EPPLER 549 AIRFOIL (e549-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 549 AIRFOIL (e549-il) Reynolds number: 200,000 Max Cl/Cd: 66.67 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e549-il-200000.txt Download as CSV file: xf-e549-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.2738 0.12914 0.12581 -0.0510 1.0000 0.0531
-13.750 -0.2696 0.12683 0.12351 -0.0511 1.0000 0.0542
-13.500 -0.4002 0.12508 0.12148 -0.0525 1.0000 0.0522
-13.250 -0.3907 0.12300 0.11941 -0.0517 1.0000 0.0531
-12.750 -0.3793 0.08505 0.08170 -0.0694 1.0000 0.0324
-12.500 -0.4058 0.07757 0.07416 -0.0723 1.0000 0.0317
-12.250 -0.4372 0.07036 0.06687 -0.0748 1.0000 0.0313
-12.000 -0.4651 0.06444 0.06087 -0.0760 1.0000 0.0308
-11.750 -0.5435 0.05394 0.04986 -0.0767 1.0000 0.0265
-11.500 -0.5639 0.05027 0.04614 -0.0750 1.0000 0.0262
-11.250 -0.5891 0.04815 0.04400 -0.0714 1.0000 0.0260
-11.000 -0.6108 0.04629 0.04212 -0.0685 0.9983 0.0257
-10.750 -0.7220 0.05725 0.05252 -0.0624 0.9970 0.0270
-10.500 -0.7034 0.05086 0.04607 -0.0654 0.9932 0.0252
-10.250 -0.7138 0.04430 0.03844 -0.0664 0.9783 0.0216
-10.000 -0.6892 0.04007 0.03393 -0.0686 0.9726 0.0213
-9.750 -0.6645 0.03669 0.03019 -0.0702 0.9655 0.0213
-9.500 -0.6333 0.03384 0.02698 -0.0722 0.9601 0.0214
-9.250 -0.5954 0.03144 0.02427 -0.0748 0.9573 0.0217
-9.000 -0.5558 0.02915 0.02203 -0.0771 0.9537 0.0233
-8.750 -0.5178 0.02779 0.02060 -0.0796 0.9482 0.0254
-8.500 -0.4738 0.02636 0.01900 -0.0824 0.9449 0.0271
-8.250 -0.4315 0.02464 0.01741 -0.0845 0.9424 0.0297
-8.000 -0.4003 0.02347 0.01619 -0.0859 0.9323 0.0327
-7.750 -0.3721 0.02197 0.01474 -0.0878 0.9225 0.0382
-7.500 -0.3503 0.02049 0.01323 -0.0889 0.9106 0.0457
-7.250 -0.3429 0.01929 0.01198 -0.0871 0.8955 0.0557
-7.000 -0.3386 0.01829 0.01101 -0.0843 0.8810 0.0750
-6.750 -0.3384 0.01712 0.01005 -0.0809 0.8671 0.1111
-6.500 -0.3396 0.01575 0.00911 -0.0775 0.8545 0.1892
-6.250 -0.3455 0.01387 0.00805 -0.0737 0.8432 0.3481
-6.000 -0.3303 0.01383 0.00869 -0.0712 0.8344 0.5185
-5.750 -0.3060 0.01443 0.00915 -0.0700 0.8250 0.5553
-5.500 -0.2756 0.01535 0.00998 -0.0692 0.8179 0.5759
-5.250 -0.2494 0.01603 0.01058 -0.0681 0.8088 0.5897
-5.000 -0.2203 0.01661 0.01102 -0.0675 0.8021 0.6026
-4.750 -0.1921 0.01746 0.01186 -0.0663 0.7935 0.6118
-4.500 -0.1628 0.01800 0.01228 -0.0656 0.7867 0.6208
-4.250 -0.1365 0.01856 0.01279 -0.0645 0.7783 0.6296
-4.000 -0.1041 0.01978 0.01399 -0.0630 0.7718 0.6388
-3.750 -0.0795 0.02028 0.01442 -0.0617 0.7642 0.6503
-3.500 -0.0501 0.02065 0.01471 -0.0609 0.7573 0.6535
-3.250 -0.0249 0.02054 0.01450 -0.0605 0.7502 0.6574
-3.000 -0.0043 0.01976 0.01353 -0.0611 0.7427 0.6646
-2.750 0.0235 0.01974 0.01342 -0.0608 0.7368 0.6663
-2.500 0.0485 0.01967 0.01330 -0.0602 0.7293 0.6684
-2.250 0.0764 0.01952 0.01303 -0.0604 0.7237 0.6709
-2.000 0.0998 0.01926 0.01272 -0.0602 0.7163 0.6741
-1.750 0.1262 0.01883 0.01214 -0.0610 0.7103 0.6781
-1.500 0.1521 0.01848 0.01167 -0.0615 0.7043 0.6808
-1.250 0.1777 0.01838 0.01155 -0.0612 0.6976 0.6824
-1.000 0.2063 0.01827 0.01133 -0.0615 0.6927 0.6841
-0.750 0.2310 0.01815 0.01120 -0.0613 0.6861 0.6859
-0.500 0.2581 0.01801 0.01100 -0.0616 0.6805 0.6881
-0.250 0.2873 0.01787 0.01074 -0.0623 0.6759 0.6907
0.000 0.3121 0.01768 0.01054 -0.0625 0.6692 0.6932
0.250 0.3410 0.01747 0.01022 -0.0635 0.6641 0.6956
0.500 0.3691 0.01741 0.01010 -0.0638 0.6598 0.6972
0.750 0.3935 0.01740 0.01014 -0.0634 0.6537 0.6990
1.000 0.4213 0.01734 0.01005 -0.0636 0.6486 0.7008
