EPPLER 547 AIRFOIL (e547-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 547 AIRFOIL (e547-il) Reynolds number: 500,000 Max Cl/Cd: 90.17 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e547-il-500000.txt Download as CSV file: xf-e547-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 547 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.2822 0.15269 0.15047 -0.0336 1.0000 0.0167
-16.250 -0.2807 0.14996 0.14774 -0.0352 1.0000 0.0173
-10.000 -0.6686 0.03224 0.02742 -0.0633 0.9579 0.0108
-9.750 -0.6378 0.02846 0.02332 -0.0660 0.9508 0.0103
-9.500 -0.5982 0.02481 0.01921 -0.0686 0.9460 0.0094
-9.250 -0.5530 0.02263 0.01674 -0.0719 0.9399 0.0091
-9.000 -0.5072 0.02119 0.01517 -0.0759 0.9293 0.0093
-8.750 -0.4655 0.02003 0.01387 -0.0793 0.9136 0.0096
-8.500 -0.4356 0.01913 0.01283 -0.0805 0.8936 0.0099
-8.250 -0.4157 0.01846 0.01203 -0.0797 0.8740 0.0100
-8.000 -0.3998 0.01782 0.01126 -0.0782 0.8574 0.0107
-7.750 -0.3843 0.01727 0.01060 -0.0765 0.8426 0.0111
-7.500 -0.3756 0.01643 0.00966 -0.0740 0.8290 0.0116
-7.250 -0.3638 0.01582 0.00897 -0.0718 0.8170 0.0122
-7.000 -0.3512 0.01528 0.00837 -0.0697 0.8051 0.0134
-6.750 -0.3380 0.01481 0.00781 -0.0675 0.7945 0.0143
-6.500 -0.3296 0.01422 0.00716 -0.0646 0.7846 0.0168
-6.250 -0.3214 0.01378 0.00668 -0.0613 0.7744 0.0203
-6.000 -0.3097 0.01334 0.00622 -0.0587 0.7653 0.0289
-5.750 -0.2991 0.01275 0.00574 -0.0560 0.7566 0.0518
-5.500 -0.2862 0.01220 0.00535 -0.0538 0.7482 0.0870
-5.250 -0.2727 0.01164 0.00496 -0.0517 0.7404 0.1360
-5.000 -0.2633 0.01078 0.00450 -0.0491 0.7323 0.2253
-4.750 -0.2595 0.00947 0.00381 -0.0458 0.7247 0.3787
-4.500 -0.2544 0.00823 0.00347 -0.0423 0.7170 0.5901
-4.250 -0.2282 0.00841 0.00362 -0.0419 0.7100 0.6345
-4.000 -0.2009 0.00865 0.00379 -0.0416 0.7031 0.6546
-3.750 -0.1734 0.00889 0.00393 -0.0414 0.6961 0.6670
-3.500 -0.1451 0.00912 0.00412 -0.0413 0.6895 0.6742
-3.250 -0.1178 0.00932 0.00420 -0.0411 0.6823 0.6829
-3.000 -0.0892 0.00966 0.00454 -0.0409 0.6761 0.6903
-2.750 -0.0616 0.00997 0.00481 -0.0406 0.6693 0.6999
-2.500 -0.0330 0.01054 0.00540 -0.0400 0.6632 0.7088
-2.250 -0.0056 0.01076 0.00557 -0.0398 0.6569 0.7158
-2.000 0.0221 0.01077 0.00552 -0.0398 0.6504 0.7175
-1.750 0.0501 0.01078 0.00545 -0.0399 0.6447 0.7189
-1.500 0.0779 0.01073 0.00536 -0.0401 0.6386 0.7203
-1.250 0.1057 0.01071 0.00526 -0.0403 0.6328 0.7218
-1.000 0.1336 0.01067 0.00517 -0.0406 0.6271 0.7232
-0.750 0.1614 0.01062 0.00506 -0.0408 0.6211 0.7247
-0.500 0.1894 0.01061 0.00495 -0.0411 0.6159 0.7263
-0.250 0.2173 0.01056 0.00486 -0.0414 0.6104 0.7276
0.000 0.2453 0.01051 0.00476 -0.0417 0.6049 0.7287
0.250 0.2735 0.01053 0.00468 -0.0421 0.5999 0.7300
0.500 0.3010 0.01045 0.00461 -0.0423 0.5946 0.7310
0.750 0.3288 0.01042 0.00456 -0.0425 0.5894 0.7319
1.000 0.3568 0.01045 0.00452 -0.0427 0.5846 0.7328
1.250 0.3845 0.01043 0.00452 -0.0429 0.5796 0.7338
1.500 0.4123 0.01043 0.00451 -0.0432 0.5746 0.7348
1.750 0.4403 0.01048 0.00450 -0.0434 0.5700 0.7359
2.000 0.4680 0.01050 0.00453 -0.0436 0.5653 0.7372
2.250 0.4957 0.01051 0.00455 -0.0439 0.5603 0.7385
2.500 0.5236 0.01055 0.00455 -0.0441 0.5557 0.7397
2.750 0.5514 0.01059 0.00458 -0.0444 0.5511 0.7408
3.000 0.5789 0.01060 0.00461 -0.0446 0.5460 0.7420
3.250 0.6066 0.01064 0.00462 -0.0449 0.5413 0.7432
