EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 582 AIRFOIL (e582-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.21 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e582-il-1000000-n5.txt Download as CSV file: xf-e582-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3656 0.03162 0.02834 -0.1354 0.7767 0.0024
-10.000 -0.3967 0.02668 0.02294 -0.1300 0.7692 0.0023
-9.500 -0.3965 0.02136 0.01688 -0.1244 0.7589 0.0025
-9.250 -0.3820 0.02003 0.01533 -0.1230 0.7543 0.0025
-9.000 -0.3652 0.01892 0.01402 -0.1218 0.7500 0.0026
-8.750 -0.3454 0.01813 0.01308 -0.1210 0.7462 0.0026
-8.500 -0.3249 0.01728 0.01208 -0.1202 0.7426 0.0026
-8.250 -0.3093 0.01562 0.01014 -0.1188 0.7389 0.0029
-8.000 -0.2869 0.01500 0.00941 -0.1182 0.7353 0.0030
-7.750 -0.2636 0.01453 0.00885 -0.1178 0.7319 0.0031
-7.500 -0.2394 0.01403 0.00828 -0.1174 0.7289 0.0032
-7.250 -0.2155 0.01348 0.00765 -0.1170 0.7259 0.0033
-7.000 -0.1910 0.01306 0.00715 -0.1167 0.7226 0.0034
-6.750 -0.1664 0.01266 0.00666 -0.1164 0.7195 0.0035
-6.500 -0.1416 0.01228 0.00621 -0.1161 0.7165 0.0037
-6.250 -0.1160 0.01191 0.00580 -0.1159 0.7140 0.0038
-6.000 -0.0906 0.01153 0.00536 -0.1157 0.7112 0.0039
-5.750 -0.0649 0.01120 0.00498 -0.1155 0.7082 0.0041
-5.500 -0.0392 0.01089 0.00460 -0.1153 0.7052 0.0042
-5.250 -0.0134 0.01061 0.00427 -0.1151 0.7024 0.0042
-5.000 0.0131 0.01036 0.00398 -0.1151 0.6999 0.0043
-4.750 0.0396 0.01008 0.00368 -0.1151 0.6971 0.0045
-4.500 0.0661 0.00980 0.00338 -0.1150 0.6942 0.0050
-4.250 0.0930 0.00962 0.00317 -0.1150 0.6913 0.0054
-4.000 0.1199 0.00945 0.00296 -0.1150 0.6884 0.0059
-3.750 0.1469 0.00929 0.00276 -0.1150 0.6856 0.0064
-3.500 0.1744 0.00908 0.00256 -0.1151 0.6830 0.0076
-3.250 0.2019 0.00891 0.00239 -0.1153 0.6800 0.0107
-3.000 0.2291 0.00871 0.00223 -0.1154 0.6767 0.0227
-2.750 0.2564 0.00856 0.00211 -0.1155 0.6736 0.0371
-2.500 0.2835 0.00838 0.00201 -0.1156 0.6706 0.0608
-2.250 0.3109 0.00809 0.00191 -0.1159 0.6675 0.1145
-2.000 0.3380 0.00772 0.00182 -0.1162 0.6640 0.1994
-1.750 0.3655 0.00745 0.00174 -0.1166 0.6604 0.2725
-1.500 0.3929 0.00716 0.00166 -0.1169 0.6569 0.3559
-1.250 0.4211 0.00663 0.00156 -0.1177 0.6536 0.5043
-1.000 0.4495 0.00604 0.00156 -0.1184 0.6498 0.6939
-0.750 0.4776 0.00608 0.00165 -0.1185 0.6457 0.7350
-0.500 0.5056 0.00615 0.00168 -0.1186 0.6416 0.7467
-0.250 0.5342 0.00620 0.00171 -0.1189 0.6375 0.7561
0.000 0.5625 0.00629 0.00177 -0.1191 0.6324 0.7675
0.250 0.5893 0.00642 0.00189 -0.1189 0.6272 0.7793
0.500 0.6171 0.00653 0.00199 -0.1189 0.6224 0.7878
0.750 0.6447 0.00659 0.00204 -0.1190 0.6171 0.7910
1.000 0.6722 0.00666 0.00206 -0.1191 0.6120 0.7921
1.250 0.7004 0.00670 0.00209 -0.1193 0.6068 0.7930
1.500 0.7280 0.00676 0.00211 -0.1195 0.6005 0.7940
1.750 0.7553 0.00683 0.00215 -0.1196 0.5942 0.7949
2.000 0.7828 0.00689 0.00219 -0.1197 0.5867 0.7957
2.250 0.8096 0.00698 0.00224 -0.1197 0.5795 0.7964
2.500 0.8368 0.00705 0.00229 -0.1198 0.5717 0.7971
2.750 0.8632 0.00715 0.00235 -0.1197 0.5637 0.7979
3.000 0.8897 0.00725 0.00242 -0.1197 0.5549 0.7987
3.250 0.9160 0.00736 0.00250 -0.1196 0.5460 0.7994
