EPPLER 551 AIRFOIL (e551-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 551 AIRFOIL (e551-il) Reynolds number: 200,000 Max Cl/Cd: 72.4 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e551-il-200000.txt Download as CSV file: xf-e551-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 551 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6551 0.06340 0.05850 -0.0846 1.0000 0.0212
-12.750 -0.6636 0.05998 0.05500 -0.0846 1.0000 0.0210
-12.500 -0.6809 0.05645 0.05131 -0.0844 1.0000 0.0210
-12.250 -0.6911 0.05354 0.04831 -0.0835 1.0000 0.0209
-12.000 -0.7036 0.05094 0.04560 -0.0821 1.0000 0.0208
-11.750 -0.7197 0.04883 0.04339 -0.0795 1.0000 0.0207
-11.500 -0.7448 0.04773 0.04224 -0.0748 1.0000 0.0207
-11.250 -0.7625 0.04651 0.04097 -0.0713 0.9986 0.0206
-11.000 -0.7455 0.04272 0.03679 -0.0753 0.9919 0.0207
-10.750 -0.7245 0.03954 0.03323 -0.0784 0.9844 0.0209
-10.500 -0.7034 0.03694 0.03026 -0.0807 0.9757 0.0214
-10.250 -0.6651 0.03474 0.02805 -0.0830 0.9730 0.0221
-10.000 -0.6350 0.03328 0.02654 -0.0857 0.9662 0.0241
-9.750 -0.6015 0.03147 0.02448 -0.0877 0.9604 0.0251
-9.500 -0.5602 0.02984 0.02290 -0.0889 0.9587 0.0263
-9.250 -0.5239 0.02845 0.02152 -0.0911 0.9550 0.0282
-9.000 -0.4952 0.02702 0.02004 -0.0922 0.9471 0.0307
-8.750 -0.4600 0.02545 0.01849 -0.0959 0.9421 0.0344
-8.500 -0.4383 0.02373 0.01680 -0.0978 0.9308 0.0394
-8.250 -0.4192 0.02196 0.01499 -0.0994 0.9194 0.0450
-8.000 -0.3980 0.02040 0.01339 -0.1008 0.9093 0.0572
-7.750 -0.3895 0.01901 0.01208 -0.0996 0.8953 0.0730
-7.500 -0.3803 0.01768 0.01089 -0.0982 0.8827 0.1051
-7.250 -0.3731 0.01592 0.00955 -0.0969 0.8717 0.1829
-7.000 -0.3673 0.01419 0.00875 -0.0952 0.8609 0.3549
-6.750 -0.3432 0.01446 0.00905 -0.0944 0.8514 0.4214
-6.500 -0.3139 0.01490 0.00934 -0.0942 0.8437 0.4494
-6.250 -0.2878 0.01540 0.00975 -0.0934 0.8348 0.4667
-6.000 -0.2588 0.01581 0.01002 -0.0932 0.8274 0.4806
-5.750 -0.2330 0.01617 0.01022 -0.0926 0.8188 0.4931
-5.500 -0.2032 0.01666 0.01074 -0.0921 0.8113 0.5015
-5.250 -0.1771 0.01686 0.01078 -0.0916 0.8035 0.5115
-5.000 -0.1485 0.01730 0.01124 -0.0910 0.7960 0.5186
-4.750 -0.1211 0.01751 0.01130 -0.0908 0.7893 0.5286
-4.500 -0.0938 0.01813 0.01199 -0.0896 0.7812 0.5363
-4.250 -0.0655 0.01806 0.01169 -0.0899 0.7752 0.5448
-4.000 -0.0405 0.01807 0.01170 -0.0892 0.7668 0.5479
-3.750 -0.0121 0.01800 0.01154 -0.0892 0.7606 0.5512
-3.500 0.0142 0.01785 0.01128 -0.0892 0.7538 0.5548
-3.250 0.0410 0.01756 0.01083 -0.0896 0.7467 0.5589
-3.000 0.0699 0.01729 0.01038 -0.0901 0.7412 0.5620
-2.750 0.0949 0.01717 0.01027 -0.0897 0.7335 0.5642
-2.500 0.1233 0.01705 0.01005 -0.0899 0.7278 0.5666
-2.250 0.1506 0.01694 0.00987 -0.0901 0.7219 0.5691
-2.000 0.1773 0.01682 0.00968 -0.0901 0.7151 0.5724
-1.750 0.2068 0.01665 0.00935 -0.0908 0.7099 0.5759
-1.500 0.2332 0.01652 0.00914 -0.0909 0.7035 0.5786
-1.250 0.2604 0.01641 0.00901 -0.0910 0.6976 0.5806
-1.000 0.2899 0.01635 0.00887 -0.0914 0.6930 0.5829
-0.750 0.3155 0.01635 0.00887 -0.0912 0.6868 0.5859
-0.500 0.3431 0.01629 0.00877 -0.0913 0.6810 0.5892
-0.250 0.3733 0.01623 0.00858 -0.0920 0.6765 0.5924
0.000 0.3995 0.01622 0.00854 -0.0921 0.6708 0.5954
0.250 0.4263 0.01618 0.00852 -0.0921 0.6653 0.5977
0.500 0.4556 0.01616 0.00846 -0.0925 0.6609 0.6004
0.750 0.4823 0.01622 0.00853 -0.0925 0.6557 0.6037
1.000 0.5088 0.01626 0.00857 -0.0925 0.6503 0.6075
1.250 0.5382 0.01627 0.00850 -0.0930 0.6458 0.6113
