EPPLER 548 AIRFOIL (e548-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 548 AIRFOIL (e548-il) Reynolds number: 500,000 Max Cl/Cd: 93.68 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e548-il-500000.txt Download as CSV file: xf-e548-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 548 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3548 0.09472 0.09269 -0.0467 1.0000 0.0213
-12.000 -0.3953 0.07902 0.07696 -0.0551 1.0000 0.0210
-10.500 -0.7633 0.03756 0.03314 -0.0444 1.0000 0.0105
-10.250 -0.7607 0.03645 0.03207 -0.0417 1.0000 0.0107
-9.750 -0.7143 0.02823 0.02304 -0.0443 0.9541 0.0090
-9.500 -0.6503 0.02444 0.01874 -0.0519 0.9365 0.0087
-9.250 -0.5638 0.02207 0.01607 -0.0641 0.9056 0.0089
-9.000 -0.5151 0.02096 0.01459 -0.0687 0.8439 0.0096
-8.750 -0.4975 0.02035 0.01373 -0.0672 0.8048 0.0099
-8.250 -0.4664 0.01922 0.01226 -0.0638 0.7545 0.0102
-8.000 -0.4558 0.01831 0.01126 -0.0615 0.7357 0.0106
-7.750 -0.4427 0.01770 0.01058 -0.0595 0.7191 0.0114
-7.500 -0.4289 0.01716 0.00992 -0.0576 0.7043 0.0124
-7.250 -0.4156 0.01662 0.00927 -0.0556 0.6907 0.0127
-7.000 -0.4062 0.01593 0.00852 -0.0530 0.6780 0.0135
-6.750 -0.3948 0.01543 0.00797 -0.0506 0.6669 0.0146
-6.500 -0.3848 0.01504 0.00750 -0.0478 0.6569 0.0166
-6.250 -0.3697 0.01468 0.00709 -0.0458 0.6472 0.0186
-6.000 -0.3544 0.01425 0.00661 -0.0439 0.6387 0.0228
-5.750 -0.3400 0.01371 0.00608 -0.0418 0.6302 0.0323
-5.500 -0.3257 0.01314 0.00562 -0.0398 0.6230 0.0548
-5.250 -0.3103 0.01256 0.00522 -0.0380 0.6155 0.0931
-5.000 -0.2949 0.01197 0.00482 -0.0363 0.6089 0.1480
-4.750 -0.2817 0.01108 0.00435 -0.0345 0.6023 0.2420
-4.500 -0.2741 0.00966 0.00363 -0.0320 0.5963 0.4103
-4.250 -0.2612 0.00874 0.00348 -0.0298 0.5908 0.6059
-4.000 -0.2335 0.00893 0.00365 -0.0296 0.5850 0.6405
-3.750 -0.2056 0.00922 0.00388 -0.0294 0.5795 0.6585
-3.500 -0.1775 0.00948 0.00399 -0.0293 0.5745 0.6692
-3.250 -0.1489 0.00968 0.00419 -0.0292 0.5696 0.6763
-3.000 -0.1206 0.00993 0.00435 -0.0291 0.5647 0.6852
-2.750 -0.0924 0.01030 0.00470 -0.0288 0.5601 0.6928
-2.500 -0.0642 0.01071 0.00504 -0.0285 0.5558 0.7031
-2.250 -0.0360 0.01123 0.00565 -0.0278 0.5517 0.7111
-2.000 -0.0077 0.01146 0.00581 -0.0278 0.5478 0.7172
-1.750 0.0207 0.01146 0.00568 -0.0281 0.5441 0.7193
-1.500 0.0488 0.01138 0.00555 -0.0283 0.5407 0.7205
-1.250 0.0771 0.01132 0.00546 -0.0286 0.5372 0.7217
-1.000 0.1055 0.01127 0.00538 -0.0288 0.5336 0.7228
-0.750 0.1339 0.01127 0.00532 -0.0291 0.5302 0.7239
-0.500 0.1624 0.01130 0.00527 -0.0294 0.5271 0.7252
-0.250 0.1910 0.01130 0.00523 -0.0297 0.5243 0.7263
0.000 0.2196 0.01126 0.00518 -0.0301 0.5214 0.7274
0.250 0.2482 0.01125 0.00514 -0.0304 0.5183 0.7288
0.500 0.2768 0.01124 0.00509 -0.0308 0.5153 0.7302
0.750 0.3055 0.01125 0.00504 -0.0312 0.5125 0.7314
1.000 0.3345 0.01132 0.00504 -0.0317 0.5097 0.7325
1.250 0.3632 0.01131 0.00502 -0.0321 0.5073 0.7336
1.500 0.3919 0.01130 0.00501 -0.0325 0.5045 0.7347
1.750 0.4205 0.01131 0.00500 -0.0329 0.5017 0.7359
2.000 0.4488 0.01128 0.00497 -0.0332 0.4991 0.7370
2.250 0.4772 0.01130 0.00497 -0.0335 0.4966 0.7379
2.500 0.5059 0.01140 0.00504 -0.0340 0.4938 0.7389
2.750 0.5341 0.01143 0.00510 -0.0342 0.4914 0.7398
3.000 0.5622 0.01145 0.00516 -0.0345 0.4888 0.7409
