EPPLER 544 AIRFOIL (e544-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 544 AIRFOIL (e544-il) Reynolds number: 50,000 Max Cl/Cd: 18.51 at α=11.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e544-il-50000-n5.txt Download as CSV file: xf-e544-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 544 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4551 0.09957 0.09239 -0.0678 1.0000 0.0358
-12.250 -0.4715 0.09377 0.08659 -0.0702 1.0000 0.0356
-12.000 -0.4887 0.08861 0.08142 -0.0719 1.0000 0.0353
-11.750 -0.5081 0.08387 0.07666 -0.0729 1.0000 0.0350
-11.500 -0.5259 0.07984 0.07259 -0.0731 1.0000 0.0345
-11.250 -0.5491 0.07592 0.06861 -0.0725 1.0000 0.0344
-11.000 -0.5712 0.07262 0.06524 -0.0710 1.0000 0.0342
-10.750 -0.5947 0.06984 0.06238 -0.0686 1.0000 0.0342
-10.500 -0.6170 0.06765 0.06014 -0.0652 1.0000 0.0340
-10.250 -0.6414 0.06606 0.05851 -0.0607 1.0000 0.0339
-10.000 -0.6692 0.06503 0.05745 -0.0550 1.0000 0.0338
-9.750 -0.6968 0.06433 0.05673 -0.0489 1.0000 0.0335
-9.500 -0.7178 0.06285 0.05511 -0.0441 0.9984 0.0337
-9.250 -0.7108 0.05899 0.05077 -0.0450 0.9876 0.0343
-9.000 -0.6997 0.05536 0.04663 -0.0455 0.9776 0.0350
-8.750 -0.6810 0.05192 0.04264 -0.0461 0.9696 0.0355
-8.500 -0.6583 0.04893 0.03925 -0.0466 0.9616 0.0363
-8.250 -0.6241 0.04637 0.03650 -0.0487 0.9569 0.0379
-8.000 -0.5941 0.04439 0.03424 -0.0494 0.9496 0.0411
-7.500 -0.4768 0.04061 0.03006 -0.0559 0.9473 0.0544
-7.250 -0.4308 0.03947 0.02886 -0.0578 0.9440 0.0654
-7.000 -0.4043 0.03835 0.02777 -0.0579 0.9366 0.0791
-6.750 -0.3810 0.03700 0.02649 -0.0582 0.9295 0.1018
-6.500 -0.3703 0.03550 0.02530 -0.0571 0.9205 0.1339
-6.250 -0.3660 0.03351 0.02391 -0.0558 0.9121 0.1985
-5.750 -0.3307 0.03627 0.02861 -0.0461 0.8970 0.6021
-5.500 -0.3257 0.03739 0.02950 -0.0415 0.8867 0.6398
-5.250 -0.3044 0.03872 0.03050 -0.0389 0.8801 0.6765
-5.000 -0.2326 0.04127 0.03257 -0.0416 0.8792 0.7105
-4.750 -0.1645 0.04209 0.03294 -0.0463 0.8775 0.7315
-4.500 -0.1476 0.04215 0.03280 -0.0446 0.8686 0.7441
-4.250 -0.1151 0.04180 0.03217 -0.0460 0.8638 0.7544
-4.000 -0.0884 0.04158 0.03173 -0.0463 0.8568 0.7616
-3.750 -0.0705 0.04132 0.03128 -0.0454 0.8498 0.7700
-3.500 -0.0345 0.04080 0.03052 -0.0476 0.8459 0.7758
-3.250 -0.0233 0.04081 0.03041 -0.0454 0.8370 0.7820
-3.000 -0.0106 0.04049 0.02994 -0.0438 0.8311 0.7892
-2.750 0.0139 0.04035 0.02966 -0.0439 0.8244 0.7933
-2.500 0.0308 0.04019 0.02937 -0.0428 0.8180 0.7985
-2.250 0.0418 0.03987 0.02892 -0.0408 0.8131 0.8045
-2.000 0.0519 0.04004 0.02903 -0.0385 0.8046 0.8083
-1.750 0.0773 0.03978 0.02864 -0.0389 0.7999 0.8121
-1.500 0.0620 0.03999 0.02882 -0.0323 0.7915 0.8181
-1.250 0.0732 0.03992 0.02868 -0.0303 0.7855 0.8218
-1.000 0.1060 0.03961 0.02825 -0.0319 0.7820 0.8243
-0.750 0.0939 0.04001 0.02864 -0.0260 0.7730 0.8289
-0.500 0.0998 0.03988 0.02845 -0.0231 0.7677 0.8330
-0.250 0.0944 0.04002 0.02856 -0.0183 0.7607 0.8369
0.000 0.1042 0.04016 0.02865 -0.0162 0.7543 0.8398
0.250 0.1292 0.03997 0.02839 -0.0164 0.7506 0.8422
0.500 0.1001 0.04038 0.02882 -0.0080 0.7413 0.8472
0.750 0.1025 0.04024 0.02863 -0.0045 0.7358 0.8509
1.000 0.1371 0.04005 0.02838 -0.0063 0.7331 0.8522
1.250 0.1147 0.04072 0.02907 0.0006 0.7229 0.8561