1.500 0.5672 0.01629 0.00850 -0.0934 0.6417 0.6142
1.750 0.5914 0.01636 0.00867 -0.0930 0.6359 0.6171
2.000 0.6191 0.01641 0.00873 -0.0931 0.6313 0.6207
2.250 0.6494 0.01645 0.00872 -0.0937 0.6274 0.6249
2.500 0.6750 0.01659 0.00888 -0.0937 0.6222 0.6293
2.750 0.7005 0.01666 0.00904 -0.0934 0.6171 0.6329
3.000 0.7292 0.01671 0.00911 -0.0937 0.6129 0.6370
3.250 0.7584 0.01682 0.00920 -0.0941 0.6088 0.6418
3.500 0.7821 0.01697 0.00943 -0.0937 0.6030 0.6465
3.750 0.8090 0.01701 0.00955 -0.0936 0.5982 0.6505
4.000 0.8397 0.01708 0.00959 -0.0942 0.5943 0.6556
4.250 0.8628 0.01727 0.00989 -0.0937 0.5884 0.6617
4.500 0.8884 0.01733 0.01004 -0.0934 0.5830 0.6668
4.750 0.9186 0.01736 0.01007 -0.0939 0.5785 0.6730
5.000 0.9421 0.01755 0.01035 -0.0934 0.5726 0.6798
5.250 0.9668 0.01759 0.01051 -0.0929 0.5666 0.6854
5.500 0.9978 0.01761 0.01050 -0.0935 0.5619 0.6930
5.750 1.0187 0.01778 0.01085 -0.0924 0.5553 0.7000
6.000 1.0444 0.01782 0.01096 -0.0921 0.5492 0.7085
6.250 1.0739 0.01785 0.01101 -0.0924 0.5439 0.7174
6.500 1.0930 0.01798 0.01133 -0.0910 0.5363 0.7274
6.750 1.1214 0.01792 0.01130 -0.0911 0.5301 0.7374
7.000 1.1412 0.01804 0.01159 -0.0897 0.5225 0.7489
7.250 1.1665 0.01801 0.01163 -0.0893 0.5153 0.7619
7.500 1.1868 0.01806 0.01184 -0.0879 0.5076 0.7757
7.750 1.2088 0.01802 0.01191 -0.0868 0.4994 0.7921
8.000 1.2271 0.01806 0.01211 -0.0851 0.4910 0.8118
8.250 1.2459 0.01796 0.01213 -0.0832 0.4823 0.8351
8.500 1.2579 0.01796 0.01234 -0.0802 0.4731 0.8695
8.750 1.2792 0.01771 0.01223 -0.0788 0.4635 1.0000
9.000 1.2960 0.01790 0.01250 -0.0774 0.4515 1.0000
9.250 1.3111 0.01813 0.01276 -0.0755 0.4392 1.0000
9.500 1.3233 0.01835 0.01300 -0.0730 0.4262 1.0000
9.750 1.3316 0.01865 0.01330 -0.0699 0.4124 1.0000
10.000 1.3378 0.01906 0.01372 -0.0665 0.3972 1.0000
10.250 1.3421 0.01961 0.01428 -0.0631 0.3805 1.0000
10.500 1.3445 0.02033 0.01498 -0.0597 0.3621 1.0000
10.750 1.3449 0.02127 0.01586 -0.0563 0.3425 1.0000
11.000 1.3429 0.02247 0.01697 -0.0529 0.3225 1.0000
11.250 1.3403 0.02388 0.01832 -0.0498 0.3015 1.0000
11.500 1.3358 0.02555 0.01991 -0.0468 0.2814 1.0000
11.750 1.3302 0.02746 0.02173 -0.0441 0.2625 1.0000
12.000 1.3253 0.02950 0.02371 -0.0418 0.2445 1.0000
12.250 1.3206 0.03168 0.02585 -0.0398 0.2271 1.0000
12.500 1.3156 0.03402 0.02814 -0.0380 0.2106 1.0000
12.750 1.3108 0.03648 0.03056 -0.0365 0.1956 1.0000
13.000 1.3058 0.03908 0.03313 -0.0352 0.1812 1.0000
13.250 1.3009 0.04181 0.03582 -0.0341 0.1677 1.0000
13.500 1.2955 0.04470 0.03866 -0.0332 0.1552 1.0000
13.750 1.2912 0.04763 0.04157 -0.0326 0.1431 1.0000
14.000 1.2883 0.05055 0.04450 -0.0321 0.1315 1.0000
14.250 1.2852 0.05358 0.04754 -0.0318 0.1209 1.0000
14.500 1.2811 0.05680 0.05074 -0.0316 0.1114 1.0000
14.750 1.2764 0.06019 0.05409 -0.0316 0.1027 1.0000
15.000 1.2753 0.06329 0.05725 -0.0317 0.0940 1.0000
15.250 1.2716 0.06673 0.06067 -0.0318 0.0870 1.0000
15.500 1.2692 0.07014 0.06409 -0.0322 0.0802 1.0000
15.750 1.2675 0.07350 0.06749 -0.0325 0.0738 1.0000
16.000 1.2643 0.07713 0.07110 -0.0331 0.0686 1.0000
16.250 1.2637 0.08049 0.07454 -0.0336 0.0633 1.0000
16.500 1.2616 0.08410 0.07816 -0.0344 0.0590 1.0000
16.750 1.2609 0.08758 0.08171 -0.0350 0.0547 1.0000
17.000 1.2600 0.09116 0.08533 -0.0360 0.0512 1.0000
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Polar data table (+)
Polar graphs
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