EPPLER 585 AIRFOIL (e585-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 585 AIRFOIL (e585-il) Reynolds number: 100,000 Max Cl/Cd: 47.75 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e585-il-100000-n5.txt Download as CSV file: xf-e585-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 585 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1671 0.08134 0.07648 -0.1020 0.9321 0.0232
-9.000 -0.1588 0.07722 0.07236 -0.1056 0.9250 0.0227
-8.750 -0.1524 0.07177 0.06689 -0.1113 0.9180 0.0222
-8.500 -0.1545 0.06582 0.06089 -0.1174 0.9085 0.0217
-8.250 -0.1592 0.06031 0.05524 -0.1224 0.9001 0.0211
-8.000 -0.1717 0.05647 0.05126 -0.1229 0.8886 0.0207
-7.750 -0.1786 0.05240 0.04696 -0.1232 0.8798 0.0203
-7.500 -0.1840 0.04771 0.04189 -0.1230 0.8720 0.0196
-7.000 -0.1827 0.03978 0.03286 -0.1199 0.8575 0.0186
-6.750 -0.1680 0.03702 0.02969 -0.1194 0.8530 0.0186
-6.500 -0.1577 0.03490 0.02720 -0.1174 0.8460 0.0186
-6.250 -0.1375 0.03254 0.02448 -0.1171 0.8418 0.0188
-6.000 -0.1124 0.03050 0.02209 -0.1174 0.8388 0.0192
-5.750 -0.0985 0.02929 0.02066 -0.1153 0.8321 0.0195
-5.500 -0.0744 0.02801 0.01918 -0.1150 0.8280 0.0208
-5.250 -0.0459 0.02664 0.01744 -0.1152 0.8250 0.0232
-5.000 -0.0256 0.02563 0.01635 -0.1141 0.8202 0.0248
-4.750 -0.0049 0.02475 0.01538 -0.1130 0.8152 0.0264
-4.500 0.0210 0.02372 0.01420 -0.1126 0.8117 0.0285
-4.250 0.0487 0.02280 0.01324 -0.1128 0.8090 0.0327
-4.000 0.0645 0.02235 0.01274 -0.1108 0.8031 0.0380
-3.750 0.0864 0.02173 0.01207 -0.1099 0.7987 0.0469
-3.500 0.1126 0.02097 0.01136 -0.1098 0.7955 0.0696
-3.250 0.1399 0.02003 0.01076 -0.1101 0.7930 0.1320
-3.000 0.1501 0.01948 0.01078 -0.1078 0.7863 0.2472
-2.750 0.1630 0.01822 0.01087 -0.1054 0.7822 0.5422
-2.500 0.1808 0.01857 0.01151 -0.1016 0.7792 0.7040
-2.250 0.1979 0.01904 0.01187 -0.0989 0.7745 0.7480
-2.000 0.2124 0.01950 0.01222 -0.0957 0.7691 0.7755
-1.750 0.2340 0.01974 0.01231 -0.0937 0.7657 0.7996
-1.500 0.2546 0.01993 0.01239 -0.0908 0.7631 0.8216
-1.250 0.2575 0.02041 0.01285 -0.0855 0.7562 0.8447
-1.000 0.2691 0.02057 0.01295 -0.0811 0.7519 0.8655
-0.750 0.2941 0.02051 0.01275 -0.0800 0.7490 0.8785
-0.500 0.3167 0.02054 0.01266 -0.0792 0.7449 0.8850
-0.250 0.3304 0.02073 0.01278 -0.0771 0.7385 0.8914
0.000 0.3595 0.02065 0.01257 -0.0774 0.7352 0.8955
0.250 0.3929 0.02050 0.01228 -0.0786 0.7327 0.8992
0.500 0.4027 0.02083 0.01259 -0.0760 0.7254 0.9052
0.750 0.4290 0.02083 0.01250 -0.0759 0.7213 0.9089
1.000 0.4617 0.02071 0.01228 -0.0770 0.7185 0.9123
1.500 0.5003 0.02107 0.01258 -0.0749 0.7072 0.9219
1.750 0.5323 0.02098 0.01243 -0.0759 0.7041 0.9254
2.000 0.5687 0.02081 0.01220 -0.0776 0.7017 0.9282
2.250 0.5745 0.02134 0.01277 -0.0745 0.6929 0.9352
2.500 0.6072 0.02125 0.01265 -0.0756 0.6893 0.9390
2.750 0.6451 0.02103 0.01239 -0.0775 0.6868 0.9422
3.000 0.6544 0.02157 0.01299 -0.0751 0.6778 0.9497