1.250 0.4496 0.01730 0.00996 -0.0640 0.6436 0.7026
1.500 0.4748 0.01725 0.00993 -0.0639 0.6372 0.7046
1.750 0.5040 0.01716 0.00978 -0.0646 0.6322 0.7069
2.000 0.5322 0.01716 0.00974 -0.0652 0.6277 0.7095
2.250 0.5581 0.01717 0.00977 -0.0654 0.6224 0.7120
2.500 0.5856 0.01717 0.00978 -0.0655 0.6181 0.7137
2.750 0.6156 0.01722 0.00979 -0.0662 0.6146 0.7156
3.000 0.6389 0.01731 0.00998 -0.0657 0.6090 0.7176
3.250 0.6660 0.01731 0.00999 -0.0659 0.6037 0.7199
3.500 0.6970 0.01731 0.00993 -0.0667 0.5994 0.7224
3.750 0.7211 0.01742 0.01013 -0.0666 0.5940 0.7253
4.000 0.7478 0.01749 0.01024 -0.0668 0.5892 0.7280
4.250 0.7767 0.01753 0.01028 -0.0671 0.5853 0.7302
4.500 0.8017 0.01765 0.01048 -0.0669 0.5801 0.7326
4.750 0.8266 0.01776 0.01068 -0.0667 0.5748 0.7353
5.000 0.8558 0.01782 0.01075 -0.0673 0.5707 0.7383
5.250 0.8834 0.01795 0.01090 -0.0676 0.5658 0.7415
5.500 0.9067 0.01800 0.01107 -0.0671 0.5591 0.7442
5.750 0.9367 0.01795 0.01099 -0.0675 0.5536 0.7470
6.000 0.9576 0.01806 0.01125 -0.0665 0.5463 0.7505
6.250 0.9853 0.01805 0.01127 -0.0667 0.5401 0.7544
6.500 1.0107 0.01814 0.01141 -0.0666 0.5334 0.7583
6.750 1.0342 0.01812 0.01149 -0.0659 0.5260 0.7613
7.000 1.0594 0.01815 0.01158 -0.0655 0.5191 0.7650
7.250 1.0820 0.01817 0.01171 -0.0648 0.5109 0.7693
7.500 1.1067 0.01821 0.01179 -0.0644 0.5030 0.7739
7.750 1.1284 0.01816 0.01185 -0.0634 0.4942 0.7778
8.000 1.1476 0.01821 0.01201 -0.0620 0.4846 0.7829
8.250 1.1718 0.01820 0.01201 -0.0615 0.4751 0.7889
8.500 1.1867 0.01821 0.01219 -0.0592 0.4639 0.7940
8.750 1.2026 0.01829 0.01238 -0.0573 0.4524 0.8004
9.000 1.2178 0.01835 0.01253 -0.0552 0.4399 0.8069
9.250 1.2300 0.01845 0.01272 -0.0526 0.4267 0.8141
9.500 1.2386 0.01859 0.01293 -0.0494 0.4124 0.8225
9.750 1.2429 0.01881 0.01323 -0.0455 0.3970 0.8322
10.000 1.2460 0.01916 0.01366 -0.0415 0.3804 0.8438
10.250 1.2479 0.01964 0.01420 -0.0377 0.3623 0.8584
10.500 1.2474 0.02026 0.01486 -0.0337 0.3430 0.8791
10.750 1.2452 0.02095 0.01565 -0.0297 0.3226 0.9239
11.000 1.2482 0.02218 0.01679 -0.0280 0.2993 1.0000
11.250 1.2474 0.02378 0.01824 -0.0259 0.2804 1.0000
11.500 1.2471 0.02544 0.01982 -0.0239 0.2627 1.0000
11.750 1.2469 0.02718 0.02152 -0.0220 0.2442 1.0000
12.000 1.2451 0.02909 0.02340 -0.0203 0.2248 1.0000
12.250 1.2406 0.03129 0.02552 -0.0186 0.2072 1.0000
12.500 1.2360 0.03365 0.02781 -0.0172 0.1903 1.0000
12.750 1.2314 0.03613 0.03023 -0.0159 0.1752 1.0000
13.000 1.2269 0.03872 0.03278 -0.0148 0.1611 1.0000
13.250 1.2225 0.04142 0.03544 -0.0140 0.1480 1.0000
13.500 1.2175 0.04428 0.03825 -0.0133 0.1359 1.0000
13.750 1.2144 0.04711 0.04106 -0.0128 0.1243 1.0000
14.000 1.2123 0.04995 0.04392 -0.0125 0.1134 1.0000
14.250 1.2096 0.05291 0.04689 -0.0123 0.1037 1.0000
14.500 1.2048 0.05618 0.05009 -0.0122 0.0955 1.0000
14.750 1.2039 0.05916 0.05312 -0.0123 0.0871 1.0000
15.000 1.2018 0.06232 0.05629 -0.0125 0.0799 1.0000
15.250 1.1989 0.06565 0.05961 -0.0128 0.0737 1.0000
15.500 1.1981 0.06883 0.06285 -0.0131 0.0675 1.0000
15.750 1.1957 0.07225 0.06625 -0.0137 0.0625 1.0000
16.000 1.1952 0.07547 0.06954 -0.0141 0.0577 1.0000
16.250 1.1945 0.07886 0.07299 -0.0149 0.0535 1.0000
16.500 1.1929 0.08222 0.07632 -0.0154 0.0496 1.0000
16.750 1.1935 0.08559 0.07984 -0.0163 0.0462 1.0000
17.000 1.1921 0.08920 0.08347 -0.0173 0.0431 1.0000
17.250 1.1925 0.09243 0.08672 -0.0179 0.0401 1.0000
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Polar data table (+)
Polar graphs
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