EPPLER 552 AIRFOIL (e552-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 552 AIRFOIL (e552-il) Reynolds number: 200,000 Max Cl/Cd: 70.3 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e552-il-200000.txt Download as CSV file: xf-e552-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 552 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.3325 0.11264 0.10930 -0.0509 1.0000 0.0349
-13.750 -0.3289 0.11048 0.10718 -0.0508 1.0000 0.0341
-13.500 -0.5854 0.08241 0.07827 -0.0685 1.0000 0.0291
-13.250 -0.5731 0.07958 0.07550 -0.0677 1.0000 0.0281
-13.000 -0.5930 0.07396 0.06978 -0.0704 1.0000 0.0278
-12.750 -0.6112 0.06886 0.06457 -0.0725 1.0000 0.0273
-12.500 -0.6322 0.06379 0.05935 -0.0742 1.0000 0.0268
-12.250 -0.6532 0.05903 0.05440 -0.0754 1.0000 0.0262
-12.000 -0.6809 0.05393 0.04903 -0.0760 1.0000 0.0253
-11.750 -0.7304 0.04868 0.04317 -0.0751 1.0000 0.0240
-11.500 -0.7447 0.04692 0.04122 -0.0730 1.0000 0.0237
-11.250 -0.7574 0.04555 0.03973 -0.0698 1.0000 0.0236
-11.000 -0.7615 0.04347 0.03753 -0.0670 1.0000 0.0235
-10.750 -0.7632 0.04135 0.03532 -0.0643 1.0000 0.0234
-10.250 -0.7344 0.03658 0.03015 -0.0646 0.9923 0.0234
-10.000 -0.6974 0.03353 0.02689 -0.0672 0.9841 0.0238
-9.750 -0.6589 0.03136 0.02473 -0.0691 0.9730 0.0247
-9.500 -0.6195 0.02966 0.02300 -0.0715 0.9586 0.0258
-9.250 -0.5755 0.02806 0.02132 -0.0746 0.9448 0.0277
-9.000 -0.5279 0.02633 0.01957 -0.0788 0.9292 0.0302
-8.750 -0.4765 0.02475 0.01786 -0.0852 0.9054 0.0352
-8.500 -0.4408 0.02275 0.01584 -0.0897 0.8742 0.0405
-8.250 -0.4283 0.02123 0.01418 -0.0900 0.8434 0.0465
-8.000 -0.4189 0.02016 0.01298 -0.0887 0.8194 0.0547
-7.750 -0.4105 0.01909 0.01184 -0.0870 0.8005 0.0669
-7.500 -0.4008 0.01799 0.01074 -0.0854 0.7840 0.0887
-7.250 -0.3926 0.01659 0.00956 -0.0839 0.7691 0.1342
-7.000 -0.3865 0.01467 0.00824 -0.0826 0.7557 0.2482
-6.750 -0.3702 0.01406 0.00824 -0.0815 0.7437 0.3980
-6.500 -0.3434 0.01450 0.00851 -0.0810 0.7334 0.4361
-6.250 -0.3166 0.01500 0.00889 -0.0804 0.7224 0.4570
-6.000 -0.2892 0.01549 0.00925 -0.0799 0.7132 0.4718
-5.750 -0.2618 0.01590 0.00953 -0.0794 0.7043 0.4839
-5.500 -0.2348 0.01629 0.00975 -0.0790 0.6958 0.4963
-5.250 -0.2065 0.01687 0.01034 -0.0782 0.6879 0.5052
-5.000 -0.1795 0.01711 0.01046 -0.0779 0.6803 0.5143
-4.750 -0.1516 0.01750 0.01079 -0.0773 0.6731 0.5212
-4.500 -0.1242 0.01784 0.01103 -0.0769 0.6672 0.5309
-4.250 -0.0968 0.01841 0.01163 -0.0760 0.6604 0.5395
-4.000 -0.0695 0.01836 0.01140 -0.0761 0.6551 0.5462
-3.750 -0.0421 0.01840 0.01140 -0.0759 0.6496 0.5493
-3.500 -0.0148 0.01832 0.01125 -0.0759 0.6437 0.5527
-3.250 0.0134 0.01814 0.01089 -0.0763 0.6389 0.5566
-3.000 0.0412 0.01789 0.01046 -0.0770 0.6341 0.5608
-2.750 0.0684 0.01776 0.01032 -0.0769 0.6291 0.5629
-2.500 0.0965 0.01768 0.01016 -0.0771 0.6249 0.5651
-2.250 0.1253 0.01766 0.01003 -0.0774 0.6214 0.5679
-2.000 0.1526 0.01757 0.00992 -0.0776 0.6169 0.5710
-1.750 0.1807 0.01744 0.00969 -0.0781 0.6124 0.5740
-1.500 0.2097 0.01731 0.00941 -0.0787 0.6085 0.5772
-1.250 0.2383 0.01730 0.00934 -0.0790 0.6054 0.5794
-1.000 0.2654 0.01730 0.00938 -0.0790 0.6017 0.5819
-0.750 0.2930 0.01730 0.00937 -0.0792 0.5980 0.5844
-0.500 0.3214 0.01728 0.00930 -0.0796 0.5945 0.5873
-0.250 0.3507 0.01726 0.00918 -0.0801 0.5913 0.5905
0.000 0.3802 0.01732 0.00912 -0.0807 0.5884 0.5939
0.250 0.4063 0.01735 0.00925 -0.0806 0.5849 0.5964
0.500 0.4337 0.01742 0.00936 -0.0807 0.5815 0.5991
0.750 0.4618 0.01747 0.00940 -0.0810 0.5784 0.6021
1.000 0.4910 0.01752 0.00939 -0.0815 0.5755 0.6056
