EPPLER 479 AIRFOIL (e479-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 479 AIRFOIL (e479-il) Reynolds number: 500,000 Max Cl/Cd: 76.94 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e479-il-500000.txt Download as CSV file: xf-e479-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 479 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -1.1995 0.08625 0.08182 -0.0176 1.0000 0.0467
-18.000 -1.2100 0.08139 0.07692 -0.0198 1.0000 0.0482
-17.750 -1.2184 0.07692 0.07236 -0.0217 1.0000 0.0497
-17.500 -1.2229 0.07299 0.06833 -0.0233 1.0000 0.0514
-17.250 -1.2355 0.06817 0.06345 -0.0252 1.0000 0.0528
-17.000 -1.2476 0.06347 0.05870 -0.0271 1.0000 0.0542
-16.750 -1.2572 0.05920 0.05438 -0.0287 1.0000 0.0558
-16.500 -1.2638 0.05542 0.05051 -0.0300 1.0000 0.0576
-16.000 -1.2796 0.04784 0.04278 -0.0324 1.0000 0.0611
-15.750 -1.2878 0.04411 0.03898 -0.0335 1.0000 0.0628
-15.500 -1.2918 0.04091 0.03573 -0.0343 1.0000 0.0649
-15.250 -1.2909 0.03830 0.03302 -0.0348 1.0000 0.0669
-15.000 -1.2938 0.03538 0.03003 -0.0353 1.0000 0.0692
-14.750 -1.2969 0.03254 0.02715 -0.0356 1.0000 0.0716
-14.500 -1.2949 0.03033 0.02490 -0.0356 1.0000 0.0744
-14.250 -1.2882 0.02865 0.02312 -0.0354 1.0000 0.0769
-14.000 -1.2883 0.02655 0.02098 -0.0348 1.0000 0.0795
-13.750 -1.2857 0.02485 0.01925 -0.0339 1.0000 0.0827
-13.500 -1.2784 0.02361 0.01796 -0.0328 1.0000 0.0858
-13.250 -1.2714 0.02248 0.01677 -0.0314 1.0000 0.0890
-13.000 -1.2675 0.02131 0.01559 -0.0294 1.0000 0.0924
-12.750 -1.2584 0.02051 0.01476 -0.0275 1.0000 0.0963
-12.500 -1.2475 0.01986 0.01405 -0.0254 1.0000 0.0997
-12.250 -1.2421 0.01905 0.01325 -0.0226 1.0000 0.1039
-12.000 -1.2316 0.01850 0.01268 -0.0201 1.0000 0.1081
-11.750 -1.2181 0.01801 0.01214 -0.0180 1.0000 0.1124
-11.500 -1.2050 0.01738 0.01154 -0.0160 1.0000 0.1176
-11.250 -1.1865 0.01699 0.01111 -0.0146 1.0000 0.1229
-11.000 -1.1711 0.01641 0.01056 -0.0128 1.0000 0.1289
-10.750 -1.1522 0.01600 0.01014 -0.0114 1.0000 0.1350
-10.500 -1.1340 0.01554 0.00968 -0.0100 1.0000 0.1406
-10.250 -1.1152 0.01511 0.00926 -0.0085 1.0000 0.1468
-10.000 -1.0948 0.01477 0.00889 -0.0073 1.0000 0.1525
-9.750 -1.0762 0.01432 0.00848 -0.0058 1.0000 0.1592
-9.500 -1.0546 0.01406 0.00818 -0.0046 1.0000 0.1652
-9.250 -1.0360 0.01362 0.00779 -0.0031 1.0000 0.1721
-9.000 -1.0146 0.01334 0.00750 -0.0019 1.0000 0.1788
-8.750 -0.9949 0.01297 0.00717 -0.0005 1.0000 0.1859
-8.500 -0.9736 0.01270 0.00689 0.0008 1.0000 0.1930
-8.250 -0.9534 0.01239 0.00661 0.0022 1.0000 0.2002
-8.000 -0.9324 0.01214 0.00637 0.0035 1.0000 0.2077
-7.750 -0.9122 0.01187 0.00613 0.0049 1.0000 0.2150
