EPPLER 682 AIRFOIL (e682-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 682 AIRFOIL (e682-il) Reynolds number: 500,000 Max Cl/Cd: 87.7 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e682-il-500000-n5.txt Download as CSV file: xf-e682-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 682 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2945 0.08766 0.08425 -0.0917 0.7875 0.0090
-11.750 -0.3174 0.07850 0.07514 -0.0960 0.7861 0.0090
-11.500 -0.3998 0.05447 0.05096 -0.1108 0.7843 0.0086
-11.250 -0.4212 0.04990 0.04626 -0.1120 0.7825 0.0084
-11.000 -0.4658 0.04349 0.03955 -0.1102 0.7805 0.0085
-10.750 -0.4939 0.03937 0.03514 -0.1068 0.7786 0.0086
-10.500 -0.5079 0.03670 0.03224 -0.1034 0.7770 0.0085
-10.250 -0.5227 0.03389 0.02913 -0.0991 0.7754 0.0087
-10.000 -0.5312 0.03173 0.02669 -0.0949 0.7739 0.0087
-9.750 -0.5325 0.02977 0.02448 -0.0914 0.7726 0.0087
-9.500 -0.5276 0.02782 0.02226 -0.0887 0.7714 0.0088
-9.250 -0.5172 0.02625 0.02044 -0.0867 0.7701 0.0090
-9.000 -0.5037 0.02486 0.01880 -0.0850 0.7687 0.0091
-8.750 -0.4875 0.02365 0.01738 -0.0836 0.7673 0.0091
-8.500 -0.4692 0.02276 0.01628 -0.0824 0.7661 0.0093
-8.250 -0.4495 0.02173 0.01507 -0.0815 0.7650 0.0093
-8.000 -0.4289 0.02042 0.01360 -0.0807 0.7640 0.0095
-7.750 -0.4072 0.01925 0.01231 -0.0802 0.7630 0.0097
-7.500 -0.3850 0.01851 0.01152 -0.0797 0.7621 0.0100
-7.250 -0.3620 0.01794 0.01089 -0.0792 0.7611 0.0103
-7.000 -0.3386 0.01732 0.01019 -0.0788 0.7602 0.0106
-6.750 -0.3151 0.01670 0.00950 -0.0783 0.7593 0.0108
-6.500 -0.2918 0.01611 0.00883 -0.0778 0.7583 0.0110
-6.250 -0.2688 0.01555 0.00823 -0.0772 0.7572 0.0112
-6.000 -0.2457 0.01504 0.00769 -0.0766 0.7562 0.0115
-5.750 -0.2227 0.01459 0.00720 -0.0760 0.7552 0.0118
-5.500 -0.1995 0.01418 0.00675 -0.0754 0.7541 0.0121
-5.250 -0.1759 0.01382 0.00636 -0.0749 0.7530 0.0124
-5.000 -0.1520 0.01350 0.00600 -0.0744 0.7517 0.0126
-4.750 -0.1292 0.01306 0.00554 -0.0738 0.7504 0.0131
-4.500 -0.1052 0.01274 0.00519 -0.0733 0.7493 0.0137
-4.250 -0.0804 0.01249 0.00492 -0.0730 0.7480 0.0145
-4.000 -0.0553 0.01227 0.00467 -0.0727 0.7468 0.0155
-3.750 -0.0298 0.01208 0.00444 -0.0725 0.7456 0.0165
-3.500 -0.0045 0.01187 0.00419 -0.0722 0.7444 0.0180
-3.250 0.0210 0.01169 0.00401 -0.0720 0.7431 0.0210
-3.000 0.0446 0.01138 0.00384 -0.0714 0.7415 0.0459
-2.750 0.0674 0.01101 0.00369 -0.0709 0.7398 0.0956
-2.500 0.0894 0.01059 0.00355 -0.0702 0.7380 0.1691
-2.250 0.1091 0.01000 0.00340 -0.0692 0.7362 0.2860
-2.000 0.1292 0.00945 0.00324 -0.0683 0.7343 0.3984
-1.750 0.1464 0.00866 0.00302 -0.0669 0.7325 0.5547
-1.500 0.1606 0.00831 0.00356 -0.0636 0.7308 0.7766
-1.250 0.1888 0.00853 0.00372 -0.0636 0.7292 0.8054
-1.000 0.2164 0.00878 0.00392 -0.0635 0.7274 0.8193
-0.750 0.2429 0.00903 0.00418 -0.0630 0.7252 0.8295
-0.500 0.2692 0.00924 0.00440 -0.0625 0.7229 0.8357
-0.250 0.2958 0.00942 0.00458 -0.0621 0.7205 0.8412
0.000 0.3239 0.00948 0.00458 -0.0624 0.7182 0.8472
0.250 0.3507 0.00956 0.00466 -0.0620 0.7160 0.8496
0.500 0.3784 0.00961 0.00467 -0.0620 0.7140 0.8515
0.750 0.4062 0.00962 0.00467 -0.0622 0.7117 0.8531
1.000 0.4331 0.00961 0.00468 -0.0622 0.7086 0.8545
1.250 0.4607 0.00958 0.00464 -0.0624 0.7052 0.8558
1.500 0.4889 0.00953 0.00457 -0.0628 0.7019 0.8570
1.750 0.5177 0.00947 0.00448 -0.0632 0.6988 0.8581