3.500 0.9413 0.00749 0.00259 -0.1193 0.5358 0.8000
3.750 0.9667 0.00761 0.00269 -0.1191 0.5245 0.8007
4.000 0.9915 0.00775 0.00280 -0.1187 0.5128 0.8014
4.250 1.0154 0.00792 0.00293 -0.1182 0.4989 0.8022
4.500 1.0386 0.00812 0.00308 -0.1175 0.4840 0.8029
4.750 1.0611 0.00833 0.00324 -0.1168 0.4684 0.8037
5.000 1.0825 0.00858 0.00343 -0.1158 0.4509 0.8045
5.250 1.1031 0.00885 0.00364 -0.1146 0.4331 0.8053
5.500 1.1229 0.00914 0.00386 -0.1133 0.4148 0.8063
5.750 1.1407 0.00944 0.00409 -0.1117 0.3961 0.8074
6.000 1.1571 0.00974 0.00433 -0.1097 0.3778 0.8084
6.250 1.1727 0.01010 0.00462 -0.1076 0.3592 0.8094
6.500 1.1877 0.01050 0.00495 -0.1055 0.3400 0.8104
6.750 1.2030 0.01090 0.00528 -0.1035 0.3218 0.8114
7.000 1.2169 0.01136 0.00566 -0.1012 0.3011 0.8124
7.250 1.2304 0.01184 0.00606 -0.0990 0.2831 0.8134
7.750 1.2581 0.01281 0.00692 -0.0947 0.2509 0.8152
8.000 1.2710 0.01334 0.00740 -0.0926 0.2352 0.8163
8.250 1.2827 0.01393 0.00794 -0.0903 0.2185 0.8175
8.500 1.2933 0.01460 0.00855 -0.0879 0.2010 0.8187
8.750 1.3032 0.01532 0.00922 -0.0855 0.1843 0.8199
9.000 1.3120 0.01614 0.00997 -0.0830 0.1674 0.8213
9.250 1.3204 0.01703 0.01079 -0.0806 0.1504 0.8228
9.500 1.3260 0.01811 0.01177 -0.0779 0.1294 0.8244
9.750 1.3337 0.01913 0.01273 -0.0757 0.1143 0.8259
10.000 1.3469 0.01989 0.01351 -0.0742 0.1079 0.8272
10.250 1.3504 0.02124 0.01475 -0.0717 0.0887 0.8285
10.500 1.3566 0.02250 0.01594 -0.0696 0.0744 0.8298
10.750 1.3589 0.02405 0.01740 -0.0672 0.0561 0.8312
11.000 1.3689 0.02515 0.01850 -0.0657 0.0495 0.8326
11.250 1.3758 0.02649 0.01981 -0.0640 0.0405 0.8342
11.500 1.3829 0.02786 0.02118 -0.0624 0.0331 0.8357
11.750 1.3897 0.02929 0.02261 -0.0609 0.0264 0.8374
12.250 1.4047 0.03220 0.02552 -0.0583 0.0175 0.8409
12.500 1.4113 0.03379 0.02713 -0.0570 0.0133 0.8426
12.750 1.4196 0.03529 0.02865 -0.0560 0.0109 0.8444
13.250 1.4355 0.03843 0.03189 -0.0541 0.0076 0.8482
13.500 1.4436 0.04004 0.03355 -0.0533 0.0063 0.8504
13.750 1.4509 0.04177 0.03534 -0.0524 0.0054 0.8530
14.000 1.4569 0.04365 0.03726 -0.0517 0.0039 0.8558
14.250 1.4622 0.04566 0.03933 -0.0509 0.0028 0.8585
14.750 1.4753 0.04956 0.04337 -0.0498 0.0020 0.8645
15.000 1.4804 0.05173 0.04562 -0.0494 0.0017 0.8681
15.250 1.4831 0.05421 0.04818 -0.0489 0.0009 0.8718
15.750 1.4916 0.05898 0.05312 -0.0483 0.0006 0.8805
16.000 1.4942 0.06163 0.05586 -0.0482 0.0005 0.8861
16.250 1.4967 0.06434 0.05867 -0.0481 0.0003 0.8926
16.500 1.4986 0.06712 0.06157 -0.0481 0.0003 0.9016
16.750 1.4998 0.06995 0.06452 -0.0480 0.0002 0.9156
17.000 1.4995 0.07292 0.06767 -0.0481 0.0002 0.9783
17.250 1.5007 0.07603 0.07086 -0.0484 0.0002 1.0000
17.500 1.4999 0.07955 0.07449 -0.0490 0.0002 1.0000
17.750 1.5001 0.08299 0.07801 -0.0497 0.0002 1.0000
18.000 1.4962 0.08709 0.08222 -0.0506 0.0001 1.0000
18.250 1.4935 0.09109 0.08632 -0.0517 0.0001 1.0000
18.750 1.4852 0.09978 0.09522 -0.0542 0.0001 1.0000
19.000 1.4814 0.10414 0.09969 -0.0557 0.0001 1.0000
19.250 1.4768 0.10868 0.10434 -0.0574 0.0001 1.0000
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