EPPLER 543 AIRFOIL (e543-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 543 AIRFOIL (e543-il) Reynolds number: 500,000 Max Cl/Cd: 82.66 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e543-il-500000-n5.txt Download as CSV file: xf-e543-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 543 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6232 0.08053 0.07789 -0.0649 1.0000 0.0039
-14.250 -0.6651 0.06861 0.06570 -0.0717 1.0000 0.0039
-14.000 -0.6844 0.06272 0.05966 -0.0740 1.0000 0.0039
-13.750 -0.7164 0.05604 0.05271 -0.0751 1.0000 0.0039
-13.500 -0.7449 0.05060 0.04701 -0.0745 1.0000 0.0038
-13.250 -0.7601 0.04705 0.04326 -0.0732 1.0000 0.0038
-13.000 -0.7670 0.04458 0.04064 -0.0718 1.0000 0.0039
-12.750 -0.7717 0.04245 0.03838 -0.0701 1.0000 0.0040
-12.500 -0.7810 0.03985 0.03558 -0.0677 1.0000 0.0040
-12.250 -0.7852 0.03704 0.03252 -0.0660 0.9993 0.0040
-12.000 -0.7710 0.03495 0.03026 -0.0669 0.9923 0.0041
-11.750 -0.7627 0.03282 0.02792 -0.0662 0.9760 0.0041
-11.500 -0.7417 0.03073 0.02561 -0.0678 0.9578 0.0042
-11.250 -0.7096 0.02876 0.02341 -0.0714 0.9466 0.0043
-11.000 -0.6701 0.02687 0.02128 -0.0761 0.9379 0.0044
-10.750 -0.6254 0.02531 0.01951 -0.0816 0.9270 0.0046
-10.250 -0.5455 0.02297 0.01671 -0.0898 0.8892 0.0050
-10.000 -0.5247 0.02197 0.01555 -0.0898 0.8691 0.0052
-9.750 -0.5081 0.02118 0.01463 -0.0888 0.8524 0.0053
-9.500 -0.4918 0.02055 0.01389 -0.0877 0.8381 0.0055
-9.250 -0.4756 0.01998 0.01321 -0.0864 0.8254 0.0056
-8.750 -0.4446 0.01880 0.01184 -0.0834 0.8023 0.0059
-8.500 -0.4287 0.01827 0.01122 -0.0820 0.7925 0.0059
-8.250 -0.4130 0.01773 0.01060 -0.0805 0.7833 0.0062
-8.000 -0.3967 0.01724 0.01002 -0.0790 0.7751 0.0065
-7.750 -0.3803 0.01678 0.00947 -0.0776 0.7669 0.0068
-7.500 -0.3632 0.01636 0.00898 -0.0762 0.7594 0.0069
-7.250 -0.3476 0.01586 0.00844 -0.0745 0.7515 0.0077
-7.000 -0.3308 0.01547 0.00797 -0.0731 0.7442 0.0083
-6.750 -0.3134 0.01510 0.00754 -0.0717 0.7371 0.0090
-6.500 -0.2973 0.01470 0.00710 -0.0700 0.7308 0.0107
-6.250 -0.2811 0.01429 0.00668 -0.0684 0.7246 0.0137
-6.000 -0.2651 0.01393 0.00629 -0.0668 0.7185 0.0176
-5.750 -0.2501 0.01354 0.00590 -0.0649 0.7128 0.0249
-5.500 -0.2376 0.01310 0.00553 -0.0626 0.7066 0.0394
-5.250 -0.2271 0.01273 0.00519 -0.0599 0.7009 0.0557
-5.000 -0.2193 0.01235 0.00492 -0.0566 0.6956 0.0815
-4.750 -0.2082 0.01190 0.00461 -0.0540 0.6905 0.1205
-4.500 -0.1979 0.01137 0.00429 -0.0513 0.6856 0.1762
