EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 582 AIRFOIL (e582-il) Reynolds number: 100,000 Max Cl/Cd: 45.41 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e582-il-100000-n5.txt Download as CSV file: xf-e582-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 582 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 -0.1668 0.08086 0.07599 -0.1043 0.9312 0.0239
-9.000 -0.1588 0.07722 0.07234 -0.1070 0.9235 0.0235
-8.750 -0.1516 0.07181 0.06691 -0.1129 0.9173 0.0230
-8.500 -0.1534 0.06661 0.06166 -0.1178 0.9077 0.0225
-8.250 -0.1578 0.06145 0.05637 -0.1219 0.8995 0.0219
-8.000 -0.1695 0.05762 0.05241 -0.1223 0.8886 0.0215
-7.750 -0.1767 0.05367 0.04824 -0.1221 0.8798 0.0210
-7.500 -0.1805 0.04940 0.04365 -0.1217 0.8723 0.0203
-7.250 -0.1876 0.04508 0.03889 -0.1195 0.8639 0.0196
-7.000 -0.1849 0.04104 0.03421 -0.1176 0.8575 0.0191
-6.750 -0.1729 0.03831 0.03109 -0.1166 0.8526 0.0190
-6.500 -0.1637 0.03616 0.02860 -0.1145 0.8458 0.0190
-6.250 -0.1446 0.03361 0.02557 -0.1139 0.8417 0.0191
-6.000 -0.1235 0.03143 0.02304 -0.1134 0.8380 0.0193
-5.750 -0.1090 0.03004 0.02142 -0.1114 0.8317 0.0196
-5.500 -0.0848 0.02849 0.01961 -0.1111 0.8278 0.0202
-5.250 -0.0564 0.02706 0.01794 -0.1114 0.8250 0.0213
-5.000 -0.0373 0.02615 0.01683 -0.1099 0.8198 0.0229
-4.750 -0.0160 0.02524 0.01578 -0.1088 0.8150 0.0251
-4.500 0.0104 0.02428 0.01473 -0.1087 0.8117 0.0277
-4.250 0.0387 0.02323 0.01352 -0.1087 0.8091 0.0302
-4.000 0.0523 0.02283 0.01317 -0.1064 0.8029 0.0343
-3.750 0.0740 0.02220 0.01249 -0.1055 0.7986 0.0417
-3.500 0.1004 0.02147 0.01171 -0.1053 0.7955 0.0574
-3.250 0.1269 0.02061 0.01107 -0.1053 0.7928 0.0985
-3.000 0.1365 0.02022 0.01109 -0.1025 0.7861 0.1716
-2.750 0.1530 0.01902 0.01083 -0.1013 0.7821 0.3840
-2.500 0.1572 0.01891 0.01206 -0.0935 0.7791 0.6888
-2.250 0.1714 0.01941 0.01237 -0.0911 0.7735 0.7680
-2.000 0.1856 0.01992 0.01274 -0.0876 0.7685 0.8016
-1.750 0.2051 0.02024 0.01292 -0.0847 0.7652 0.8266
-1.500 0.2281 0.02042 0.01293 -0.0824 0.7628 0.8487
-1.250 0.2267 0.02094 0.01344 -0.0760 0.7554 0.8700
-1.000 0.2464 0.02113 0.01353 -0.0727 0.7518 0.8981
-0.750 0.2825 0.02111 0.01333 -0.0734 0.7495 0.9168
-0.500 0.3189 0.02094 0.01297 -0.0751 0.7474 0.9211
-0.250 0.3241 0.02128 0.01329 -0.0715 0.7395 0.9275
0.000 0.3484 0.02120 0.01309 -0.0711 0.7358 0.9317
0.250 0.3822 0.02105 0.01279 -0.0725 0.7333 0.9341
0.500 0.3972 0.02131 0.01301 -0.0707 0.7270 0.9381
0.750 0.4195 0.02136 0.01299 -0.0702 0.7221 0.9414
1.000 0.4499 0.02125 0.01278 -0.0709 0.7191 0.9437
1.250 0.4844 0.02107 0.01249 -0.0723 0.7168 0.9454
1.500 0.4864 0.02159 0.01304 -0.0685 0.7080 0.9503
1.750 0.5183 0.02150 0.01289 -0.0695 0.7046 0.9520
2.000 0.5546 0.02133 0.01264 -0.0713 0.7022 0.9530
2.250 0.5555 0.02185 0.01320 -0.0673 0.6934 0.9588
2.500 0.5866 0.02178 0.01310 -0.0682 0.6896 0.9605
2.750 0.6247 0.02157 0.01284 -0.0702 0.6870 0.9612