2.000 0.5452 0.00943 0.00446 -0.0635 0.6946 0.8590
2.250 0.5728 0.00939 0.00443 -0.0637 0.6898 0.8601
2.500 0.6011 0.00933 0.00436 -0.0641 0.6854 0.8610
2.750 0.6290 0.00929 0.00433 -0.0645 0.6801 0.8617
3.000 0.6564 0.00925 0.00430 -0.0647 0.6735 0.8623
3.250 0.6831 0.00920 0.00427 -0.0647 0.6670 0.8629
3.500 0.7092 0.00918 0.00427 -0.0646 0.6582 0.8635
3.750 0.7354 0.00916 0.00426 -0.0645 0.6483 0.8640
4.000 0.7609 0.00915 0.00423 -0.0643 0.6360 0.8645
4.250 0.7852 0.00918 0.00422 -0.0638 0.6195 0.8650
4.500 0.8075 0.00927 0.00424 -0.0629 0.6000 0.8656
4.750 0.8279 0.00944 0.00432 -0.0617 0.5782 0.8663
5.000 0.8469 0.00967 0.00446 -0.0603 0.5559 0.8670
5.250 0.8648 0.00992 0.00464 -0.0587 0.5345 0.8679
5.500 0.8819 0.01019 0.00483 -0.0569 0.5136 0.8690
5.750 0.8973 0.01048 0.00505 -0.0549 0.4936 0.8698
6.000 0.9093 0.01076 0.00527 -0.0522 0.4731 0.8708
6.250 0.9207 0.01107 0.00554 -0.0495 0.4540 0.8718
6.500 0.9308 0.01151 0.00590 -0.0466 0.4328 0.8729
6.750 0.9408 0.01201 0.00633 -0.0439 0.4098 0.8740
7.000 0.9481 0.01264 0.00685 -0.0409 0.3838 0.8750
7.250 0.9553 0.01335 0.00745 -0.0380 0.3566 0.8760
7.500 0.9619 0.01416 0.00812 -0.0352 0.3275 0.8770
7.750 0.9655 0.01510 0.00891 -0.0320 0.2950 0.8782
8.250 0.9774 0.01703 0.01055 -0.0269 0.2306 0.8801
8.500 0.9862 0.01795 0.01134 -0.0248 0.2047 0.8810
8.750 0.9951 0.01890 0.01217 -0.0229 0.1784 0.8818
9.000 1.0066 0.01974 0.01294 -0.0213 0.1585 0.8826
9.250 1.0183 0.02060 0.01373 -0.0198 0.1405 0.8835
9.500 1.0282 0.02157 0.01460 -0.0182 0.1200 0.8843
9.750 1.0376 0.02261 0.01554 -0.0166 0.0986 0.8852
10.000 1.0473 0.02365 0.01650 -0.0150 0.0802 0.8860
10.250 1.0555 0.02482 0.01756 -0.0134 0.0610 0.8869
10.500 1.0641 0.02600 0.01865 -0.0119 0.0444 0.8877
10.750 1.0719 0.02726 0.01984 -0.0104 0.0302 0.8885
11.000 1.0806 0.02850 0.02103 -0.0090 0.0190 0.8893
11.250 1.0905 0.02969 0.02221 -0.0078 0.0134 0.8901
11.500 1.1012 0.03086 0.02341 -0.0068 0.0109 0.8908
12.000 1.1234 0.03317 0.02583 -0.0048 0.0091 0.8925
12.250 1.1346 0.03434 0.02707 -0.0039 0.0086 0.8935
12.500 1.1448 0.03561 0.02842 -0.0030 0.0083 0.8944
12.750 1.1550 0.03691 0.02980 -0.0021 0.0080 0.8953
13.000 1.1630 0.03844 0.03140 -0.0012 0.0075 0.8961
13.250 1.1712 0.04000 0.03305 -0.0004 0.0073 0.8971
13.500 1.1770 0.04182 0.03496 0.0004 0.0070 0.8980
13.750 1.1864 0.04336 0.03658 0.0010 0.0068 0.8989
14.000 1.1925 0.04524 0.03856 0.0016 0.0067 0.8999
14.250 1.1985 0.04720 0.04061 0.0022 0.0065 0.9009
14.500 1.2046 0.04921 0.04272 0.0026 0.0064 0.9019
14.750 1.2092 0.05144 0.04505 0.0029 0.0063 0.9029
15.000 1.2126 0.05385 0.04756 0.0031 0.0061 0.9039
15.250 1.2170 0.05622 0.05003 0.0032 0.0060 0.9049
15.500 1.2184 0.05903 0.05294 0.0032 0.0060 0.9059
15.750 1.2209 0.06173 0.05574 0.0031 0.0058 0.9069
16.000 1.2217 0.06470 0.05881 0.0029 0.0058 0.9080
16.250 1.2216 0.06786 0.06209 0.0026 0.0057 0.9091
16.500 1.2211 0.07115 0.06549 0.0021 0.0056 0.9103
16.750 1.2196 0.07469 0.06914 0.0014 0.0056 0.9115
17.000 1.2172 0.07844 0.07300 0.0005 0.0055 0.9128
17.250 1.2148 0.08228 0.07696 -0.0005 0.0055 0.9140
17.500 1.2118 0.08630 0.08110 -0.0017 0.0054 0.9153
17.750 1.2067 0.09072 0.08562 -0.0032 0.0052 0.9165
18.000 1.2021 0.09517 0.09019 -0.0048 0.0052 0.9177
18.250 1.1985 0.09955 0.09468 -0.0065 0.0052 0.9190
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