EPPLER 583 AIRFOIL (e583-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 583 AIRFOIL (e583-il) Reynolds number: 500,000 Max Cl/Cd: 107.74 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e583-il-500000-n5.txt Download as CSV file: xf-e583-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 583 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1227 0.07902 0.07535 -0.1171 0.7362 0.0049
-10.750 -0.1544 0.06601 0.06237 -0.1233 0.7276 0.0047
-10.250 -0.2857 0.03900 0.03491 -0.1334 0.7186 0.0044
-10.000 -0.3372 0.03295 0.02839 -0.1279 0.7138 0.0044
-9.750 -0.3563 0.03029 0.02544 -0.1230 0.7091 0.0043
-9.500 -0.3693 0.02698 0.02167 -0.1186 0.7047 0.0044
-9.250 -0.3643 0.02511 0.01949 -0.1161 0.7008 0.0044
-9.000 -0.3556 0.02329 0.01734 -0.1138 0.6974 0.0045
-8.750 -0.3411 0.02202 0.01585 -0.1123 0.6941 0.0046
-8.500 -0.3249 0.02080 0.01442 -0.1109 0.6908 0.0046
-8.250 -0.3065 0.01979 0.01317 -0.1097 0.6875 0.0048
-8.000 -0.2875 0.01887 0.01208 -0.1086 0.6846 0.0049
-7.750 -0.2684 0.01795 0.01103 -0.1076 0.6818 0.0051
-7.500 -0.2466 0.01734 0.01034 -0.1069 0.6788 0.0053
-7.250 -0.2245 0.01676 0.00968 -0.1062 0.6757 0.0054
-7.000 -0.2018 0.01626 0.00910 -0.1056 0.6728 0.0057
-6.750 -0.1792 0.01572 0.00847 -0.1049 0.6702 0.0058
-6.500 -0.1559 0.01529 0.00794 -0.1043 0.6678 0.0062
-6.250 -0.1327 0.01484 0.00741 -0.1037 0.6655 0.0064
-6.000 -0.1090 0.01440 0.00691 -0.1032 0.6632 0.0066
-5.750 -0.0849 0.01402 0.00648 -0.1027 0.6605 0.0068
-5.500 -0.0612 0.01361 0.00603 -0.1022 0.6579 0.0073
-5.250 -0.0367 0.01329 0.00567 -0.1018 0.6554 0.0077
-5.000 -0.0116 0.01305 0.00539 -0.1015 0.6532 0.0086
-4.750 0.0133 0.01279 0.00506 -0.1011 0.6510 0.0094
-4.500 0.0383 0.01250 0.00474 -0.1008 0.6488 0.0104
-4.000 0.0892 0.01197 0.00418 -0.1003 0.6442 0.0142
-3.750 0.1147 0.01173 0.00394 -0.1000 0.6418 0.0193
-3.500 0.1403 0.01149 0.00375 -0.0998 0.6394 0.0308
-3.250 0.1658 0.01126 0.00358 -0.0996 0.6372 0.0497
-3.000 0.1913 0.01101 0.00342 -0.0995 0.6351 0.0790
-2.750 0.2167 0.01074 0.00329 -0.0994 0.6329 0.1196
-2.500 0.2416 0.01036 0.00316 -0.0992 0.6308 0.1867
-2.250 0.2659 0.00989 0.00303 -0.0991 0.6285 0.2858
-2.000 0.2900 0.00933 0.00288 -0.0991 0.6261 0.4097
-1.750 0.3130 0.00856 0.00271 -0.0988 0.6238 0.5895
-1.500 0.3376 0.00838 0.00290 -0.0982 0.6216 0.7098
-1.250 0.3653 0.00847 0.00296 -0.0981 0.6194 0.7367
-1.000 0.3934 0.00856 0.00301 -0.0982 0.6172 0.7520
-0.750 0.4213 0.00862 0.00306 -0.0983 0.6149 0.7621
-0.500 0.4488 0.00873 0.00316 -0.0982 0.6124 0.7766
-0.250 0.4750 0.00893 0.00338 -0.0977 0.6098 0.7936
0.000 0.5017 0.00908 0.00351 -0.0974 0.6073 0.8034
0.250 0.5304 0.00912 0.00348 -0.0977 0.6048 0.8062
0.500 0.5585 0.00917 0.00347 -0.0980 0.6024 0.8078
0.750 0.5865 0.00920 0.00349 -0.0982 0.5999 0.8091
1.000 0.6142 0.00922 0.00352 -0.0984 0.5971 0.8105
1.250 0.6421 0.00926 0.00355 -0.0986 0.5943 0.8120
1.500 0.6699 0.00929 0.00356 -0.0988 0.5913 0.8135
1.750 0.6977 0.00934 0.00358 -0.0990 0.5886 0.8149
2.000 0.7256 0.00941 0.00360 -0.0992 0.5859 0.8165
2.250 0.7532 0.00944 0.00366 -0.0994 0.5828 0.8183
2.500 0.7809 0.00948 0.00371 -0.0997 0.5794 0.8200
2.750 0.8084 0.00953 0.00374 -0.0999 0.5757 0.8215
3.000 0.8358 0.00959 0.00378 -0.1001 0.5721 0.8229
