EPPLER 548 AIRFOIL (e548-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 548 AIRFOIL (e548-il) Reynolds number: 50,000 Max Cl/Cd: 10.76 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e548-il-50000-n5.txt Download as CSV file: xf-e548-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4732 0.09840 0.09133 -0.0510 1.0000 0.0382
-12.000 -0.4854 0.09259 0.08553 -0.0538 1.0000 0.0378
-11.750 -0.5036 0.08669 0.07959 -0.0566 1.0000 0.0375
-11.500 -0.5255 0.08116 0.07400 -0.0587 1.0000 0.0373
-11.250 -0.5447 0.07659 0.06935 -0.0596 1.0000 0.0369
-11.000 -0.5641 0.07246 0.06511 -0.0597 1.0000 0.0366
-10.750 -0.5842 0.06870 0.06122 -0.0590 1.0000 0.0365
-10.500 -0.6015 0.06553 0.05791 -0.0574 1.0000 0.0364
-10.250 -0.6191 0.06263 0.05486 -0.0550 1.0000 0.0364
-10.000 -0.6347 0.06017 0.05226 -0.0518 1.0000 0.0364
-9.750 -0.6494 0.05782 0.04976 -0.0480 1.0000 0.0365
-9.500 -0.6581 0.05539 0.04715 -0.0446 1.0000 0.0366
-9.250 -0.6639 0.05311 0.04466 -0.0412 1.0000 0.0367
-9.000 -0.6680 0.05090 0.04224 -0.0378 1.0000 0.0370
-8.750 -0.6721 0.04906 0.04022 -0.0341 1.0000 0.0374
-8.500 -0.6589 0.04658 0.03737 -0.0332 0.9918 0.0380
-8.250 -0.6225 0.04382 0.03443 -0.0361 0.9725 0.0402
-8.000 -0.5812 0.04131 0.03155 -0.0390 0.9559 0.0441
-7.750 -0.5283 0.03889 0.02899 -0.0424 0.9445 0.0482
-7.500 -0.4614 0.03699 0.02695 -0.0468 0.9369 0.0575
-7.250 -0.4032 0.03552 0.02540 -0.0503 0.9254 0.0701
-7.000 -0.3619 0.03399 0.02389 -0.0528 0.9078 0.0884
-6.750 -0.3319 0.03227 0.02233 -0.0545 0.8881 0.1183
-6.500 -0.3148 0.03032 0.02079 -0.0548 0.8678 0.1704
-6.250 -0.3137 0.02825 0.01943 -0.0528 0.8479 0.2602
-6.000 -0.2615 0.03195 0.02453 -0.0479 0.8340 0.5688
-5.750 -0.2575 0.03243 0.02471 -0.0440 0.8163 0.6156
-5.500 -0.2460 0.03349 0.02546 -0.0401 0.8012 0.6507
-5.250 -0.2079 0.03522 0.02678 -0.0387 0.7887 0.6807
-5.000 -0.1653 0.03653 0.02768 -0.0384 0.7772 0.7067
-4.750 -0.1220 0.03726 0.02807 -0.0391 0.7655 0.7264
-4.500 -0.0929 0.03733 0.02783 -0.0389 0.7552 0.7404
-4.250 -0.0768 0.03718 0.02745 -0.0372 0.7452 0.7528
-4.000 -0.0395 0.03697 0.02696 -0.0388 0.7356 0.7597
-3.750 -0.0269 0.03671 0.02650 -0.0368 0.7274 0.7694
-3.500 0.0063 0.03645 0.02602 -0.0380 0.7188 0.7751
-3.250 0.0196 0.03620 0.02561 -0.0362 0.7114 0.7833
-3.000 0.0463 0.03593 0.02516 -0.0364 0.7038 0.7884
-2.750 0.0711 0.03568 0.02475 -0.0365 0.6965 0.7937
-2.500 0.0772 0.03552 0.02445 -0.0335 0.6906 0.8010
-2.250 0.1077 0.03529 0.02412 -0.0346 0.6833 0.8044
-2.000 0.1338 0.03506 0.02373 -0.0349 0.6777 0.8087
-1.750 0.1478 0.03496 0.02354 -0.0333 0.6719 0.8138
-1.500 0.1599 0.03490 0.02343 -0.0314 0.6656 0.8186
-1.250 0.1879 0.03468 0.02308 -0.0320 0.6605 0.8215
-1.000 0.2083 0.03463 0.02296 -0.0315 0.6552 0.8252
-0.750 0.2180 0.03469 0.02300 -0.0292 0.6496 0.8295
-0.500 0.2251 0.03467 0.02292 -0.0263 0.6450 0.8338
-0.250 0.2524 0.03455 0.02269 -0.0268 0.6409 0.8362
0.000 0.2669 0.03474 0.02292 -0.0255 0.6348 0.8392
0.250 0.2815 0.03479 0.02294 -0.0240 0.6300 0.8425
0.500 0.2942 0.03478 0.02286 -0.0220 0.6264 0.8461