3.250 0.6895 0.02144 0.01286 -0.0766 0.6740 0.9535
3.500 0.7299 0.02117 0.01257 -0.0789 0.6713 0.9569
3.750 0.7434 0.02175 0.01324 -0.0775 0.6619 0.9666
4.000 0.7822 0.02155 0.01306 -0.0796 0.6582 0.9712
4.250 0.8068 0.02186 0.01344 -0.0799 0.6507 0.9823
4.500 0.8372 0.02182 0.01344 -0.0809 0.6449 1.0000
4.750 0.8770 0.02147 0.01311 -0.0830 0.6413 1.0000
5.000 0.8812 0.02210 0.01381 -0.0799 0.6311 1.0000
5.250 0.9217 0.02174 0.01347 -0.0821 0.6268 1.0000
5.500 0.9291 0.02234 0.01414 -0.0795 0.6167 1.0000
5.750 0.9701 0.02193 0.01378 -0.0817 0.6118 1.0000
6.000 0.9784 0.02254 0.01447 -0.0792 0.6011 1.0000
6.250 1.0071 0.02250 0.01450 -0.0796 0.5937 1.0000
6.500 1.0293 0.02267 0.01475 -0.0790 0.5844 1.0000
6.750 1.0464 0.02305 0.01521 -0.0778 0.5741 1.0000
7.000 1.0785 0.02286 0.01506 -0.0786 0.5657 1.0000
7.250 1.0962 0.02320 0.01549 -0.0774 0.5541 1.0000
7.500 1.1125 0.02362 0.01600 -0.0761 0.5419 1.0000
7.750 1.1320 0.02392 0.01637 -0.0752 0.5294 1.0000
8.000 1.1523 0.02420 0.01670 -0.0743 0.5162 1.0000
8.250 1.1713 0.02453 0.01710 -0.0733 0.5019 1.0000
8.500 1.1888 0.02495 0.01756 -0.0721 0.4867 1.0000
8.750 1.2052 0.02544 0.01810 -0.0709 0.4706 1.0000
9.000 1.2209 0.02600 0.01868 -0.0695 0.4536 1.0000
9.250 1.2361 0.02660 0.01930 -0.0682 0.4360 1.0000
9.500 1.2506 0.02727 0.01996 -0.0668 0.4177 1.0000
9.750 1.2600 0.02827 0.02098 -0.0650 0.3985 1.0000
10.000 1.2692 0.02933 0.02203 -0.0632 0.3791 1.0000
10.250 1.2778 0.03045 0.02313 -0.0615 0.3596 1.0000
10.500 1.2851 0.03172 0.02440 -0.0597 0.3406 1.0000
10.750 1.2908 0.03314 0.02583 -0.0580 0.3214 1.0000
11.000 1.2958 0.03467 0.02734 -0.0563 0.3027 1.0000
11.250 1.3000 0.03630 0.02895 -0.0547 0.2845 1.0000
11.500 1.3034 0.03806 0.03071 -0.0531 0.2666 1.0000
11.750 1.3063 0.03993 0.03260 -0.0517 0.2491 1.0000
12.000 1.3085 0.04194 0.03461 -0.0503 0.2319 1.0000
12.250 1.3100 0.04406 0.03675 -0.0490 0.2154 1.0000
12.500 1.3110 0.04631 0.03901 -0.0479 0.1997 1.0000
12.750 1.3116 0.04869 0.04140 -0.0469 0.1845 1.0000
13.000 1.3118 0.05121 0.04394 -0.0460 0.1699 1.0000
13.250 1.3114 0.05386 0.04661 -0.0452 0.1560 1.0000
13.500 1.3109 0.05664 0.04942 -0.0446 0.1427 1.0000
13.750 1.3099 0.05956 0.05238 -0.0442 0.1301 1.0000
14.000 1.3086 0.06262 0.05549 -0.0439 0.1182 1.0000
14.250 1.3068 0.06582 0.05875 -0.0437 0.1074 1.0000
14.500 1.3038 0.06928 0.06226 -0.0437 0.0974 1.0000
14.750 1.2994 0.07300 0.06602 -0.0439 0.0886 1.0000
15.000 1.2973 0.07656 0.06968 -0.0441 0.0798 1.0000
15.250 1.2934 0.08045 0.07364 -0.0446 0.0725 1.0000
15.500 1.2874 0.08472 0.07796 -0.0453 0.0661 1.0000
15.750 1.2841 0.08872 0.08209 -0.0460 0.0599 1.0000
16.000 1.2767 0.09341 0.08681 -0.0472 0.0552 1.0000
16.250 1.2732 0.09760 0.09114 -0.0482 0.0502 1.0000
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Polar data table (+)
Polar graphs
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