3.500 0.6344 0.01072 0.00467 -0.0452 0.5365 0.7443
3.750 0.6616 0.01074 0.00472 -0.0453 0.5310 0.7453
4.000 0.6884 0.01074 0.00472 -0.0454 0.5258 0.7465
4.250 0.7153 0.01080 0.00479 -0.0454 0.5206 0.7477
4.500 0.7416 0.01081 0.00487 -0.0454 0.5148 0.7489
4.750 0.7682 0.01089 0.00494 -0.0454 0.5095 0.7502
5.000 0.7947 0.01095 0.00504 -0.0454 0.5041 0.7514
5.250 0.8209 0.01099 0.00514 -0.0453 0.4982 0.7527
5.500 0.8473 0.01111 0.00522 -0.0453 0.4926 0.7540
5.750 0.8730 0.01115 0.00534 -0.0452 0.4863 0.7555
6.000 0.8985 0.01122 0.00543 -0.0450 0.4798 0.7569
6.250 0.9238 0.01131 0.00555 -0.0448 0.4729 0.7584
6.500 0.9487 0.01139 0.00565 -0.0445 0.4654 0.7598
6.750 0.9733 0.01149 0.00579 -0.0442 0.4581 0.7611
7.000 0.9969 0.01156 0.00590 -0.0437 0.4496 0.7627
7.250 1.0203 0.01165 0.00606 -0.0431 0.4409 0.7643
7.500 1.0424 0.01180 0.00622 -0.0423 0.4318 0.7660
7.750 1.0647 0.01191 0.00640 -0.0415 0.4206 0.7677
8.000 1.0859 0.01207 0.00659 -0.0406 0.4088 0.7695
8.250 1.1055 0.01226 0.00680 -0.0394 0.3950 0.7714
8.500 1.1229 0.01251 0.00704 -0.0378 0.3779 0.7733
8.750 1.1356 0.01281 0.00730 -0.0353 0.3589 0.7753
9.000 1.1458 0.01318 0.00762 -0.0325 0.3375 0.7772
9.250 1.1523 0.01374 0.00810 -0.0291 0.3126 0.7794
9.500 1.1584 0.01439 0.00867 -0.0258 0.2871 0.7816
9.750 1.1629 0.01514 0.00934 -0.0225 0.2636 0.7842
10.000 1.1660 0.01601 0.01013 -0.0192 0.2405 0.7871
10.250 1.1697 0.01692 0.01097 -0.0162 0.2202 0.7901
10.500 1.1728 0.01791 0.01190 -0.0133 0.2006 0.7929
10.750 1.1750 0.01899 0.01295 -0.0105 0.1829 0.7958
11.000 1.1773 0.02017 0.01410 -0.0080 0.1671 0.7989
11.250 1.1792 0.02148 0.01537 -0.0056 0.1512 0.8024
11.500 1.1817 0.02285 0.01671 -0.0036 0.1374 0.8059
11.750 1.1834 0.02432 0.01816 -0.0016 0.1237 0.8094
12.000 1.1845 0.02590 0.01975 0.0003 0.1113 0.8133
12.250 1.1859 0.02756 0.02140 0.0019 0.0996 0.8176
12.500 1.1886 0.02923 0.02308 0.0032 0.0898 0.8222
12.750 1.1899 0.03100 0.02489 0.0046 0.0807 0.8270
13.000 1.1895 0.03299 0.02689 0.0059 0.0722 0.8329
13.250 1.1906 0.03495 0.02888 0.0069 0.0646 0.8393
13.500 1.1920 0.03691 0.03090 0.0078 0.0578 0.8470
13.750 1.1898 0.03925 0.03328 0.0088 0.0513 0.8561
14.000 1.1918 0.04127 0.03538 0.0095 0.0458 0.8685
14.250 1.1894 0.04364 0.03787 0.0104 0.0417 0.8891
14.500 1.2010 0.04614 0.04056 0.0083 0.0365 0.9458
14.750 1.2013 0.04874 0.04320 0.0082 0.0330 1.0000
15.000 1.2042 0.05121 0.04571 0.0080 0.0302 1.0000
15.250 1.2014 0.05433 0.04883 0.0078 0.0272 1.0000
15.500 1.2065 0.05667 0.05124 0.0074 0.0252 1.0000
15.750 1.2070 0.05956 0.05417 0.0070 0.0232 1.0000
16.000 1.2035 0.06298 0.05762 0.0065 0.0214 1.0000
16.250 1.2062 0.06573 0.06047 0.0060 0.0200 1.0000
16.500 1.2080 0.06862 0.06338 0.0053 0.0181 1.0000
16.750 1.2028 0.07249 0.06732 0.0044 0.0171 1.0000
17.000 1.2054 0.07542 0.07034 0.0036 0.0158 1.0000
17.250 1.2037 0.07896 0.07396 0.0025 0.0147 1.0000
17.500 1.2003 0.08282 0.07787 0.0013 0.0138 1.0000
17.750 1.1960 0.08688 0.08202 0.0000 0.0128 1.0000
18.000 1.1949 0.09057 0.08580 -0.0013 0.0118 1.0000
18.250 1.1919 0.09457 0.08988 -0.0028 0.0110 1.0000
18.500 1.1830 0.09956 0.09494 -0.0048 0.0104 1.0000
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Polar data table (+)
Polar graphs
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