EPPLER 546 AIRFOIL (e546-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 546 AIRFOIL (e546-il) Reynolds number: 500,000 Max Cl/Cd: 87.37 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e546-il-500000.txt Download as CSV file: xf-e546-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 546 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.3109 0.13717 0.13492 -0.0380 1.0000 0.0165
-14.250 -0.3234 0.13114 0.12891 -0.0411 1.0000 0.0177
-14.000 -0.4388 0.13795 0.13552 -0.0334 1.0000 0.0151
-13.750 -0.4355 0.13450 0.13208 -0.0345 1.0000 0.0154
-13.500 -0.4336 0.13066 0.12826 -0.0358 1.0000 0.0162
-13.250 -0.4339 0.12605 0.12366 -0.0376 1.0000 0.0161
-9.250 -0.6866 0.03020 0.02530 -0.0513 0.9736 0.0108
-9.000 -0.6637 0.02704 0.02177 -0.0516 0.9660 0.0104
-8.750 -0.6347 0.02482 0.01928 -0.0527 0.9598 0.0105
-8.500 -0.6012 0.02284 0.01706 -0.0542 0.9546 0.0105
-8.250 -0.5644 0.02136 0.01541 -0.0564 0.9488 0.0108
-8.000 -0.5210 0.01986 0.01375 -0.0596 0.9454 0.0111
-7.750 -0.4778 0.01853 0.01233 -0.0629 0.9400 0.0111
-7.500 -0.4353 0.01738 0.01108 -0.0663 0.9312 0.0114
-7.250 -0.3966 0.01634 0.00996 -0.0694 0.9178 0.0117
-7.000 -0.3713 0.01524 0.00879 -0.0702 0.8985 0.0124
-6.750 -0.3526 0.01463 0.00807 -0.0692 0.8797 0.0133
-6.500 -0.3398 0.01417 0.00749 -0.0669 0.8626 0.0139
-6.250 -0.3298 0.01366 0.00689 -0.0640 0.8470 0.0158
-6.000 -0.3149 0.01325 0.00640 -0.0619 0.8335 0.0183
-5.750 -0.3010 0.01273 0.00586 -0.0596 0.8212 0.0253
-5.500 -0.2890 0.01208 0.00533 -0.0572 0.8098 0.0522
-5.250 -0.2754 0.01148 0.00491 -0.0551 0.7989 0.0992
-5.000 -0.2615 0.01082 0.00451 -0.0531 0.7882 0.1631
-4.750 -0.2521 0.00979 0.00396 -0.0507 0.7785 0.2851
-4.500 -0.2510 0.00798 0.00315 -0.0471 0.7685 0.5210
-4.250 -0.2286 0.00797 0.00341 -0.0460 0.7598 0.6312
-4.000 -0.2013 0.00821 0.00358 -0.0456 0.7511 0.6515
-3.750 -0.1739 0.00846 0.00375 -0.0453 0.7426 0.6653
-3.500 -0.1463 0.00874 0.00391 -0.0451 0.7346 0.6765
-3.250 -0.1184 0.00894 0.00410 -0.0449 0.7264 0.6828
-3.000 -0.0908 0.00923 0.00428 -0.0446 0.7184 0.6915
-2.750 -0.0631 0.00964 0.00472 -0.0440 0.7103 0.7001
-2.500 -0.0357 0.01009 0.00511 -0.0435 0.7027 0.7107
-2.250 -0.0081 0.01042 0.00545 -0.0430 0.6951 0.7156
-2.000 0.0194 0.01045 0.00540 -0.0430 0.6873 0.7180
-1.750 0.0471 0.01042 0.00529 -0.0431 0.6800 0.7199
-1.500 0.0747 0.01036 0.00515 -0.0433 0.6725 0.7217
-1.250 0.1026 0.01032 0.00500 -0.0436 0.6657 0.7234
-1.000 0.1304 0.01026 0.00487 -0.0439 0.6581 0.7249
-0.750 0.1582 0.01022 0.00472 -0.0441 0.6515 0.7260
-0.500 0.1857 0.01012 0.00462 -0.0442 0.6443 0.7271
-0.250 0.2133 0.01010 0.00454 -0.0444 0.6378 0.7281
0.000 0.2410 0.01007 0.00448 -0.0445 0.6309 0.7291
0.250 0.2687 0.01006 0.00443 -0.0447 0.6243 0.7300
0.500 0.2965 0.01007 0.00438 -0.0449 0.6182 0.7310
0.750 0.3242 0.01005 0.00435 -0.0451 0.6114 0.7322
1.000 0.3520 0.01008 0.00433 -0.0453 0.6054 0.7335
1.250 0.3798 0.01007 0.00432 -0.0455 0.5991 0.7348
1.500 0.4075 0.01007 0.00429 -0.0457 0.5928 0.7359
1.750 0.4354 0.01011 0.00427 -0.0459 0.5870 0.7371
2.000 0.4631 0.01010 0.00426 -0.0462 0.5806 0.7382
2.250 0.4908 0.01013 0.00425 -0.0464 0.5745 0.7394
