EPPLER 584 AIRFOIL (e584-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 584 AIRFOIL (e584-il) Reynolds number: 500,000 Max Cl/Cd: 101.76 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e584-il-500000-n5.txt Download as CSV file: xf-e584-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 584 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0788 0.09309 0.08911 -0.1161 0.6946 0.0081
-11.500 -0.0764 0.08993 0.08595 -0.1174 0.6914 0.0079
-11.250 -0.0751 0.08658 0.08260 -0.1187 0.6885 0.0078
-11.000 -0.0788 0.08219 0.07821 -0.1204 0.6860 0.0076
-10.750 -0.0809 0.07829 0.07431 -0.1220 0.6834 0.0074
-10.250 -0.2393 0.04235 0.03813 -0.1366 0.6811 0.0059
-10.000 -0.2793 0.03724 0.03274 -0.1328 0.6790 0.0058
-9.750 -0.2949 0.03474 0.03005 -0.1290 0.6768 0.0058
-9.500 -0.3125 0.03231 0.02739 -0.1239 0.6746 0.0057
-9.250 -0.3219 0.03002 0.02482 -0.1196 0.6727 0.0057
-9.000 -0.3268 0.02737 0.02180 -0.1157 0.6711 0.0057
-8.750 -0.3221 0.02535 0.01945 -0.1128 0.6695 0.0057
-8.250 -0.2985 0.02217 0.01572 -0.1087 0.6666 0.0056
-8.000 -0.2815 0.02096 0.01429 -0.1072 0.6654 0.0056
-7.750 -0.2630 0.01981 0.01293 -0.1060 0.6640 0.0057
-7.500 -0.2428 0.01886 0.01181 -0.1049 0.6627 0.0057
-7.250 -0.2216 0.01806 0.01088 -0.1040 0.6612 0.0057
-7.000 -0.2000 0.01732 0.01000 -0.1032 0.6596 0.0058
-6.750 -0.1779 0.01668 0.00925 -0.1024 0.6579 0.0058
-6.500 -0.1554 0.01613 0.00860 -0.1016 0.6564 0.0059
-6.250 -0.1326 0.01561 0.00798 -0.1009 0.6549 0.0060
-6.000 -0.1095 0.01515 0.00745 -0.1003 0.6535 0.0060
-5.750 -0.0872 0.01460 0.00683 -0.0995 0.6522 0.0062
-5.500 -0.0640 0.01419 0.00639 -0.0989 0.6510 0.0064
-5.250 -0.0402 0.01383 0.00601 -0.0983 0.6495 0.0068
-5.000 -0.0161 0.01353 0.00567 -0.0978 0.6479 0.0071
-4.750 0.0083 0.01324 0.00534 -0.0973 0.6461 0.0077
-4.500 0.0331 0.01300 0.00505 -0.0969 0.6446 0.0082
-4.250 0.0577 0.01273 0.00476 -0.0965 0.6431 0.0093
-4.000 0.0830 0.01253 0.00451 -0.0962 0.6415 0.0107
-3.750 0.1084 0.01235 0.00430 -0.0959 0.6398 0.0134
-3.500 0.1339 0.01216 0.00412 -0.0957 0.6382 0.0205
-3.250 0.1582 0.01191 0.00396 -0.0952 0.6366 0.0354
-3.000 0.1825 0.01165 0.00382 -0.0948 0.6348 0.0589
-2.750 0.2065 0.01135 0.00370 -0.0944 0.6329 0.0987
-2.500 0.2300 0.01101 0.00358 -0.0939 0.6310 0.1588
-2.250 0.2531 0.01062 0.00347 -0.0935 0.6291 0.2379
-2.000 0.2755 0.01015 0.00335 -0.0929 0.6273 0.3457
-1.750 0.2969 0.00953 0.00319 -0.0924 0.6256 0.4901
-1.500 0.3147 0.00876 0.00324 -0.0907 0.6239 0.7092
-1.250 0.3383 0.00898 0.00364 -0.0894 0.6220 0.7814
-1.000 0.3660 0.00909 0.00372 -0.0894 0.6198 0.7984
-0.750 0.3939 0.00919 0.00377 -0.0895 0.6175 0.8090
-0.500 0.4207 0.00936 0.00391 -0.0892 0.6153 0.8192
-0.250 0.4448 0.00967 0.00422 -0.0880 0.6133 0.8319
0.000 0.4678 0.01000 0.00455 -0.0865 0.6114 0.8441
0.250 0.4929 0.01016 0.00469 -0.0858 0.6095 0.8497
0.500 0.5205 0.01015 0.00466 -0.0860 0.6068 0.8516
0.750 0.5486 0.01013 0.00462 -0.0863 0.6040 0.8533
1.000 0.5770 0.01011 0.00458 -0.0868 0.6013 0.8547
1.250 0.6055 0.01009 0.00452 -0.0872 0.5987 0.8557
1.500 0.6327 0.01008 0.00447 -0.0873 0.5964 0.8565
1.750 0.6597 0.01007 0.00447 -0.0874 0.5934 0.8572
2.000 0.6868 0.01006 0.00447 -0.0875 0.5900 0.8578
2.250 0.7135 0.01005 0.00446 -0.0875 0.5866 0.8586
2.500 0.7400 0.01005 0.00444 -0.0874 0.5835 0.8594
