EPPLER 549 AIRFOIL (e549-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 549 AIRFOIL (e549-il) Reynolds number: 500,000 Max Cl/Cd: 90.32 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e549-il-500000-n5.txt Download as CSV file: xf-e549-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 549 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.5892 0.13226 0.12948 -0.0384 1.0000 0.0040
-17.000 -0.6472 0.11398 0.11098 -0.0469 1.0000 0.0039
-16.750 -0.6717 0.10419 0.10104 -0.0519 1.0000 0.0039
-16.500 -0.6983 0.09437 0.09104 -0.0572 1.0000 0.0038
-16.250 -0.7215 0.08592 0.08241 -0.0617 1.0000 0.0038
-16.000 -0.7349 0.07977 0.07613 -0.0648 1.0000 0.0038
-15.750 -0.7483 0.07398 0.07020 -0.0675 1.0000 0.0038
-15.500 -0.7640 0.06822 0.06426 -0.0699 1.0000 0.0038
-15.250 -0.7762 0.06336 0.05922 -0.0716 1.0000 0.0039
-15.000 -0.7811 0.05975 0.05550 -0.0727 1.0000 0.0038
-14.750 -0.7874 0.05614 0.05176 -0.0734 1.0000 0.0038
-14.500 -0.7920 0.05291 0.04839 -0.0739 1.0000 0.0039
-14.250 -0.7951 0.05001 0.04536 -0.0740 1.0000 0.0039
-14.000 -0.7966 0.04743 0.04267 -0.0739 1.0000 0.0039
-13.750 -0.7975 0.04506 0.04019 -0.0735 1.0000 0.0039
-13.500 -0.7976 0.04285 0.03786 -0.0729 1.0000 0.0039
-13.250 -0.7959 0.04090 0.03582 -0.0722 1.0000 0.0040
-13.000 -0.7926 0.03920 0.03405 -0.0714 1.0000 0.0039
-12.750 -0.7908 0.03741 0.03215 -0.0703 1.0000 0.0040
-12.500 -0.7920 0.03546 0.03011 -0.0688 1.0000 0.0041
-12.250 -0.7923 0.03370 0.02829 -0.0672 1.0000 0.0042
-12.000 -0.7690 0.03204 0.02654 -0.0695 0.9957 0.0042
-11.750 -0.7567 0.03039 0.02483 -0.0697 0.9787 0.0042
-11.500 -0.7311 0.02882 0.02318 -0.0723 0.9586 0.0044
-11.250 -0.6945 0.02724 0.02150 -0.0771 0.9463 0.0046
-11.000 -0.6499 0.02566 0.01981 -0.0834 0.9354 0.0047
-10.750 -0.6019 0.02420 0.01821 -0.0903 0.9193 0.0049
-10.500 -0.5638 0.02300 0.01686 -0.0948 0.8977 0.0053
-10.250 -0.5411 0.02212 0.01582 -0.0959 0.8735 0.0053
-10.000 -0.5260 0.02135 0.01491 -0.0952 0.8536 0.0055
-9.750 -0.5137 0.02058 0.01400 -0.0940 0.8365 0.0058
-9.500 -0.5038 0.01973 0.01306 -0.0924 0.8217 0.0062
-9.250 -0.4921 0.01901 0.01225 -0.0909 0.8086 0.0064
-9.000 -0.4795 0.01837 0.01152 -0.0895 0.7966 0.0067
-8.750 -0.4678 0.01772 0.01078 -0.0879 0.7853 0.0072
-8.500 -0.4562 0.01708 0.01006 -0.0862 0.7745 0.0077
-8.250 -0.4460 0.01645 0.00935 -0.0842 0.7647 0.0082
-8.000 -0.4384 0.01591 0.00873 -0.0816 0.7548 0.0088
-7.750 -0.4276 0.01549 0.00824 -0.0793 0.7459 0.0097
-7.500 -0.4120 0.01510 0.00778 -0.0777 0.7378 0.0108
-7.250 -0.3954 0.01469 0.00734 -0.0763 0.7294 0.0134
-7.000 -0.3782 0.01429 0.00690 -0.0749 0.7216 0.0165
-6.750 -0.3592 0.01390 0.00650 -0.0739 0.7136 0.0213
