EPPLER 585 AIRFOIL (e585-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 585 AIRFOIL (e585-il) Reynolds number: 200,000 Max Cl/Cd: 81.43 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e585-il-200000.txt Download as CSV file: xf-e585-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 585 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2125 0.11730 0.11390 -0.0712 0.9810 0.0341
-10.750 -0.2041 0.11237 0.10899 -0.0777 0.9759 0.0360
-10.500 -0.2006 0.10613 0.10277 -0.0888 0.9720 0.0367
-10.250 -0.1844 0.10190 0.09854 -0.0873 0.9676 0.0378
-10.000 -0.1653 0.09861 0.09524 -0.0892 0.9636 0.0392
-9.750 -0.1488 0.09445 0.09107 -0.0936 0.9606 0.0407
-9.500 -0.1366 0.08978 0.08640 -0.0989 0.9562 0.0428
-8.750 -0.1027 0.07426 0.07088 -0.1173 0.9406 0.0486
-8.500 -0.0880 0.07006 0.06666 -0.1225 0.9344 0.0515
-8.250 -0.0877 0.06366 0.06020 -0.1319 0.9245 0.0534
-8.000 -0.1012 0.05898 0.05535 -0.1368 0.9124 0.0548
-7.750 -0.1199 0.05659 0.05248 -0.1380 0.9006 0.0561
-7.250 -0.1047 0.04909 0.04503 -0.1375 0.8874 0.0595
-7.000 -0.0961 0.04698 0.04283 -0.1367 0.8811 0.0618
-6.750 -0.0969 0.04761 0.04273 -0.1344 0.8726 0.0686
-5.500 -0.0264 0.02607 0.01905 -0.1265 0.8466 0.0290
-5.250 -0.0018 0.02385 0.01657 -0.1260 0.8429 0.0281
-5.000 0.0266 0.02207 0.01451 -0.1259 0.8401 0.0277
-4.750 0.0477 0.02101 0.01329 -0.1245 0.8351 0.0280
-4.500 0.0710 0.02009 0.01224 -0.1234 0.8303 0.0288
-4.250 0.0965 0.01891 0.01102 -0.1229 0.8269 0.0304
-4.000 0.1249 0.01831 0.01039 -0.1231 0.8242 0.0362
-3.750 0.1410 0.01775 0.00992 -0.1213 0.8184 0.0428
-3.500 0.1630 0.01692 0.00916 -0.1205 0.8139 0.0645
-3.250 0.1860 0.01544 0.00841 -0.1205 0.8107 0.2117
-3.000 0.1990 0.01392 0.00871 -0.1183 0.8074 0.6459
-2.750 0.2140 0.01456 0.00943 -0.1150 0.8014 0.7309
-2.500 0.2364 0.01504 0.00981 -0.1129 0.7976 0.7653
-2.250 0.2596 0.01544 0.01010 -0.1108 0.7947 0.7876
-2.000 0.2766 0.01589 0.01051 -0.1077 0.7905 0.8052
-1.750 0.2909 0.01627 0.01085 -0.1044 0.7850 0.8202
-1.500 0.3112 0.01646 0.01095 -0.1020 0.7814 0.8345
-1.250 0.3353 0.01654 0.01092 -0.1004 0.7787 0.8478
-1.000 0.3458 0.01685 0.01122 -0.0966 0.7730 0.8613
-0.750 0.3562 0.01701 0.01136 -0.0921 0.7681 0.8779
-0.500 0.3744 0.01697 0.01126 -0.0889 0.7649 0.8941
-0.250 0.4030 0.01689 0.01106 -0.0887 0.7625 0.9044
0.000 0.4108 0.01707 0.01126 -0.0851 0.7553 0.9110
0.250 0.4374 0.01698 0.01110 -0.0852 0.7515 0.9161
0.500 0.4700 0.01682 0.01083 -0.0862 0.7487 0.9196
0.750 0.4908 0.01688 0.01087 -0.0852 0.7440 0.9236
1.000 0.5108 0.01693 0.01091 -0.0841 0.7383 0.9282
1.250 0.5418 0.01681 0.01071 -0.0850 0.7350 0.9314
1.500 0.5777 0.01663 0.01044 -0.0867 0.7324 0.9338
1.750 0.5910 0.01683 0.01069 -0.0845 0.7253 0.9382
2.000 0.6204 0.01672 0.01054 -0.0850 0.7210 0.9416
2.250 0.6564 0.01652 0.01028 -0.0867 0.7180 0.9442
2.500 0.6755 0.01664 0.01043 -0.0856 0.7117 0.9482
2.750 0.7039 0.01658 0.01038 -0.0860 0.7066 0.9516
3.000 0.7410 0.01637 0.01012 -0.0879 0.7032 0.9543