1.250 0.5212 0.01766 0.00940 -0.0822 0.5730 0.6093
1.500 0.5467 0.01775 0.00963 -0.0820 0.5697 0.6121
1.750 0.5731 0.01789 0.00985 -0.0820 0.5664 0.6154
2.000 0.6007 0.01800 0.00998 -0.0822 0.5632 0.6192
2.250 0.6296 0.01809 0.01004 -0.0826 0.5603 0.6233
2.500 0.6591 0.01823 0.01014 -0.0831 0.5580 0.6271
2.750 0.6851 0.01843 0.01044 -0.0830 0.5550 0.6303
3.000 0.7105 0.01863 0.01075 -0.0828 0.5514 0.6343
3.250 0.7377 0.01881 0.01096 -0.0830 0.5481 0.6393
3.500 0.7658 0.01892 0.01110 -0.0833 0.5452 0.6439
3.750 0.7945 0.01905 0.01126 -0.0835 0.5426 0.6483
4.000 0.8211 0.01933 0.01159 -0.0836 0.5395 0.6535
4.250 0.8456 0.01958 0.01195 -0.0834 0.5354 0.6589
4.500 0.8715 0.01973 0.01221 -0.0832 0.5317 0.6635
4.750 0.9000 0.01982 0.01233 -0.0834 0.5285 0.6694
5.000 0.9303 0.01996 0.01243 -0.0840 0.5257 0.6759
5.250 0.9516 0.02026 0.01296 -0.0831 0.5212 0.6818
5.500 0.9769 0.02047 0.01325 -0.0830 0.5168 0.6896
5.750 1.0046 0.02050 0.01336 -0.0830 0.5132 0.6962
6.000 1.0355 0.02057 0.01341 -0.0836 0.5101 0.7047
6.250 1.0556 0.02087 0.01393 -0.0825 0.5049 0.7121
6.500 1.0809 0.02096 0.01412 -0.0822 0.4999 0.7219
6.750 1.1101 0.02084 0.01406 -0.0824 0.4959 0.7312
7.000 1.1350 0.02100 0.01432 -0.0820 0.4912 0.7423
7.250 1.1564 0.02114 0.01464 -0.0811 0.4853 0.7549
7.500 1.1842 0.02099 0.01457 -0.0809 0.4808 0.7680
7.750 1.2092 0.02100 0.01469 -0.0804 0.4757 0.7825
8.000 1.2284 0.02104 0.01493 -0.0790 0.4691 0.7993
8.250 1.2562 0.02074 0.01468 -0.0787 0.4640 0.8195
8.500 1.2721 0.02078 0.01496 -0.0765 0.4574 0.8447
8.750 1.2897 0.02050 0.01485 -0.0744 0.4510 0.8827
9.000 1.3148 0.02016 0.01464 -0.0737 0.4445 1.0000
9.250 1.3377 0.02020 0.01477 -0.0733 0.4362 1.0000
9.500 1.3623 0.02016 0.01474 -0.0730 0.4284 1.0000
9.750 1.3825 0.02013 0.01478 -0.0719 0.4192 1.0000
10.000 1.3990 0.02023 0.01497 -0.0702 0.4092 1.0000
10.250 1.4168 0.02023 0.01499 -0.0686 0.3989 1.0000
10.500 1.4299 0.02034 0.01515 -0.0664 0.3868 1.0000
10.750 1.4361 0.02063 0.01552 -0.0631 0.3734 1.0000
11.000 1.4403 0.02106 0.01598 -0.0596 0.3589 1.0000
11.250 1.4424 0.02170 0.01660 -0.0562 0.3431 1.0000
11.500 1.4411 0.02264 0.01751 -0.0527 0.3258 1.0000
11.750 1.4371 0.02393 0.01877 -0.0494 0.3077 1.0000
12.000 1.4307 0.02561 0.02039 -0.0464 0.2901 1.0000
12.250 1.4219 0.02769 0.02241 -0.0438 0.2729 1.0000
12.500 1.4124 0.03011 0.02477 -0.0417 0.2568 1.0000
12.750 1.4021 0.03283 0.02744 -0.0400 0.2413 1.0000
13.000 1.3922 0.03574 0.03032 -0.0386 0.2267 1.0000
13.250 1.3824 0.03882 0.03337 -0.0376 0.2129 1.0000
13.500 1.3728 0.04203 0.03657 -0.0368 0.1997 1.0000
13.750 1.3640 0.04529 0.03981 -0.0363 0.1874 1.0000
14.000 1.3551 0.04870 0.04320 -0.0359 0.1756 1.0000
14.250 1.3462 0.05223 0.04668 -0.0357 0.1648 1.0000
14.500 1.3391 0.05575 0.05019 -0.0357 0.1537 1.0000
14.750 1.3336 0.05921 0.05367 -0.0359 0.1432 1.0000
15.000 1.3277 0.06281 0.05725 -0.0362 0.1334 1.0000
15.250 1.3206 0.06660 0.06098 -0.0366 0.1247 1.0000
15.500 1.3174 0.07013 0.06457 -0.0372 0.1153 1.0000
15.750 1.3129 0.07386 0.06829 -0.0378 0.1070 1.0000
16.000 1.3073 0.07775 0.07213 -0.0386 0.0996 1.0000
16.250 1.3051 0.08138 0.07584 -0.0394 0.0919 1.0000
16.500 1.3001 0.08530 0.07967 -0.0402 0.0856 1.0000
16.750 1.2986 0.08900 0.08351 -0.0412 0.0792 1.0000
17.000 1.2945 0.09290 0.08733 -0.0422 0.0736 1.0000
17.250 1.2932 0.09669 0.09125 -0.0434 0.0683 1.0000
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Polar data table (+)
Polar graphs
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