2.500 0.5186 0.01016 0.00427 -0.0466 0.5683 0.7404
2.750 0.5461 0.01019 0.00428 -0.0468 0.5615 0.7416
3.000 0.5732 0.01021 0.00428 -0.0469 0.5551 0.7428
3.250 0.6001 0.01019 0.00431 -0.0469 0.5482 0.7439
3.500 0.6271 0.01025 0.00434 -0.0470 0.5420 0.7449
3.750 0.6541 0.01028 0.00442 -0.0470 0.5354 0.7459
4.000 0.6808 0.01033 0.00447 -0.0470 0.5285 0.7470
4.250 0.7076 0.01040 0.00455 -0.0470 0.5219 0.7482
4.500 0.7341 0.01044 0.00462 -0.0470 0.5143 0.7494
4.750 0.7604 0.01053 0.00470 -0.0469 0.5072 0.7507
5.000 0.7867 0.01057 0.00479 -0.0468 0.4991 0.7520
5.250 0.8127 0.01068 0.00489 -0.0467 0.4918 0.7535
5.500 0.8389 0.01073 0.00499 -0.0466 0.4834 0.7551
5.750 0.8644 0.01085 0.00510 -0.0464 0.4751 0.7565
6.000 0.8899 0.01093 0.00522 -0.0462 0.4655 0.7578
6.250 0.9146 0.01099 0.00532 -0.0459 0.4556 0.7591
6.500 0.9383 0.01111 0.00545 -0.0453 0.4449 0.7605
6.750 0.9620 0.01122 0.00561 -0.0447 0.4323 0.7618
7.000 0.9853 0.01136 0.00578 -0.0441 0.4187 0.7633
7.250 1.0076 0.01154 0.00597 -0.0433 0.4033 0.7649
7.500 1.0283 0.01177 0.00619 -0.0423 0.3850 0.7666
7.750 1.0481 0.01205 0.00643 -0.0411 0.3629 0.7684
8.000 1.0646 0.01244 0.00674 -0.0393 0.3356 0.7702
8.250 1.0783 0.01295 0.00712 -0.0372 0.3034 0.7722
8.500 1.0878 0.01352 0.00754 -0.0343 0.2717 0.7742
8.750 1.0957 0.01408 0.00801 -0.0310 0.2448 0.7763
9.000 1.1050 0.01469 0.00855 -0.0282 0.2203 0.7784
9.250 1.1134 0.01538 0.00915 -0.0253 0.1970 0.7806
9.500 1.1212 0.01611 0.00981 -0.0225 0.1750 0.7830
9.750 1.1288 0.01687 0.01051 -0.0198 0.1560 0.7856
10.000 1.1363 0.01768 0.01126 -0.0172 0.1381 0.7881
10.250 1.1429 0.01854 0.01207 -0.0147 0.1221 0.7906
10.500 1.1483 0.01947 0.01299 -0.0121 0.1073 0.7933
10.750 1.1534 0.02050 0.01400 -0.0097 0.0940 0.7961
11.000 1.1577 0.02165 0.01513 -0.0074 0.0814 0.7993
11.250 1.1621 0.02288 0.01634 -0.0053 0.0706 0.8027
11.500 1.1661 0.02421 0.01766 -0.0034 0.0610 0.8062
11.750 1.1694 0.02560 0.01907 -0.0015 0.0528 0.8099
12.000 1.1725 0.02711 0.02060 0.0001 0.0459 0.8140
12.250 1.1744 0.02882 0.02230 0.0017 0.0403 0.8183
12.500 1.1793 0.03036 0.02389 0.0028 0.0351 0.8226
12.750 1.1827 0.03204 0.02565 0.0040 0.0314 0.8273
13.000 1.1850 0.03390 0.02757 0.0051 0.0285 0.8329
13.250 1.1899 0.03561 0.02935 0.0058 0.0253 0.8387
13.500 1.1902 0.03773 0.03152 0.0067 0.0229 0.8456
13.750 1.1959 0.03946 0.03336 0.0073 0.0206 0.8539
14.000 1.1956 0.04173 0.03572 0.0080 0.0188 0.8649
14.250 1.1994 0.04363 0.03779 0.0086 0.0172 0.8810
14.500 1.2000 0.04596 0.04031 0.0089 0.0158 0.9233
14.750 1.2064 0.04863 0.04312 0.0075 0.0143 1.0000
15.000 1.2076 0.05138 0.04591 0.0071 0.0127 1.0000
15.250 1.2078 0.05429 0.04890 0.0067 0.0116 1.0000
15.500 1.2066 0.05743 0.05209 0.0062 0.0100 1.0000
15.750 1.2057 0.06064 0.05538 0.0056 0.0092 1.0000
16.000 1.2039 0.06404 0.05887 0.0048 0.0082 1.0000
16.250 1.1995 0.06785 0.06274 0.0038 0.0076 1.0000
16.500 1.1979 0.07141 0.06641 0.0028 0.0066 1.0000
16.750 1.1936 0.07544 0.07054 0.0016 0.0064 1.0000
17.000 1.1896 0.07949 0.07468 0.0002 0.0061 1.0000
17.250 1.1792 0.08462 0.07991 -0.0017 0.0056 1.0000
17.500 1.1736 0.08917 0.08458 -0.0034 0.0054 1.0000
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