1.500 0.1385 0.04061 0.02893 0.0006 0.7189 0.8586
2.000 0.1339 0.04103 0.02931 0.0081 0.7050 0.8654
2.250 0.1648 0.04091 0.02917 0.0071 0.7016 0.8671
2.500 0.1577 0.04161 0.02989 0.0111 0.6924 0.8706
2.750 0.1814 0.04163 0.02992 0.0111 0.6878 0.8730
3.250 0.1990 0.04224 0.03053 0.0147 0.6740 0.8787
3.500 0.2266 0.04214 0.03044 0.0143 0.6701 0.8811
3.750 0.2279 0.04290 0.03126 0.0167 0.6607 0.8843
4.000 0.2551 0.04298 0.03137 0.0163 0.6558 0.8867
4.250 0.2659 0.04350 0.03194 0.0176 0.6480 0.8899
4.500 0.2852 0.04376 0.03223 0.0179 0.6412 0.8926
4.750 0.3195 0.04357 0.03211 0.0168 0.6374 0.8947
5.000 0.3190 0.04456 0.03316 0.0190 0.6263 0.8984
5.250 0.3537 0.04442 0.03311 0.0179 0.6222 0.9007
5.500 0.3572 0.04540 0.03416 0.0196 0.6110 0.9048
5.750 0.3911 0.04521 0.03408 0.0186 0.6065 0.9078
6.000 0.3954 0.04620 0.03515 0.0201 0.5951 0.9122
6.250 0.4327 0.04588 0.03496 0.0188 0.5905 0.9147
6.500 0.4393 0.04695 0.03614 0.0199 0.5785 0.9188
6.750 0.4786 0.04641 0.03574 0.0186 0.5742 0.9218
7.000 0.4852 0.04753 0.03697 0.0196 0.5614 0.9268
7.250 0.5006 0.04837 0.03796 0.0197 0.5501 0.9315
7.500 0.5373 0.04788 0.03765 0.0187 0.5441 0.9358
7.750 0.5512 0.04888 0.03882 0.0186 0.5313 0.9412
8.250 0.6115 0.04881 0.03915 0.0168 0.5129 0.9514
8.500 0.6304 0.04968 0.04022 0.0161 0.4992 0.9579
8.750 0.6513 0.05033 0.04106 0.0153 0.4859 0.9666
9.250 0.7126 0.04905 0.04021 0.0143 0.4662 1.0000
9.500 0.7244 0.04963 0.04091 0.0151 0.4521 1.0000
9.750 0.7398 0.05005 0.04149 0.0155 0.4382 1.0000
10.000 0.7588 0.05022 0.04182 0.0158 0.4243 1.0000
10.250 0.7811 0.05007 0.04183 0.0161 0.4101 1.0000
10.500 0.8057 0.04970 0.04164 0.0163 0.3953 1.0000
10.750 0.8316 0.04920 0.04128 0.0167 0.3791 1.0000
11.000 0.8589 0.04855 0.04073 0.0171 0.3612 1.0000
11.250 0.8865 0.04790 0.04011 0.0176 0.3413 1.0000
11.500 0.8978 0.04902 0.04129 0.0180 0.3197 1.0000
11.750 0.9151 0.04950 0.04174 0.0185 0.2977 1.0000
12.000 0.9240 0.05094 0.04316 0.0190 0.2762 1.0000
12.250 0.9309 0.05263 0.04484 0.0194 0.2557 1.0000
12.500 0.9380 0.05430 0.04643 0.0198 0.2361 1.0000
12.750 0.9422 0.05639 0.04848 0.0201 0.2177 1.0000
13.000 0.9447 0.05878 0.05088 0.0202 0.2005 1.0000
13.250 0.9468 0.06127 0.05336 0.0202 0.1844 1.0000
13.500 0.9489 0.06384 0.05593 0.0201 0.1696 1.0000
13.750 0.9508 0.06652 0.05859 0.0200 0.1560 1.0000
14.000 0.9532 0.06920 0.06124 0.0197 0.1438 1.0000
14.250 0.9550 0.07202 0.06407 0.0194 0.1324 1.0000
14.500 0.9555 0.07524 0.06741 0.0189 0.1219 1.0000
14.750 0.9566 0.07838 0.07062 0.0183 0.1128 1.0000
15.000 0.9600 0.08110 0.07326 0.0178 0.1044 1.0000
15.250 0.9577 0.08505 0.07746 0.0168 0.0971 1.0000
15.500 0.9612 0.08792 0.08027 0.0162 0.0905 1.0000
15.750 0.9574 0.09229 0.08492 0.0149 0.0848 1.0000
16.000 0.9632 0.09477 0.08727 0.0143 0.0791 1.0000
16.250 0.9541 0.10027 0.09313 0.0122 0.0753 1.0000
16.500 0.9486 0.10508 0.09813 0.0103 0.0716 1.0000
16.750 0.9549 0.10761 0.10057 0.0095 0.0672 1.0000
17.000 0.9388 0.11473 0.10803 0.0061 0.0655 1.0000
17.250 0.9196 0.12277 0.11634 0.0020 0.0642 1.0000
17.500 0.8938 0.13275 0.12655 -0.0035 0.0637 1.0000
17.750 0.8564 0.14661 0.14053 -0.0113 0.0644 1.0000
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