-7.500 -0.8919 0.01165 0.00593 0.0063 1.0000 0.2228
-7.250 -0.8566 0.01138 0.00569 0.0046 0.9964 0.2319
-6.750 -0.7744 0.01090 0.00526 -0.0008 0.9815 0.2512
-6.500 -0.7357 0.01068 0.00504 -0.0030 0.9686 0.2601
-6.250 -0.6954 0.01045 0.00484 -0.0054 0.9510 0.2695
-6.000 -0.6535 0.01023 0.00461 -0.0082 0.9262 0.2781
-5.750 -0.6185 0.01011 0.00441 -0.0093 0.8918 0.2864
-5.500 -0.5920 0.01004 0.00424 -0.0087 0.8564 0.2934
-5.250 -0.5667 0.01000 0.00410 -0.0079 0.8255 0.3003
-5.000 -0.5408 0.01000 0.00396 -0.0072 0.7979 0.3070
-4.750 -0.5155 0.00991 0.00382 -0.0065 0.7721 0.3139
-4.500 -0.4891 0.00991 0.00370 -0.0060 0.7477 0.3206
-4.000 -0.4365 0.00980 0.00346 -0.0049 0.7047 0.3340
-3.750 -0.4094 0.00979 0.00335 -0.0045 0.6839 0.3404
-3.500 -0.3831 0.00971 0.00325 -0.0041 0.6640 0.3472
-3.250 -0.3558 0.00970 0.00316 -0.0037 0.6455 0.3540
-3.000 -0.3289 0.00964 0.00306 -0.0034 0.6277 0.3607
-2.750 -0.3018 0.00961 0.00298 -0.0030 0.6101 0.3677
-2.500 -0.2743 0.00961 0.00290 -0.0027 0.5931 0.3745
-2.250 -0.2474 0.00955 0.00283 -0.0024 0.5774 0.3817
-2.000 -0.2198 0.00955 0.00277 -0.0021 0.5621 0.3890
-1.750 -0.1927 0.00952 0.00271 -0.0018 0.5470 0.3964
-1.500 -0.1651 0.00950 0.00266 -0.0015 0.5323 0.4045
-1.250 -0.1376 0.00947 0.00262 -0.0013 0.5188 0.4122
-1.000 -0.1101 0.00947 0.00259 -0.0010 0.5058 0.4210
-0.750 -0.0827 0.00947 0.00256 -0.0007 0.4933 0.4295
-0.500 -0.0551 0.00946 0.00254 -0.0005 0.4811 0.4390
-0.250 -0.0275 0.00944 0.00253 -0.0003 0.4699 0.4486
0.000 0.0000 0.00948 0.00252 0.0000 0.4591 0.4590
0.250 0.0275 0.00944 0.00253 0.0003 0.4486 0.4699
0.500 0.0551 0.00946 0.00254 0.0005 0.4390 0.4811
0.750 0.0827 0.00947 0.00256 0.0007 0.4295 0.4932
1.000 0.1101 0.00947 0.00259 0.0010 0.4210 0.5058
1.250 0.1376 0.00947 0.00262 0.0013 0.4122 0.5188
1.500 0.1651 0.00950 0.00266 0.0015 0.4045 0.5323
1.750 0.1927 0.00952 0.00271 0.0018 0.3964 0.5470
2.000 0.2198 0.00955 0.00277 0.0021 0.3890 0.5622
2.250 0.2474 0.00955 0.00283 0.0024 0.3817 0.5774
2.500 0.2743 0.00961 0.00290 0.0027 0.3744 0.5932
2.750 0.3018 0.00961 0.00298 0.0030 0.3676 0.6102
3.000 0.3289 0.00964 0.00306 0.0034 0.3607 0.6277
3.250 0.3558 0.00970 0.00316 0.0037 0.3540 0.6456
3.500 0.3831 0.00971 0.00325 0.0041 0.3472 0.6640
3.750 0.4094 0.00979 0.00335 0.0045 0.3404 0.6838
4.000 0.4366 0.00980 0.00346 0.0049 0.3340 0.7046
4.500 0.4891 0.00991 0.00370 0.0060 0.3207 0.7476
4.750 0.5155 0.00991 0.00382 0.0065 0.3139 0.7720
5.000 0.5408 0.01000 0.00396 0.0072 0.3070 0.7980
5.250 0.5667 0.01000 0.00410 0.0079 0.3003 0.8256
5.500 0.5920 0.01004 0.00423 0.0087 0.2933 0.8563
5.750 0.6186 0.01011 0.00441 0.0093 0.2865 0.8918