3.250 0.7633 0.01646 0.01023 -0.0873 0.6974 0.9588
3.500 0.7923 0.01641 0.01020 -0.0879 0.6915 0.9621
3.750 0.8325 0.01617 0.00993 -0.0904 0.6878 0.9641
4.000 0.8574 0.01627 0.01009 -0.0903 0.6808 0.9692
4.250 0.8907 0.01613 0.00995 -0.0917 0.6751 0.9729
4.500 0.9339 0.01585 0.00965 -0.0947 0.6712 0.9744
4.750 0.9585 0.01601 0.00992 -0.0948 0.6624 0.9798
5.000 0.9982 0.01576 0.00965 -0.0972 0.6574 0.9825
5.250 1.0292 0.01584 0.00983 -0.0985 0.6489 0.9876
5.500 1.0695 0.01561 0.00960 -0.1011 0.6427 0.9910
5.750 1.0986 0.01565 0.00975 -0.1020 0.6334 1.0000
6.000 1.1256 0.01543 0.00950 -0.1020 0.6268 1.0000
6.250 1.1358 0.01553 0.00970 -0.0992 0.6169 1.0000
6.500 1.1625 0.01547 0.00966 -0.0993 0.6081 1.0000
6.750 1.1894 0.01541 0.00964 -0.0995 0.5981 1.0000
7.000 1.2110 0.01549 0.00980 -0.0988 0.5863 1.0000
7.250 1.2350 0.01556 0.00992 -0.0985 0.5743 1.0000
7.500 1.2588 0.01564 0.01005 -0.0981 0.5613 1.0000
7.750 1.2812 0.01578 0.01022 -0.0976 0.5472 1.0000
8.000 1.3012 0.01598 0.01045 -0.0965 0.5318 1.0000
8.250 1.3178 0.01623 0.01071 -0.0949 0.5150 1.0000
8.500 1.3327 0.01656 0.01105 -0.0930 0.4971 1.0000
8.750 1.3465 0.01699 0.01142 -0.0909 0.4783 1.0000
9.000 1.3564 0.01754 0.01197 -0.0883 0.4582 1.0000
9.250 1.3651 0.01820 0.01259 -0.0857 0.4374 1.0000
9.500 1.3722 0.01900 0.01330 -0.0829 0.4163 1.0000
9.750 1.3771 0.01992 0.01420 -0.0799 0.3943 1.0000
10.000 1.3806 0.02099 0.01519 -0.0770 0.3729 1.0000
10.250 1.3835 0.02217 0.01634 -0.0741 0.3511 1.0000
10.500 1.3847 0.02352 0.01761 -0.0713 0.3298 1.0000
10.750 1.3864 0.02496 0.01900 -0.0687 0.3092 1.0000
11.000 1.3875 0.02652 0.02052 -0.0662 0.2887 1.0000
11.250 1.3874 0.02825 0.02218 -0.0638 0.2693 1.0000
11.500 1.3885 0.03000 0.02392 -0.0618 0.2501 1.0000
11.750 1.3888 0.03189 0.02578 -0.0598 0.2309 1.0000
12.000 1.3886 0.03391 0.02775 -0.0579 0.2131 1.0000
12.250 1.3876 0.03608 0.02987 -0.0562 0.1961 1.0000
12.500 1.3884 0.03821 0.03199 -0.0547 0.1793 1.0000
12.750 1.3885 0.04050 0.03426 -0.0534 0.1627 1.0000
13.000 1.3879 0.04293 0.03668 -0.0521 0.1471 1.0000
13.250 1.3867 0.04551 0.03924 -0.0510 0.1321 1.0000
13.500 1.3849 0.04826 0.04197 -0.0501 0.1179 1.0000
13.750 1.3824 0.05117 0.04487 -0.0492 0.1044 1.0000
14.000 1.3796 0.05422 0.04791 -0.0485 0.0919 1.0000
14.250 1.3766 0.05742 0.05110 -0.0480 0.0806 1.0000
14.500 1.3729 0.06080 0.05449 -0.0476 0.0708 1.0000
14.750 1.3674 0.06447 0.05816 -0.0473 0.0627 1.0000
15.000 1.3620 0.06827 0.06197 -0.0472 0.0558 1.0000
15.250 1.3595 0.07183 0.06562 -0.0473 0.0494 1.0000
15.500 1.3512 0.07618 0.06995 -0.0475 0.0447 1.0000
15.750 1.3504 0.07972 0.07363 -0.0479 0.0398 1.0000
16.000 1.3419 0.08425 0.07814 -0.0484 0.0363 1.0000
16.250 1.3412 0.08799 0.08205 -0.0491 0.0326 1.0000
16.500 1.3349 0.09242 0.08651 -0.0500 0.0299 1.0000
16.750 1.3321 0.09649 0.09072 -0.0508 0.0270 1.0000
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Polar data table (+)
Polar graphs
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