EPPLER 544 AIRFOIL (e544-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 544 AIRFOIL (e544-il) Reynolds number: 500,000 Max Cl/Cd: 86.21 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e544-il-500000-n5.txt Download as CSV file: xf-e544-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.5951 0.09480 0.09219 -0.0578 1.0000 0.0035
-14.750 -0.6230 0.08302 0.08025 -0.0648 1.0000 0.0034
-14.500 -0.6568 0.07245 0.06946 -0.0709 1.0000 0.0033
-14.250 -0.6800 0.06551 0.06234 -0.0740 1.0000 0.0033
-14.000 -0.7060 0.05912 0.05572 -0.0757 1.0000 0.0033
-13.750 -0.7238 0.05450 0.05092 -0.0761 1.0000 0.0033
-13.500 -0.7363 0.05091 0.04716 -0.0758 1.0000 0.0033
-13.250 -0.7508 0.04730 0.04335 -0.0748 1.0000 0.0033
-13.000 -0.7652 0.04385 0.03966 -0.0733 1.0000 0.0033
-12.750 -0.7718 0.04134 0.03698 -0.0716 1.0000 0.0032
-12.500 -0.7777 0.03895 0.03441 -0.0696 1.0000 0.0033
-12.250 -0.7676 0.03618 0.03140 -0.0708 0.9973 0.0033
-12.000 -0.7584 0.03390 0.02893 -0.0707 0.9856 0.0033
-11.750 -0.7453 0.03188 0.02672 -0.0710 0.9647 0.0034
-11.500 -0.7172 0.02994 0.02458 -0.0741 0.9518 0.0034
-11.000 -0.6399 0.02619 0.02040 -0.0838 0.9325 0.0036
-10.750 -0.5957 0.02463 0.01864 -0.0895 0.9183 0.0037
-10.500 -0.5572 0.02342 0.01725 -0.0936 0.8984 0.0038
-10.250 -0.5324 0.02253 0.01617 -0.0947 0.8777 0.0038
-10.000 -0.5167 0.02167 0.01516 -0.0939 0.8594 0.0039
-9.750 -0.5027 0.02092 0.01429 -0.0927 0.8440 0.0041
-9.250 -0.4734 0.01969 0.01287 -0.0899 0.8179 0.0045
-9.000 -0.4584 0.01913 0.01222 -0.0885 0.8069 0.0048
-8.750 -0.4435 0.01859 0.01158 -0.0871 0.7968 0.0049
-8.500 -0.4280 0.01807 0.01098 -0.0857 0.7874 0.0053
-8.250 -0.4126 0.01757 0.01039 -0.0843 0.7791 0.0055
-8.000 -0.3979 0.01702 0.00979 -0.0827 0.7706 0.0060
-7.750 -0.3831 0.01652 0.00922 -0.0811 0.7630 0.0065
-7.500 -0.3673 0.01607 0.00870 -0.0797 0.7552 0.0072
-7.250 -0.3517 0.01565 0.00820 -0.0781 0.7477 0.0077
-7.000 -0.3371 0.01517 0.00769 -0.0765 0.7405 0.0086
-6.750 -0.3222 0.01476 0.00723 -0.0748 0.7340 0.0103
-6.500 -0.3085 0.01432 0.00676 -0.0729 0.7279 0.0129
-6.000 -0.2877 0.01356 0.00598 -0.0676 0.7159 0.0239
-5.750 -0.2740 0.01317 0.00564 -0.0655 0.7100 0.0363
-5.500 -0.2585 0.01280 0.00531 -0.0638 0.7042 0.0516
-5.250 -0.2434 0.01238 0.00498 -0.0620 0.6991 0.0768
-5.000 -0.2277 0.01191 0.00465 -0.0603 0.6940 0.1137
-4.750 -0.2134 0.01133 0.00429 -0.0584 0.6890 0.1686
-4.500 -0.2021 0.01052 0.00383 -0.0563 0.6847 0.2608
-4.250 -0.1936 0.00931 0.00320 -0.0538 0.6800 0.4028