3.250 0.8626 0.00964 0.00383 -0.1001 0.5685 0.8241
3.500 0.8891 0.00968 0.00391 -0.1001 0.5640 0.8253
3.750 0.9151 0.00974 0.00398 -0.1000 0.5594 0.8268
4.000 0.9408 0.00982 0.00405 -0.0998 0.5550 0.8284
4.250 0.9669 0.00988 0.00415 -0.0997 0.5500 0.8300
4.500 0.9924 0.00995 0.00424 -0.0995 0.5446 0.8315
4.750 1.0173 0.01005 0.00432 -0.0992 0.5394 0.8332
5.000 1.0428 0.01012 0.00444 -0.0991 0.5332 0.8348
5.250 1.0670 0.01023 0.00454 -0.0987 0.5265 0.8366
5.500 1.0913 0.01034 0.00467 -0.0983 0.5195 0.8383
5.750 1.1143 0.01046 0.00480 -0.0977 0.5115 0.8399
6.000 1.1363 0.01059 0.00495 -0.0968 0.5033 0.8416
6.250 1.1562 0.01076 0.00512 -0.0956 0.4941 0.8435
6.500 1.1765 0.01092 0.00530 -0.0944 0.4843 0.8455
6.750 1.1935 0.01111 0.00549 -0.0926 0.4745 0.8477
7.000 1.2086 0.01136 0.00573 -0.0905 0.4636 0.8500
7.250 1.2247 0.01164 0.00600 -0.0886 0.4516 0.8524
7.500 1.2398 0.01196 0.00631 -0.0867 0.4399 0.8548
7.750 1.2531 0.01233 0.00667 -0.0843 0.4279 0.8570
8.000 1.2646 0.01274 0.00708 -0.0818 0.4154 0.8595
8.250 1.2756 0.01320 0.00754 -0.0792 0.4023 0.8625
8.500 1.2863 0.01371 0.00804 -0.0768 0.3889 0.8658
8.750 1.2947 0.01433 0.00864 -0.0740 0.3742 0.8694
9.000 1.3018 0.01503 0.00933 -0.0712 0.3595 0.8726
9.250 1.3050 0.01591 0.01018 -0.0680 0.3426 0.8761
9.500 1.3103 0.01680 0.01106 -0.0652 0.3282 0.8801
9.750 1.3138 0.01786 0.01210 -0.0624 0.3127 0.8844
10.000 1.3186 0.01893 0.01318 -0.0599 0.2993 0.8886
10.250 1.3207 0.02019 0.01442 -0.0573 0.2842 0.8936
10.500 1.3229 0.02153 0.01575 -0.0548 0.2696 0.8995
10.750 1.3250 0.02292 0.01714 -0.0525 0.2559 0.9061
11.000 1.3271 0.02434 0.01856 -0.0502 0.2429 0.9145
11.250 1.3285 0.02585 0.02009 -0.0480 0.2296 0.9252
11.500 1.3322 0.02747 0.02171 -0.0465 0.2158 0.9424
12.000 1.3409 0.03104 0.02525 -0.0445 0.1869 1.0000
12.250 1.3428 0.03301 0.02716 -0.0432 0.1721 1.0000
12.500 1.3447 0.03502 0.02913 -0.0419 0.1581 1.0000
12.750 1.3470 0.03706 0.03113 -0.0409 0.1455 1.0000
13.000 1.3499 0.03909 0.03313 -0.0399 0.1332 1.0000
13.250 1.3541 0.04106 0.03509 -0.0391 0.1227 1.0000
13.500 1.3584 0.04307 0.03710 -0.0383 0.1136 1.0000
13.750 1.3611 0.04527 0.03928 -0.0376 0.1034 1.0000
14.000 1.3632 0.04758 0.04158 -0.0370 0.0940 1.0000
14.250 1.3674 0.04973 0.04373 -0.0364 0.0853 1.0000
14.500 1.3697 0.05212 0.04612 -0.0360 0.0768 1.0000
14.750 1.3720 0.05457 0.04856 -0.0356 0.0692 1.0000
15.000 1.3732 0.05718 0.05116 -0.0353 0.0616 1.0000
15.250 1.3749 0.05980 0.05379 -0.0350 0.0544 1.0000
15.500 1.3775 0.06236 0.05637 -0.0349 0.0486 1.0000
15.750 1.3783 0.06520 0.05923 -0.0349 0.0431 1.0000
16.000 1.3796 0.06803 0.06208 -0.0349 0.0381 1.0000
16.250 1.3809 0.07093 0.06501 -0.0351 0.0336 1.0000
16.500 1.3814 0.07395 0.06807 -0.0353 0.0294 1.0000
16.750 1.3815 0.07710 0.07125 -0.0356 0.0260 1.0000
17.000 1.3822 0.08024 0.07444 -0.0361 0.0231 1.0000
17.250 1.3818 0.08357 0.07782 -0.0366 0.0199 1.0000
17.500 1.3806 0.08706 0.08135 -0.0373 0.0174 1.0000
17.750 1.3805 0.09045 0.08481 -0.0380 0.0156 1.0000
18.000 1.3805 0.09387 0.08830 -0.0388 0.0141 1.0000
18.500 1.3769 0.10140 0.09595 -0.0409 0.0107 1.0000
18.750 1.3753 0.10519 0.09981 -0.0421 0.0095 1.0000
19.000 1.3739 0.10898 0.10368 -0.0433 0.0083 1.0000
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