-6.500 -0.3399 0.01353 0.00611 -0.0728 0.7067 0.0287
-6.250 -0.3197 0.01313 0.00575 -0.0719 0.6996 0.0396
-6.000 -0.2994 0.01274 0.00539 -0.0711 0.6927 0.0551
-5.750 -0.2784 0.01232 0.00503 -0.0703 0.6858 0.0773
-5.500 -0.2579 0.01185 0.00467 -0.0696 0.6787 0.1102
-5.250 -0.2378 0.01126 0.00427 -0.0688 0.6722 0.1606
-5.000 -0.2196 0.01042 0.00376 -0.0680 0.6657 0.2461
-4.750 -0.2043 0.00917 0.00307 -0.0670 0.6600 0.3900
-4.500 -0.1815 0.00870 0.00295 -0.0665 0.6536 0.4897
-4.250 -0.1541 0.00870 0.00291 -0.0665 0.6472 0.5127
-4.000 -0.1261 0.00873 0.00290 -0.0666 0.6411 0.5286
-3.750 -0.0980 0.00878 0.00288 -0.0667 0.6349 0.5417
-3.500 -0.0700 0.00889 0.00290 -0.0668 0.6294 0.5547
-3.250 -0.0418 0.00902 0.00301 -0.0668 0.6234 0.5670
-3.000 -0.0139 0.00910 0.00304 -0.0668 0.6173 0.5737
-2.750 0.0143 0.00910 0.00298 -0.0670 0.6117 0.5756
-2.500 0.0427 0.00910 0.00292 -0.0672 0.6059 0.5773
-2.250 0.0708 0.00912 0.00285 -0.0674 0.6002 0.5788
-2.000 0.0992 0.00911 0.00279 -0.0676 0.5950 0.5802
-1.750 0.1276 0.00912 0.00273 -0.0678 0.5895 0.5817
-1.500 0.1555 0.00915 0.00268 -0.0680 0.5841 0.5833
-1.250 0.1840 0.00916 0.00264 -0.0682 0.5785 0.5848
-1.000 0.2120 0.00917 0.00261 -0.0684 0.5725 0.5860
-0.750 0.2398 0.00920 0.00259 -0.0685 0.5673 0.5872
-0.500 0.2681 0.00920 0.00258 -0.0687 0.5620 0.5884
-0.250 0.2960 0.00923 0.00258 -0.0689 0.5567 0.5896
0.000 0.3238 0.00927 0.00258 -0.0690 0.5521 0.5910
0.250 0.3521 0.00930 0.00260 -0.0692 0.5475 0.5926
0.500 0.3801 0.00934 0.00261 -0.0694 0.5428 0.5942
0.750 0.4078 0.00939 0.00263 -0.0695 0.5384 0.5958
1.000 0.4359 0.00943 0.00266 -0.0697 0.5342 0.5972
1.250 0.4640 0.00947 0.00269 -0.0699 0.5298 0.5987
1.500 0.4917 0.00953 0.00272 -0.0701 0.5255 0.6001
1.750 0.5192 0.00960 0.00277 -0.0701 0.5216 0.6014
2.000 0.5471 0.00962 0.00282 -0.0703 0.5173 0.6027
2.250 0.5747 0.00967 0.00288 -0.0704 0.5129 0.6041
2.500 0.6020 0.00974 0.00296 -0.0705 0.5090 0.6057
2.750 0.6294 0.00981 0.00304 -0.0706 0.5051 0.6075
3.000 0.6570 0.00987 0.00312 -0.0707 0.5007 0.6093
3.250 0.6842 0.00994 0.00321 -0.0708 0.4964 0.6111
3.500 0.7111 0.01004 0.00330 -0.0707 0.4924 0.6129
3.750 0.7385 0.01012 0.00339 -0.0708 0.4887 0.6146
4.000 0.7659 0.01019 0.00350 -0.0709 0.4848 0.6162
4.250 0.7925 0.01027 0.00361 -0.0709 0.4804 0.6178
4.500 0.8185 0.01038 0.00373 -0.0707 0.4754 0.6195
4.750 0.8449 0.01045 0.00385 -0.0707 0.4685 0.6213
5.000 0.8699 0.01058 0.00398 -0.0703 0.4615 0.6232
5.250 0.8961 0.01067 0.00412 -0.0702 0.4553 0.6254
5.500 0.9210 0.01080 0.00427 -0.0698 0.4477 0.6278
5.750 0.9462 0.01092 0.00442 -0.0696 0.4400 0.6301