6.000 0.6535 0.01023 0.00461 0.0082 0.2781 0.9262
6.250 0.6954 0.01045 0.00484 0.0054 0.2695 0.9511
6.500 0.7357 0.01068 0.00504 0.0030 0.2600 0.9687
6.750 0.7744 0.01089 0.00526 0.0008 0.2513 0.9816
7.000 0.8149 0.01119 0.00549 -0.0018 0.2412 0.9899
7.250 0.8567 0.01138 0.00569 -0.0047 0.2319 0.9965
7.500 0.8918 0.01165 0.00593 -0.0063 0.2228 1.0000
7.750 0.9121 0.01187 0.00613 -0.0049 0.2151 1.0000
8.000 0.9323 0.01214 0.00637 -0.0034 0.2076 1.0000
8.250 0.9533 0.01239 0.00661 -0.0021 0.2000 1.0000
8.500 0.9736 0.01270 0.00689 -0.0008 0.1930 1.0000
8.750 0.9949 0.01297 0.00716 0.0005 0.1859 1.0000
9.000 1.0146 0.01334 0.00749 0.0019 0.1788 1.0000
9.250 1.0360 0.01362 0.00779 0.0031 0.1722 1.0000
9.500 1.0546 0.01406 0.00818 0.0046 0.1652 1.0000
9.750 1.0763 0.01432 0.00848 0.0058 0.1592 1.0000
10.000 1.0949 0.01476 0.00889 0.0073 0.1525 1.0000
10.250 1.1153 0.01511 0.00926 0.0085 0.1469 1.0000
10.500 1.1342 0.01554 0.00968 0.0099 0.1407 1.0000
10.750 1.1524 0.01600 0.01014 0.0114 0.1350 1.0000
11.000 1.1713 0.01641 0.01056 0.0128 0.1289 1.0000
11.250 1.1867 0.01698 0.01110 0.0146 0.1229 1.0000
11.500 1.2052 0.01738 0.01154 0.0159 0.1175 1.0000
11.750 1.2181 0.01802 0.01215 0.0180 0.1122 1.0000
12.000 1.2321 0.01850 0.01267 0.0200 0.1080 1.0000
12.250 1.2426 0.01905 0.01325 0.0225 0.1038 1.0000
12.500 1.2482 0.01985 0.01404 0.0253 0.0998 1.0000
12.750 1.2591 0.02051 0.01475 0.0273 0.0962 1.0000
13.000 1.2682 0.02131 0.01559 0.0293 0.0924 1.0000
13.250 1.2718 0.02249 0.01678 0.0313 0.0889 1.0000
13.500 1.2792 0.02360 0.01795 0.0327 0.0858 1.0000
13.750 1.2865 0.02483 0.01924 0.0338 0.0826 1.0000
14.000 1.2893 0.02652 0.02095 0.0347 0.0796 1.0000
14.250 1.2892 0.02862 0.02309 0.0353 0.0768 1.0000
14.500 1.2962 0.03029 0.02485 0.0355 0.0742 1.0000
14.750 1.2983 0.03250 0.02710 0.0355 0.0714 1.0000
15.000 1.2948 0.03538 0.03003 0.0351 0.0691 1.0000
15.250 1.2922 0.03828 0.03300 0.0346 0.0670 1.0000
15.500 1.2932 0.04089 0.03570 0.0341 0.0649 1.0000
15.750 1.2894 0.04408 0.03895 0.0333 0.0627 1.0000
16.000 1.2808 0.04787 0.04280 0.0321 0.0609 1.0000
16.250 1.2680 0.05218 0.04716 0.0308 0.0592 1.0000
16.500 1.2660 0.05534 0.05043 0.0298 0.0575 1.0000
16.750 1.2592 0.05916 0.05433 0.0285 0.0558 1.0000
17.000 1.2499 0.06340 0.05863 0.0269 0.0542 1.0000
17.250 1.2374 0.06814 0.06342 0.0250 0.0528 1.0000
17.500 1.2261 0.07281 0.06815 0.0231 0.0513 1.0000
17.750 1.2203 0.07689 0.07234 0.0214 0.0498 1.0000
18.000 1.2125 0.08132 0.07683 0.0195 0.0481 1.0000
18.250 1.2018 0.08621 0.08177 0.0174 0.0467 1.0000
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