-4.250 -0.1899 0.01067 0.00391 -0.0483 0.6811 0.2583
-4.000 -0.1851 0.00967 0.00340 -0.0449 0.6762 0.3806
-3.750 -0.1846 0.00823 0.00276 -0.0408 0.6714 0.5698
-3.250 -0.1343 0.00832 0.00306 -0.0397 0.6632 0.6809
-3.000 -0.1065 0.00851 0.00319 -0.0397 0.6591 0.6967
-2.750 -0.0784 0.00881 0.00347 -0.0396 0.6551 0.7081
-2.500 -0.0503 0.00913 0.00374 -0.0394 0.6514 0.7169
-2.250 -0.0221 0.00937 0.00394 -0.0395 0.6475 0.7239
-2.000 0.0058 0.00936 0.00385 -0.0397 0.6435 0.7265
-1.750 0.0338 0.00932 0.00372 -0.0401 0.6399 0.7276
-1.500 0.0619 0.00931 0.00365 -0.0403 0.6365 0.7284
-1.250 0.0901 0.00930 0.00360 -0.0406 0.6332 0.7292
-1.000 0.1184 0.00928 0.00355 -0.0409 0.6294 0.7299
-0.750 0.1466 0.00927 0.00350 -0.0412 0.6258 0.7306
-0.500 0.1746 0.00928 0.00346 -0.0415 0.6224 0.7313
0.000 0.2309 0.00930 0.00342 -0.0421 0.6159 0.7331
0.250 0.2591 0.00930 0.00341 -0.0424 0.6124 0.7339
0.500 0.2871 0.00930 0.00339 -0.0427 0.6089 0.7346
0.750 0.3151 0.00932 0.00337 -0.0430 0.6055 0.7354
1.000 0.3431 0.00935 0.00336 -0.0433 0.6024 0.7363
1.250 0.3711 0.00934 0.00336 -0.0436 0.5986 0.7371
1.500 0.3990 0.00936 0.00337 -0.0439 0.5945 0.7380
1.750 0.4266 0.00939 0.00337 -0.0441 0.5903 0.7390
2.000 0.4541 0.00942 0.00338 -0.0443 0.5861 0.7401
2.250 0.4818 0.00943 0.00340 -0.0445 0.5812 0.7410
2.500 0.5093 0.00946 0.00342 -0.0447 0.5764 0.7418
2.750 0.5365 0.00951 0.00344 -0.0449 0.5720 0.7425
3.000 0.5641 0.00953 0.00348 -0.0451 0.5671 0.7432
3.250 0.5911 0.00956 0.00353 -0.0452 0.5618 0.7439
3.500 0.6176 0.00961 0.00357 -0.0452 0.5565 0.7446
3.750 0.6445 0.00964 0.00364 -0.0453 0.5509 0.7453
4.000 0.6708 0.00969 0.00372 -0.0453 0.5445 0.7459
4.250 0.6968 0.00975 0.00379 -0.0452 0.5381 0.7467
4.500 0.7229 0.00980 0.00388 -0.0451 0.5304 0.7474
4.750 0.7480 0.00989 0.00398 -0.0448 0.5225 0.7483
5.000 0.7732 0.00997 0.00408 -0.0445 0.5128 0.7492
5.250 0.7979 0.01006 0.00420 -0.0442 0.5028 0.7502
5.500 0.8216 0.01017 0.00431 -0.0437 0.4919 0.7512
5.750 0.8443 0.01031 0.00444 -0.0430 0.4778 0.7521
6.000 0.8660 0.01048 0.00459 -0.0421 0.4605 0.7530
6.250 0.8853 0.01071 0.00477 -0.0407 0.4379 0.7540
6.500 0.9011 0.01103 0.00500 -0.0388 0.4106 0.7550
6.750 0.9144 0.01143 0.00528 -0.0364 0.3824 0.7561
7.000 0.9239 0.01185 0.00559 -0.0332 0.3545 0.7572
7.250 0.9338 0.01230 0.00594 -0.0302 0.3282 0.7583
7.500 0.9437 0.01283 0.00637 -0.0274 0.3034 0.7592
7.750 0.9537 0.01337 0.00683 -0.0246 0.2799 0.7602
8.000 0.9630 0.01394 0.00734 -0.0218 0.2571 0.7613
