EPPLER 584 AIRFOIL (e584-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 584 AIRFOIL (e584-il) Reynolds number: 200,000 Max Cl/Cd: 64.44 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e584-il-200000-n5.txt Download as CSV file: xf-e584-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0783 0.08513 0.08053 -0.1194 0.7885 0.0133
-10.750 -0.0743 0.08245 0.07780 -0.1204 0.7800 0.0131
-10.500 -0.0749 0.07874 0.07408 -0.1220 0.7731 0.0129
-10.250 -0.0769 0.07486 0.07019 -0.1238 0.7665 0.0127
-9.750 -0.1009 0.06257 0.05790 -0.1315 0.7557 0.0121
-9.250 -0.2061 0.04357 0.03823 -0.1314 0.7453 0.0106
-9.000 -0.2242 0.04105 0.03550 -0.1272 0.7406 0.0106
-8.750 -0.2352 0.03870 0.03293 -0.1234 0.7361 0.0105
-8.500 -0.2404 0.03624 0.03016 -0.1200 0.7320 0.0105
-8.250 -0.2403 0.03390 0.02748 -0.1170 0.7286 0.0104
-8.000 -0.2360 0.03165 0.02491 -0.1143 0.7251 0.0104
-7.750 -0.2290 0.02930 0.02215 -0.1117 0.7217 0.0104
-7.500 -0.2166 0.02735 0.01985 -0.1097 0.7186 0.0104
-7.250 -0.2001 0.02570 0.01785 -0.1081 0.7159 0.0105
-7.000 -0.1809 0.02416 0.01597 -0.1069 0.7135 0.0106
-6.750 -0.1600 0.02298 0.01461 -0.1061 0.7112 0.0108
-6.500 -0.1385 0.02201 0.01352 -0.1052 0.7085 0.0110
-6.250 -0.1165 0.02117 0.01258 -0.1045 0.7055 0.0114
-6.000 -0.0939 0.02038 0.01166 -0.1037 0.7027 0.0118
-5.750 -0.0713 0.01963 0.01080 -0.1030 0.7001 0.0123
-5.500 -0.0486 0.01896 0.00998 -0.1022 0.6979 0.0130
-5.250 -0.0264 0.01836 0.00931 -0.1014 0.6959 0.0138
-5.000 -0.0041 0.01795 0.00886 -0.1006 0.6935 0.0152
-4.750 0.0183 0.01754 0.00842 -0.0999 0.6910 0.0175
-4.500 0.0408 0.01713 0.00795 -0.0990 0.6885 0.0199
-4.250 0.0633 0.01670 0.00747 -0.0982 0.6860 0.0230
-4.000 0.0863 0.01630 0.00704 -0.0975 0.6838 0.0290
-3.750 0.1095 0.01591 0.00667 -0.0969 0.6820 0.0428
-3.500 0.1310 0.01553 0.00643 -0.0960 0.6796 0.0687
-3.000 0.1721 0.01467 0.00605 -0.0941 0.6744 0.1826
-2.750 0.1902 0.01404 0.00586 -0.0929 0.6721 0.2970
-2.500 0.2040 0.01316 0.00566 -0.0909 0.6699 0.4763
-2.250 0.2187 0.01330 0.00685 -0.0860 0.6679 0.7200
-2.000 0.2407 0.01369 0.00717 -0.0844 0.6656 0.7836
-1.750 0.2620 0.01395 0.00733 -0.0831 0.6628 0.8088
-1.500 0.2850 0.01428 0.00756 -0.0818 0.6602 0.8246
-1.250 0.3094 0.01461 0.00781 -0.0806 0.6577 0.8363
-1.000 0.3341 0.01506 0.00817 -0.0791 0.6555 0.8502
-0.750 0.3593 0.01563 0.00865 -0.0774 0.6534 0.8692
-0.500 0.3889 0.01598 0.00896 -0.0769 0.6510 0.8804
-0.250 0.4039 0.01601 0.00896 -0.0746 0.6479 0.8875
0.000 0.4306 0.01604 0.00892 -0.0745 0.6452 0.8895
0.250 0.4578 0.01606 0.00887 -0.0746 0.6425 0.8915
0.500 0.4853 0.01609 0.00881 -0.0748 0.6402 0.8936
0.750 0.5124 0.01613 0.00876 -0.0749 0.6381 0.8958
1.000 0.5282 0.01614 0.00881 -0.0729 0.6347 0.8991
1.250 0.5456 0.01615 0.00881 -0.0713 0.6314 0.9023
1.500 0.5702 0.01616 0.00878 -0.0710 0.6286 0.9037
1.750 0.5974 0.01617 0.00874 -0.0711 0.6260 0.9049
2.000 0.6243 0.01620 0.00872 -0.0713 0.6236 0.9061
2.250 0.6415 0.01623 0.00882 -0.0695 0.6197 0.9080
2.500 0.6626 0.01625 0.00885 -0.0686 0.6161 0.9099
2.750 0.6867 0.01625 0.00884 -0.0682 0.6131 0.9112
3.000 0.7136 0.01624 0.00880 -0.0684 0.6106 0.9123
3.250 0.7305 0.01629 0.00891 -0.0667 0.6066 0.9145
3.500 0.7503 0.01632 0.00897 -0.0656 0.6024 0.9160