0.750 0.2962 0.03502 0.02312 -0.0186 0.6216 0.8497
1.000 0.3125 0.03528 0.02340 -0.0176 0.6162 0.8521
1.250 0.3326 0.03536 0.02347 -0.0169 0.6120 0.8547
1.500 0.3533 0.03535 0.02340 -0.0162 0.6088 0.8573
1.750 0.3482 0.03596 0.02409 -0.0121 0.6031 0.8609
2.000 0.3447 0.03633 0.02449 -0.0079 0.5982 0.8651
2.250 0.3685 0.03644 0.02459 -0.0078 0.5944 0.8672
2.500 0.3927 0.03650 0.02462 -0.0077 0.5913 0.8693
2.750 0.3790 0.03758 0.02584 -0.0029 0.5843 0.8732
3.000 0.3861 0.03794 0.02622 -0.0004 0.5799 0.8768
3.250 0.3991 0.03802 0.02629 0.0015 0.5766 0.8804
3.500 0.3930 0.03915 0.02752 0.0049 0.5700 0.8841
3.750 0.3965 0.03990 0.02832 0.0073 0.5644 0.8875
4.000 0.4173 0.04007 0.02850 0.0078 0.5610 0.8902
4.500 0.4032 0.04239 0.03095 0.0144 0.5478 0.8998
4.750 0.4298 0.04257 0.03119 0.0141 0.5444 0.9027
5.250 0.4157 0.04530 0.03403 0.0197 0.5302 0.9131
5.500 0.4490 0.04532 0.03411 0.0187 0.5272 0.9156
6.000 0.4511 0.04854 0.03750 0.0209 0.5121 0.9274
6.250 0.4902 0.04827 0.03731 0.0197 0.5097 0.9302
6.500 0.4723 0.05157 0.04072 0.0203 0.4974 0.9384
6.750 0.5070 0.05151 0.04076 0.0194 0.4942 0.9423
7.000 0.5015 0.05448 0.04386 0.0187 0.4827 0.9494
7.250 0.5361 0.05453 0.04402 0.0176 0.4787 0.9543
7.750 0.5729 0.05744 0.04720 0.0147 0.4630 0.9690
8.250 0.6060 0.06020 0.05020 0.0123 0.4471 1.0000
8.750 0.6226 0.06273 0.05288 0.0129 0.4311 1.0000
9.000 0.6194 0.06529 0.05549 0.0127 0.4200 1.0000
9.250 0.6490 0.06525 0.05557 0.0124 0.4149 1.0000
9.500 0.6465 0.06797 0.05835 0.0119 0.4031 1.0000
9.750 0.6805 0.06751 0.05804 0.0117 0.3986 1.0000
10.000 0.6765 0.07049 0.06108 0.0111 0.3860 1.0000
10.500 0.7093 0.07269 0.06350 0.0104 0.3692 1.0000
10.750 0.7091 0.07548 0.06638 0.0097 0.3572 1.0000
11.000 0.7445 0.07445 0.06551 0.0099 0.3525 1.0000
11.250 0.7415 0.07758 0.06871 0.0092 0.3397 1.0000
11.500 0.7433 0.08030 0.07152 0.0085 0.3281 1.0000
11.750 0.7776 0.07900 0.07040 0.0090 0.3228 1.0000
12.250 0.7774 0.08499 0.07657 0.0075 0.2986 1.0000
12.500 0.8125 0.08313 0.07488 0.0084 0.2930 1.0000
12.750 0.8093 0.08664 0.07847 0.0075 0.2803 1.0000
13.250 0.8484 0.08682 0.07896 0.0080 0.2632 1.0000
13.750 0.8500 0.09298 0.08529 0.0064 0.2401 1.0000
14.000 0.8922 0.08915 0.08167 0.0082 0.2331 1.0000
14.250 0.8844 0.09373 0.08631 0.0067 0.2209 1.0000
14.500 0.8893 0.09621 0.08888 0.0061 0.2101 1.0000
14.750 0.9350 0.09158 0.08434 0.0084 0.2010 1.0000
15.000 0.9327 0.09525 0.08812 0.0072 0.1896 1.0000
15.250 0.9218 0.10059 0.09354 0.0052 0.1791 1.0000
15.500 0.9385 0.10097 0.09396 0.0054 0.1688 1.0000
15.750 0.9644 0.09963 0.09258 0.0064 0.1578 1.0000
16.000 0.9369 0.10830 0.10143 0.0027 0.1497 1.0000
16.250 0.9466 0.11002 0.10316 0.0022 0.1407 1.0000
16.500 0.9704 0.10896 0.10204 0.0031 0.1306 1.0000
16.750 0.9312 0.12054 0.11384 -0.0024 0.1256 1.0000
17.000 0.9604 0.11824 0.11147 -0.0010 0.1163 1.0000
17.250 0.9105 0.13285 0.12628 -0.0084 0.1128 1.0000
17.500 0.9543 0.12710 0.12045 -0.0052 0.1037 1.0000
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Polar data table (+)
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