3.000 0.6333 0.02212 0.01344 -0.0677 0.6782 0.9656
3.250 0.6662 0.02202 0.01334 -0.0689 0.6742 0.9676
3.500 0.7056 0.02175 0.01304 -0.0711 0.6715 0.9686
3.750 0.7119 0.02237 0.01374 -0.0684 0.6619 0.9741
4.000 0.7486 0.02218 0.01354 -0.0701 0.6582 0.9753
4.250 0.7686 0.02248 0.01392 -0.0695 0.6511 0.9796
4.500 0.7954 0.02254 0.01402 -0.0698 0.6451 0.9834
4.750 0.8374 0.02216 0.01365 -0.0723 0.6417 0.9843
5.000 0.8439 0.02273 0.01431 -0.0697 0.6317 1.0000
5.250 0.8802 0.02236 0.01398 -0.0711 0.6274 1.0000
5.500 0.8752 0.02295 0.01464 -0.0663 0.6173 1.0000
5.750 0.9123 0.02256 0.01428 -0.0678 0.6125 1.0000
6.250 0.9565 0.02270 0.01456 -0.0666 0.5971 1.0000
6.500 0.9641 0.02336 0.01531 -0.0642 0.5863 1.0000
6.750 0.9920 0.02329 0.01530 -0.0644 0.5784 1.0000
7.000 1.0147 0.02343 0.01553 -0.0640 0.5689 1.0000
7.250 1.0305 0.02390 0.01608 -0.0628 0.5579 1.0000
7.500 1.0562 0.02393 0.01619 -0.0628 0.5479 1.0000
7.750 1.0839 0.02387 0.01620 -0.0630 0.5372 1.0000
8.000 1.0992 0.02439 0.01681 -0.0617 0.5240 1.0000
8.250 1.1172 0.02481 0.01731 -0.0608 0.5105 1.0000
8.750 1.1554 0.02560 0.01823 -0.0593 0.4813 1.0000
9.000 1.1735 0.02607 0.01873 -0.0584 0.4654 1.0000
9.250 1.1912 0.02657 0.01926 -0.0574 0.4486 1.0000
9.500 1.2066 0.02722 0.01992 -0.0563 0.4309 1.0000
9.750 1.2183 0.02812 0.02087 -0.0549 0.4124 1.0000
10.000 1.2298 0.02906 0.02181 -0.0535 0.3933 1.0000
10.250 1.2409 0.03006 0.02280 -0.0521 0.3743 1.0000
10.500 1.2500 0.03122 0.02394 -0.0506 0.3551 1.0000
10.750 1.2572 0.03256 0.02529 -0.0491 0.3360 1.0000
11.000 1.2638 0.03398 0.02672 -0.0476 0.3173 1.0000
11.250 1.2694 0.03551 0.02824 -0.0461 0.2991 1.0000
11.500 1.2741 0.03716 0.02988 -0.0447 0.2813 1.0000
11.750 1.2781 0.03894 0.03168 -0.0434 0.2636 1.0000
12.000 1.2812 0.04085 0.03360 -0.0421 0.2463 1.0000
12.250 1.2836 0.04288 0.03563 -0.0409 0.2295 1.0000
12.500 1.2852 0.04504 0.03782 -0.0398 0.2133 1.0000
12.750 1.2864 0.04733 0.04012 -0.0388 0.1976 1.0000
13.000 1.2870 0.04976 0.04256 -0.0380 0.1826 1.0000
13.250 1.2873 0.05232 0.04513 -0.0373 0.1682 1.0000
13.500 1.2872 0.05500 0.04784 -0.0367 0.1544 1.0000
13.750 1.2866 0.05784 0.05072 -0.0362 0.1411 1.0000
14.000 1.2858 0.06078 0.05371 -0.0359 0.1287 1.0000
14.250 1.2845 0.06388 0.05686 -0.0357 0.1171 1.0000
14.500 1.2825 0.06715 0.06018 -0.0357 0.1064 1.0000
14.750 1.2793 0.07067 0.06373 -0.0358 0.0969 1.0000
15.000 1.2756 0.07438 0.06750 -0.0361 0.0879 1.0000
15.250 1.2734 0.07798 0.07121 -0.0365 0.0796 1.0000
15.500 1.2686 0.08200 0.07528 -0.0371 0.0728 1.0000
15.750 1.2643 0.08608 0.07946 -0.0379 0.0661 1.0000
16.000 1.2597 0.09028 0.08374 -0.0388 0.0605 1.0000
16.250 1.2544 0.09470 0.08825 -0.0399 0.0554 1.0000
16.500 1.2488 0.09920 0.09284 -0.0412 0.0510 1.0000
16.750 1.2443 0.10366 0.09743 -0.0426 0.0468 1.0000
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