924 0.1310
-2.750 0.4030 0.00978 0.00288 -0.1719 0.6896 0.1896
-2.500 0.4341 0.00946 0.00281 -0.1733 0.6870 0.2794
-2.250 0.4660 0.00920 0.00278 -0.1748 0.6846 0.3679
-2.000 0.4970 0.00903 0.00277 -0.1760 0.6824 0.4353
-1.750 0.5269 0.00882 0.00279 -0.1769 0.6800 0.5167
-1.500 0.5559 0.00870 0.00284 -0.1774 0.6775 0.5768
-1.250 0.5841 0.00870 0.00292 -0.1777 0.6751 0.6157
-1.000 0.6122 0.00874 0.00301 -0.1780 0.6729 0.6467
-0.750 0.6405 0.00882 0.00309 -0.1782 0.6709 0.6683
-0.500 0.6694 0.00892 0.00316 -0.1786 0.6689 0.6844
0.000 0.7253 0.00911 0.00333 -0.1790 0.6649 0.7093
0.250 0.7519 0.00918 0.00340 -0.1789 0.6627 0.7181
0.500 0.7788 0.00925 0.00348 -0.1789 0.6607 0.7246
0.750 0.8057 0.00933 0.00356 -0.1788 0.6586 0.7308
1.000 0.8333 0.00942 0.00363 -0.1790 0.6564 0.7372
1.250 0.8605 0.00952 0.00373 -0.1790 0.6542 0.7422
1.500 0.8887 0.00963 0.00383 -0.1793 0.6517 0.7474
1.750 0.9134 0.00972 0.00391 -0.1789 0.6484 0.7524
2.000 0.9356 0.00977 0.00400 -0.1779 0.6442 0.7562
2.250 0.9592 0.00986 0.00410 -0.1772 0.6403 0.7598
2.500 0.9846 0.00996 0.00420 -0.1769 0.6370 0.7635
2.750 1.0106 0.01008 0.00430 -0.1767 0.6338 0.7673
3.000 1.0339 0.01016 0.00443 -0.1760 0.6300 0.7709
3.250 1.0566 0.01025 0.00456 -0.1752 0.6259 0.7738
3.500 1.0800 0.01036 0.00469 -0.1745 0.6218 0.7770
3.750 1.1044 0.01049 0.00481 -0.1740 0.6180 0.7805
4.000 1.1272 0.01059 0.00497 -0.1732 0.6135 0.7842
4.250 1.1496 0.01071 0.00512 -0.1724 0.6086 0.7878
4.500 1.1714 0.01085 0.00527 -0.1714 0.6038 0.7912
4.750 1.1930 0.01097 0.00546 -0.1703 0.5980 0.7950
5.000 1.2138 0.01112 0.00564 -0.1692 0.5913 0.7987
5.250 1.2348 0.01129 0.00583 -0.1681 0.5847 0.8021
5.500 1.2548 0.01145 0.00604 -0.1668 0.5769 0.8047
5.750 1.2742 0.01165 0.00627 -0.1654 0.5686 0.8076
6.000 1.2923 0.01187 0.00652 -0.1637 0.5578 0.8109
6.250 1.3103 0.01213 0.00680 -0.1621 0.5451 0.8142
6.500 1.3249 0.01250 0.00713 -0.1599 0.5275 0.8175
6.750 1.3369 0.01296 0.00754 -0.1572 0.5040 0.8206
7.000 1.3400 0.01377 0.00820 -0.1529 0.4671 0.8244
7.250 1.3438 0.01472 0.00897 -0.1490 0.4319 0.8285
7.500 1.3469 0.01580 0.00986 -0.1451 0.3937 0.8324
7.750 1.3538 0.01676 0.01070 -0.1420 0.3638 0.8359
8.000 1.3579 0.01788 0.01168 -0.1385 0.3300 0.8398
8.250 1.3604 0.01916 0.01279 -0.1349 0.2940 0.8443
8.500 1.3642 0.02044 0.01391 -0.1317 0.2604 0.8491
8.750 1.3684 0.02170 0.01504 -0.1286 0.2310 0.8538
9.000 1.3748 0.02291 0.01616 -0.1259 0.2059 0.8590
9.250 1.3814 0.02415 0.01732 -0.1233 0.1832 0.8644
9.500 1.3883 0.02537 0.01848 -0.1209 0.1633 0.8702
9.750 1.3944 0.02671 0.01977 -0.1184 0.1443 0.8771
10.000 1.4012 0.02801 0.02103 -0.1161 0.1266 0.8849
10.500 1.4114 0.03089 0.02384 -0.1113 0.0933 0.9109
10.750 1.4130 0.03228 0.02524 -0.1084 0.0786 1.0000
11.000 1.4181 0.03410 0.02699 -0.1065 0.0621 1.0000
11.250 1.4230 0.03598 0.02880 -0.1047 0.0486 1.0000
11.500 1.4280 0.03791 0.03069 -0.1031 0.0362 1.0000
11.750 1.4331 0.03992 0.03266 -0.1016 0.0265 1.0000
12.000 1.4383 0.04197 0.03469 -0.1002 0.0179 1.0000
12.250 1.4446 0.04398 0.03670 -0.0990 0.0137 1.0000
12.500 1.4524 0.04588 0.03865 -0.0980 0.0119 1.0000
12.750 1.4604 0.04779 0.04062 -0.0971 0.0109 1.0000
13.000 1.4691 0.04965 0.04256 -0.0963 0.0103 1.0000
13.250 1.4769 0.05165 0.04463 -0.0955 0.0098 1.0000
13.500 1.4842 0.05371 0.04676 -0.0947 0.0094 1.0000
13.750 1.4904 0.05592 0.04904 -0.0939 0.0090 1.0000
14.000 1.4952 0.05831 0.05152 -0.0932 0.0086 1.0000
14.250 1.5020 0.06052 0.05381 -0.0926 0.0084 1.0000
14.500 1.5077 0.06288 0.05627 -0.0920 0.0082 1.0000
14.750 1.5129 0.06533 0.05881 -0.0915 0.0079 1.0000
15.000 1.5173 0.06793 0.06150 -0.0911 0.0077 1.0000
15.250 1.5207 0.07067 0.06433 -0.0907 0.0075 1.0000
15.500 1.5236 0.07352 0.06727 -0.0904 0.0074 1.0000
15.750 1.5255 0.07655 0.07042 -0.0902 0.0072 1.0000
16.000 1.5266 0.07974 0.07370 -0.0901 0.0071 1.0000
16.250 1.5266 0.08314 0.07720 -0.0901 0.0069 1.0000
16.500 1.5253 0.08679 0.08095 -0.0902 0.0068 1.0000
16.750 1.5227 0.09068 0.08494 -0.0905 0.0067 1.0000
17.000 1.5187 0.09484 0.08921 -0.0909 0.0066 1.0000
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