2.750 0.7668 0.01005 0.00443 -0.0875 0.5803 0.8600
3.000 0.7936 0.01007 0.00446 -0.0876 0.5762 0.8607
3.250 0.8200 0.01008 0.00447 -0.0876 0.5722 0.8613
3.500 0.8459 0.01010 0.00447 -0.0875 0.5682 0.8620
3.750 0.8719 0.01014 0.00451 -0.0874 0.5639 0.8628
4.000 0.8974 0.01018 0.00456 -0.0873 0.5587 0.8638
4.250 0.9225 0.01023 0.00459 -0.0870 0.5537 0.8645
4.500 0.9478 0.01029 0.00466 -0.0869 0.5486 0.8652
4.750 0.9730 0.01036 0.00475 -0.0867 0.5429 0.8660
5.000 0.9970 0.01045 0.00482 -0.0863 0.5370 0.8667
5.250 1.0217 0.01053 0.00492 -0.0860 0.5313 0.8674
5.500 1.0454 0.01062 0.00503 -0.0856 0.5244 0.8681
5.750 1.0683 0.01073 0.00514 -0.0850 0.5180 0.8689
6.000 1.0905 0.01083 0.00526 -0.0843 0.5096 0.8696
6.250 1.1102 0.01096 0.00538 -0.0830 0.5016 0.8706
6.500 1.1293 0.01110 0.00552 -0.0817 0.4922 0.8716
6.750 1.1468 0.01127 0.00569 -0.0800 0.4824 0.8724
7.000 1.1625 0.01151 0.00592 -0.0781 0.4724 0.8732
7.250 1.1783 0.01177 0.00618 -0.0762 0.4607 0.8740
7.500 1.1943 0.01205 0.00646 -0.0744 0.4502 0.8749
7.750 1.2077 0.01240 0.00680 -0.0721 0.4388 0.8758
8.000 1.2204 0.01279 0.00718 -0.0699 0.4269 0.8768
8.250 1.2327 0.01322 0.00759 -0.0676 0.4137 0.8779
8.500 1.2435 0.01371 0.00807 -0.0652 0.4005 0.8790
8.750 1.2525 0.01429 0.00864 -0.0626 0.3866 0.8803
9.000 1.2604 0.01496 0.00928 -0.0599 0.3727 0.8815
9.250 1.2667 0.01574 0.01004 -0.0572 0.3581 0.8828
9.500 1.2727 0.01660 0.01087 -0.0545 0.3445 0.8843
9.750 1.2771 0.01760 0.01185 -0.0519 0.3297 0.8859
10.000 1.2807 0.01873 0.01294 -0.0493 0.3148 0.8872
10.500 1.2861 0.02121 0.01539 -0.0443 0.2852 0.8897
10.750 1.2883 0.02260 0.01676 -0.0420 0.2707 0.8910
11.000 1.2906 0.02406 0.01821 -0.0399 0.2564 0.8924
11.250 1.2943 0.02550 0.01965 -0.0380 0.2441 0.8938
11.500 1.2970 0.02708 0.02120 -0.0362 0.2311 0.8952
11.750 1.2987 0.02879 0.02289 -0.0344 0.2172 0.8966
12.000 1.3008 0.03054 0.02461 -0.0329 0.2038 0.8981
12.250 1.3031 0.03236 0.02641 -0.0314 0.1905 0.8995
12.500 1.3052 0.03426 0.02828 -0.0301 0.1773 0.9009
12.750 1.3064 0.03628 0.03026 -0.0289 0.1630 0.9023
13.000 1.3076 0.03830 0.03225 -0.0276 0.1493 0.9036
13.250 1.3102 0.04025 0.03419 -0.0266 0.1375 0.9051
13.500 1.3147 0.04208 0.03603 -0.0257 0.1277 0.9067
13.750 1.3166 0.04418 0.03812 -0.0248 0.1168 0.9083
14.000 1.3196 0.04625 0.04019 -0.0240 0.1079 0.9101
14.250 1.3223 0.04839 0.04234 -0.0233 0.0986 0.9122
14.500 1.3268 0.05043 0.04440 -0.0227 0.0909 0.9142
14.750 1.3284 0.05280 0.04677 -0.0222 0.0822 0.9163
15.250 1.3321 0.05762 0.05161 -0.0214 0.0661 0.9206
15.500 1.3329 0.06026 0.05427 -0.0211 0.0584 0.9231
15.750 1.3350 0.06281 0.05684 -0.0210 0.0521 0.9258
16.000 1.3354 0.06564 0.05969 -0.0210 0.0460 0.9287
16.500 1.3397 0.07113 0.06526 -0.0213 0.0367 0.9359
16.750 1.3410 0.07405 0.06823 -0.0217 0.0331 0.9410
17.250 1.3452 0.08017 0.07450 -0.0231 0.0264 0.9576
17.500 1.3442 0.08338 0.07776 -0.0237 0.0234 1.0000
17.750 1.3438 0.08678 0.08121 -0.0245 0.0203 1.0000
18.000 1.3441 0.09011 0.08461 -0.0253 0.0184 1.0000
18.250 1.3426 0.09373 0.08827 -0.0263 0.0161 1.0000
18.500 1.3427 0.09719 0.09181 -0.0273 0.0146 1.0000
18.750 1.3407 0.10097 0.09565 -0.0285 0.0129 1.0000
19.000 1.3393 0.10472 0.09946 -0.0297 0.0113 1.0000
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