3.250 0.5905 0.01148 0.00520 -0.0348 0.4859 0.7419
3.500 0.6187 0.01151 0.00525 -0.0351 0.4831 0.7430
3.750 0.6471 0.01157 0.00530 -0.0354 0.4803 0.7442
4.000 0.6759 0.01174 0.00542 -0.0359 0.4770 0.7456
4.250 0.7033 0.01174 0.00549 -0.0360 0.4741 0.7471
4.500 0.7310 0.01175 0.00555 -0.0363 0.4706 0.7484
4.750 0.7590 0.01179 0.00560 -0.0365 0.4673 0.7497
5.000 0.7870 0.01185 0.00565 -0.0368 0.4640 0.7508
5.250 0.8155 0.01201 0.00579 -0.0373 0.4605 0.7519
5.500 0.8420 0.01196 0.00584 -0.0372 0.4569 0.7531
5.750 0.8689 0.01196 0.00590 -0.0373 0.4528 0.7543
6.000 0.8959 0.01199 0.00596 -0.0373 0.4489 0.7555
6.250 0.9235 0.01213 0.00609 -0.0376 0.4448 0.7568
6.500 0.9493 0.01212 0.00620 -0.0374 0.4406 0.7582
6.750 0.9756 0.01215 0.00629 -0.0373 0.4359 0.7597
7.000 1.0019 0.01221 0.00637 -0.0373 0.4311 0.7615
7.250 1.0278 0.01228 0.00651 -0.0372 0.4259 0.7632
7.500 1.0534 0.01230 0.00661 -0.0370 0.4199 0.7649
7.750 1.0789 0.01239 0.00669 -0.0369 0.4139 0.7665
8.000 1.1042 0.01244 0.00685 -0.0367 0.4073 0.7680
8.250 1.1285 0.01248 0.00693 -0.0363 0.3998 0.7696
8.500 1.1527 0.01254 0.00708 -0.0359 0.3912 0.7712
8.750 1.1753 0.01265 0.00723 -0.0352 0.3812 0.7729
9.000 1.1974 0.01279 0.00741 -0.0345 0.3684 0.7748
9.250 1.2179 0.01300 0.00764 -0.0335 0.3529 0.7768
9.500 1.2367 0.01329 0.00793 -0.0322 0.3341 0.7790
9.750 1.2512 0.01375 0.00832 -0.0303 0.3102 0.7813
10.000 1.2616 0.01435 0.00883 -0.0278 0.2852 0.7838
10.500 1.2679 0.01574 0.01008 -0.0204 0.2409 0.7891
10.750 1.2699 0.01658 0.01088 -0.0168 0.2218 0.7919
11.000 1.2694 0.01758 0.01183 -0.0132 0.2039 0.7951
11.250 1.2680 0.01872 0.01292 -0.0098 0.1879 0.7985
11.500 1.2660 0.02001 0.01419 -0.0068 0.1733 0.8018
11.750 1.2632 0.02146 0.01566 -0.0042 0.1600 0.8055
12.000 1.2599 0.02317 0.01738 -0.0019 0.1473 0.8095
12.250 1.2563 0.02511 0.01932 0.0000 0.1353 0.8138
12.500 1.2523 0.02724 0.02146 0.0015 0.1245 0.8182
12.750 1.2471 0.02956 0.02381 0.0029 0.1148 0.8230
13.000 1.2422 0.03199 0.02627 0.0040 0.1055 0.8288
13.250 1.2390 0.03439 0.02871 0.0048 0.0969 0.8347
13.500 1.2336 0.03699 0.03136 0.0057 0.0892 0.8415
13.750 1.2289 0.03965 0.03405 0.0063 0.0818 0.8495
14.000 1.2254 0.04219 0.03667 0.0069 0.0753 0.8593
14.250 1.2184 0.04511 0.03965 0.0074 0.0690 0.8724
14.750 1.2204 0.05074 0.04556 0.0057 0.0564 1.0000
15.000 1.2174 0.05391 0.04872 0.0052 0.0515 1.0000
15.250 1.2173 0.05682 0.05168 0.0047 0.0472 1.0000
15.500 1.2130 0.06025 0.05510 0.0041 0.0429 1.0000
15.750 1.2143 0.06309 0.05799 0.0034 0.0396 1.0000
16.000 1.2102 0.06665 0.06156 0.0026 0.0365 1.0000
16.250 1.2114 0.06962 0.06457 0.0019 0.0333 1.0000
16.500 1.2082 0.07320 0.06818 0.0009 0.0309 1.0000
16.750 1.2080 0.07647 0.07151 0.0000 0.0286 1.0000
17.000 1.2066 0.07995 0.07503 -0.0011 0.0264 1.0000
17.250 1.2010 0.08407 0.07918 -0.0024 0.0250 1.0000
17.500 1.2036 0.08712 0.08232 -0.0035 0.0228 1.0000
17.750 1.1999 0.09114 0.08638 -0.0050 0.0214 1.0000
18.000 1.1992 0.09478 0.09009 -0.0064 0.0199 1.0000
18.250 1.1973 0.09864 0.09403 -0.0079 0.0186 1.0000
18.500 1.1907 0.10329 0.09872 -0.0098 0.0175 1.0000
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Polar data table (+)
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