6.000 0.9705 0.01108 0.00458 -0.0691 0.4320 0.6323
6.250 0.9950 0.01120 0.00475 -0.0687 0.4234 0.6343
6.500 1.0179 0.01137 0.00495 -0.0680 0.4143 0.6364
6.750 1.0408 0.01154 0.00514 -0.0673 0.4029 0.6387
7.000 1.0622 0.01176 0.00536 -0.0664 0.3895 0.6412
7.250 1.0817 0.01203 0.00562 -0.0651 0.3735 0.6438
7.500 1.0987 0.01236 0.00590 -0.0634 0.3557 0.6465
7.750 1.1126 0.01272 0.00621 -0.0611 0.3330 0.6489
8.000 1.1208 0.01325 0.00664 -0.0578 0.3040 0.6515
8.250 1.1292 0.01387 0.00718 -0.0548 0.2839 0.6545
8.500 1.1405 0.01442 0.00770 -0.0523 0.2705 0.6579
8.750 1.1527 0.01495 0.00823 -0.0501 0.2575 0.6614
9.000 1.1649 0.01551 0.00878 -0.0479 0.2442 0.6648
9.250 1.1750 0.01614 0.00941 -0.0455 0.2260 0.6684
9.500 1.1812 0.01697 0.01017 -0.0428 0.2056 0.6722
9.750 1.1860 0.01792 0.01106 -0.0400 0.1862 0.6762
10.250 1.1960 0.01999 0.01307 -0.0350 0.1556 0.6844
10.500 1.2005 0.02115 0.01422 -0.0328 0.1413 0.6892
10.750 1.2065 0.02231 0.01538 -0.0308 0.1303 0.6942
11.000 1.2108 0.02363 0.01669 -0.0289 0.1186 0.6992
11.250 1.2153 0.02500 0.01807 -0.0271 0.1086 0.7052
11.750 1.2246 0.02791 0.02103 -0.0241 0.0893 0.7186
12.000 1.2276 0.02958 0.02272 -0.0226 0.0803 0.7263
12.250 1.2303 0.03132 0.02448 -0.0213 0.0723 0.7346
12.500 1.2349 0.03298 0.02620 -0.0202 0.0655 0.7437
12.750 1.2379 0.03481 0.02808 -0.0191 0.0596 0.7541
13.000 1.2414 0.03667 0.02999 -0.0182 0.0535 0.7658
13.250 1.2445 0.03860 0.03199 -0.0174 0.0486 0.7799
13.500 1.2484 0.04049 0.03400 -0.0166 0.0445 0.7983
13.750 1.2505 0.04253 0.03615 -0.0158 0.0407 0.8240
14.000 1.2541 0.04437 0.03826 -0.0150 0.0369 0.9021
14.500 1.2653 0.04907 0.04308 -0.0159 0.0302 1.0000
14.750 1.2672 0.05160 0.04563 -0.0158 0.0273 1.0000
15.000 1.2706 0.05403 0.04811 -0.0158 0.0250 1.0000
15.250 1.2731 0.05662 0.05074 -0.0159 0.0227 1.0000
15.500 1.2746 0.05938 0.05354 -0.0161 0.0207 1.0000
15.750 1.2778 0.06198 0.05621 -0.0164 0.0190 1.0000
16.000 1.2782 0.06497 0.05924 -0.0168 0.0170 1.0000
16.250 1.2802 0.06785 0.06218 -0.0172 0.0160 1.0000
16.500 1.2819 0.07080 0.06519 -0.0178 0.0144 1.0000
16.750 1.2815 0.07407 0.06850 -0.0185 0.0130 1.0000
17.000 1.2827 0.07720 0.07172 -0.0192 0.0122 1.0000
17.250 1.2836 0.08042 0.07502 -0.0200 0.0114 1.0000
17.500 1.2830 0.08390 0.07856 -0.0210 0.0104 1.0000
17.750 1.2817 0.08755 0.08227 -0.0221 0.0098 1.0000
18.000 1.2821 0.09100 0.08581 -0.0232 0.0092 1.0000
18.250 1.2811 0.09468 0.08957 -0.0245 0.0084 1.0000
18.500 1.2794 0.09855 0.09354 -0.0259 0.0081 1.0000
18.750 1.2761 0.10271 0.09776 -0.0274 0.0073 1.0000
19.000 1.2744 0.10668 0.10183 -0.0290 0.0071 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 549 AIRFOIL (e549-il)