8.250 0.9717 0.01456 0.00789 -0.0191 0.2351 0.7625
8.500 0.9790 0.01526 0.00851 -0.0162 0.2134 0.7638
8.750 0.9867 0.01598 0.00918 -0.0136 0.1926 0.7651
9.000 0.9942 0.01676 0.00989 -0.0111 0.1742 0.7663
9.250 1.0004 0.01764 0.01071 -0.0085 0.1555 0.7676
9.500 1.0077 0.01853 0.01154 -0.0062 0.1386 0.7689
9.750 1.0160 0.01942 0.01240 -0.0042 0.1253 0.7701
10.000 1.0242 0.02036 0.01332 -0.0024 0.1131 0.7714
10.250 1.0320 0.02137 0.01430 -0.0005 0.1010 0.7727
10.500 1.0398 0.02244 0.01534 0.0012 0.0893 0.7739
10.750 1.0490 0.02346 0.01637 0.0026 0.0806 0.7750
11.000 1.0570 0.02458 0.01749 0.0041 0.0720 0.7762
11.250 1.0642 0.02577 0.01868 0.0056 0.0637 0.7774
11.500 1.0712 0.02702 0.01994 0.0070 0.0563 0.7786
11.750 1.0789 0.02827 0.02121 0.0082 0.0494 0.7799
12.000 1.0864 0.02958 0.02254 0.0093 0.0438 0.7814
12.250 1.0926 0.03101 0.02398 0.0105 0.0378 0.7829
12.500 1.0998 0.03243 0.02542 0.0115 0.0336 0.7845
12.750 1.1059 0.03397 0.02697 0.0124 0.0284 0.7861
13.000 1.1133 0.03545 0.02849 0.0132 0.0255 0.7876
13.250 1.1189 0.03712 0.03018 0.0140 0.0217 0.7890
13.500 1.1250 0.03882 0.03190 0.0146 0.0187 0.7903
13.750 1.1316 0.04049 0.03362 0.0152 0.0162 0.7916
14.000 1.1377 0.04225 0.03543 0.0157 0.0147 0.7930
14.250 1.1438 0.04405 0.03730 0.0161 0.0129 0.7945
14.500 1.1494 0.04594 0.03925 0.0165 0.0114 0.7960
14.750 1.1550 0.04790 0.04128 0.0167 0.0102 0.7976
15.000 1.1598 0.04997 0.04343 0.0168 0.0087 0.7993
15.250 1.1658 0.05199 0.04554 0.0169 0.0084 0.8010
15.500 1.1693 0.05432 0.04793 0.0169 0.0072 0.8027
15.750 1.1740 0.05658 0.05027 0.0168 0.0064 0.8045
16.000 1.1777 0.05903 0.05280 0.0165 0.0059 0.8061
16.250 1.1802 0.06163 0.05548 0.0162 0.0053 0.8078
16.500 1.1828 0.06428 0.05823 0.0158 0.0048 0.8095
16.750 1.1838 0.06718 0.06123 0.0153 0.0043 0.8114
17.000 1.1842 0.07026 0.06441 0.0146 0.0037 0.8136
17.250 1.1851 0.07334 0.06760 0.0139 0.0034 0.8158
17.500 1.1843 0.07672 0.07109 0.0129 0.0032 0.8181
17.750 1.1835 0.08022 0.07470 0.0118 0.0031 0.8204
18.000 1.1800 0.08417 0.07874 0.0105 0.0027 0.8225
18.250 1.1784 0.08792 0.08262 0.0091 0.0027 0.8247
18.500 1.1747 0.09207 0.08691 0.0075 0.0025 0.8270
18.750 1.1709 0.09631 0.09129 0.0057 0.0024 0.8295
19.000 1.1665 0.10077 0.09587 0.0038 0.0022 0.8320
19.250 1.1605 0.10557 0.10080 0.0016 0.0021 0.8345
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Polar data table (+)
Polar graphs
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