3.750 0.7745 0.01631 0.00896 -0.0653 0.5990 0.9171
4.000 0.8018 0.01626 0.00891 -0.0656 0.5963 0.9178
4.250 0.8177 0.01632 0.00906 -0.0637 0.5913 0.9192
4.500 0.8382 0.01632 0.00909 -0.0626 0.5870 0.9207
4.750 0.8632 0.01626 0.00903 -0.0624 0.5834 0.9216
5.000 0.8850 0.01626 0.00909 -0.0616 0.5793 0.9227
5.250 0.9029 0.01632 0.00921 -0.0602 0.5739 0.9241
5.500 0.9265 0.01627 0.00918 -0.0597 0.5695 0.9251
5.750 0.9504 0.01624 0.00917 -0.0593 0.5651 0.9261
6.000 0.9661 0.01634 0.00935 -0.0576 0.5588 0.9277
6.250 0.9886 0.01631 0.00933 -0.0569 0.5538 0.9292
6.500 1.0085 0.01635 0.00941 -0.0558 0.5485 0.9308
6.750 1.0233 0.01649 0.00962 -0.0539 0.5417 0.9323
7.000 1.0473 0.01647 0.00960 -0.0535 0.5361 0.9333
7.250 1.0589 0.01672 0.00995 -0.0511 0.5285 0.9351
7.500 1.0787 0.01682 0.01008 -0.0500 0.5216 0.9365
7.750 1.0927 0.01708 0.01042 -0.0481 0.5134 0.9384
8.000 1.1116 0.01725 0.01060 -0.0471 0.5054 0.9401
8.250 1.1246 0.01760 0.01103 -0.0452 0.4962 0.9422
8.500 1.1424 0.01785 0.01130 -0.0441 0.4873 0.9440
8.750 1.1550 0.01825 0.01176 -0.0422 0.4771 0.9465
9.000 1.1678 0.01866 0.01221 -0.0404 0.4669 0.9493
9.250 1.1821 0.01909 0.01265 -0.0390 0.4563 0.9521
9.500 1.1934 0.01969 0.01329 -0.0373 0.4444 0.9551
9.750 1.2045 0.02038 0.01402 -0.0357 0.4322 0.9583
10.000 1.2160 0.02113 0.01480 -0.0343 0.4194 0.9619
10.250 1.2271 0.02201 0.01570 -0.0332 0.4056 0.9664
10.750 1.2484 0.02414 0.01786 -0.0315 0.3766 0.9816
11.000 1.2540 0.02535 0.01907 -0.0300 0.3624 1.0000
11.250 1.2593 0.02677 0.02049 -0.0286 0.3474 1.0000
11.500 1.2641 0.02828 0.02199 -0.0274 0.3325 1.0000
11.750 1.2684 0.02988 0.02359 -0.0262 0.3177 1.0000
12.000 1.2716 0.03162 0.02532 -0.0250 0.3025 1.0000
12.250 1.2745 0.03344 0.02712 -0.0239 0.2876 1.0000
12.500 1.2770 0.03536 0.02903 -0.0229 0.2728 1.0000
12.750 1.2797 0.03733 0.03101 -0.0220 0.2586 1.0000
13.000 1.2822 0.03937 0.03304 -0.0211 0.2449 1.0000
13.250 1.2843 0.04150 0.03516 -0.0204 0.2314 1.0000
13.500 1.2859 0.04372 0.03737 -0.0197 0.2182 1.0000
13.750 1.2871 0.04603 0.03968 -0.0191 0.2050 1.0000
14.000 1.2874 0.04848 0.04212 -0.0185 0.1920 1.0000
14.250 1.2879 0.05098 0.04462 -0.0180 0.1788 1.0000
14.500 1.2887 0.05353 0.04716 -0.0177 0.1658 1.0000
14.750 1.2892 0.05616 0.04980 -0.0174 0.1535 1.0000
15.000 1.2895 0.05888 0.05253 -0.0172 0.1420 1.0000
15.250 1.2892 0.06172 0.05537 -0.0171 0.1311 1.0000
15.500 1.2881 0.06474 0.05840 -0.0172 0.1209 1.0000
15.750 1.2879 0.06772 0.06141 -0.0173 0.1108 1.0000
16.000 1.2889 0.07062 0.06435 -0.0175 0.1019 1.0000
16.250 1.2880 0.07381 0.06757 -0.0178 0.0940 1.0000
16.500 1.2865 0.07714 0.07092 -0.0183 0.0860 1.0000
16.750 1.2865 0.08034 0.07418 -0.0188 0.0786 1.0000
17.000 1.2844 0.08386 0.07774 -0.0194 0.0723 1.0000
17.250 1.2830 0.08735 0.08128 -0.0201 0.0658 1.0000
17.500 1.2812 0.09094 0.08494 -0.0210 0.0600 1.0000
18.000 1.2760 0.09854 0.09267 -0.0230 0.0498 1.0000
18.250 1.2725 0.10255 0.09673 -0.0243 0.0454 1.0000
18.500 1.2696 0.10651 0.10076 -0.0256 0.0415 1.0000
18.750 1.2660 0.11062 0.10494 -0.0270 0.0380 1.0000
19.000 1.2625 0.11478 0.10918 -0.0286 0.0348 1.0000
19.250 1.2590 0.11896 0.11345 -0.0303 0.0320 1.0000
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