-4.000 -0.1825 0.00826 0.00286 -0.0515 0.6751 0.5752
-3.750 -0.1558 0.00830 0.00292 -0.0513 0.6707 0.6137
-3.500 -0.1280 0.00840 0.00297 -0.0514 0.6668 0.6331
-3.250 -0.1000 0.00855 0.00308 -0.0514 0.6627 0.6489
-3.000 -0.0720 0.00873 0.00318 -0.0515 0.6587 0.6615
-2.750 -0.0439 0.00900 0.00344 -0.0514 0.6549 0.6707
-2.500 -0.0159 0.00911 0.00345 -0.0515 0.6512 0.6770
-2.250 0.0125 0.00909 0.00339 -0.0518 0.6472 0.6782
-2.000 0.0409 0.00908 0.00333 -0.0521 0.6434 0.6792
-1.750 0.0691 0.00908 0.00328 -0.0524 0.6400 0.6802
-1.500 0.0974 0.00909 0.00322 -0.0526 0.6367 0.6811
-1.250 0.1259 0.00907 0.00318 -0.0530 0.6332 0.6821
-1.000 0.1542 0.00907 0.00314 -0.0533 0.6294 0.6830
-0.750 0.1825 0.00908 0.00310 -0.0536 0.6261 0.6841
-0.500 0.2107 0.00910 0.00307 -0.0539 0.6229 0.6853
-0.250 0.2390 0.00911 0.00305 -0.0542 0.6197 0.6864
0.000 0.2674 0.00911 0.00303 -0.0545 0.6163 0.6874
0.250 0.2957 0.00911 0.00301 -0.0549 0.6128 0.6884
0.500 0.3238 0.00913 0.00299 -0.0552 0.6095 0.6894
0.750 0.3519 0.00917 0.00298 -0.0554 0.6063 0.6904
1.000 0.3802 0.00918 0.00299 -0.0558 0.6030 0.6914
1.250 0.4084 0.00920 0.00300 -0.0561 0.5992 0.6924
1.500 0.4362 0.00922 0.00301 -0.0563 0.5950 0.6934
1.750 0.4636 0.00926 0.00303 -0.0564 0.5908 0.6943
2.000 0.4913 0.00928 0.00307 -0.0566 0.5863 0.6951
2.250 0.5189 0.00931 0.00311 -0.0568 0.5816 0.6960
2.500 0.5463 0.00935 0.00316 -0.0569 0.5772 0.6968
2.750 0.5736 0.00941 0.00321 -0.0571 0.5729 0.6978
3.000 0.6009 0.00943 0.00328 -0.0572 0.5677 0.6987
3.250 0.6278 0.00948 0.00334 -0.0572 0.5622 0.6997
3.500 0.6546 0.00955 0.00340 -0.0573 0.5572 0.7007
3.750 0.6817 0.00959 0.00348 -0.0574 0.5514 0.7018
4.000 0.7080 0.00965 0.00356 -0.0573 0.5453 0.7028
4.250 0.7344 0.00972 0.00364 -0.0573 0.5389 0.7041
4.500 0.7603 0.00979 0.00373 -0.0571 0.5312 0.7054
4.750 0.7860 0.00988 0.00383 -0.0570 0.5234 0.7066
5.000 0.8111 0.00997 0.00393 -0.0567 0.5141 0.7076
5.250 0.8361 0.01006 0.00404 -0.0564 0.5040 0.7086
5.500 0.8598 0.01017 0.00416 -0.0558 0.4923 0.7096
5.750 0.8823 0.01031 0.00430 -0.0550 0.4775 0.7106
6.000 0.9035 0.01048 0.00446 -0.0540 0.4592 0.7117
6.250 0.9217 0.01075 0.00467 -0.0524 0.4359 0.7128
6.500 0.9377 0.01109 0.00493 -0.0505 0.4088 0.7139
6.750 0.9510 0.01149 0.00523 -0.0480 0.3810 0.7152
7.000 0.9606 0.01192 0.00556 -0.0449 0.3542 0.7165
7.250 0.9701 0.01241 0.00595 -0.0418 0.3286 0.7179
7.500 0.9806 0.01293 0.00639 -0.0391 0.3047 0.7195
8.000 0.9995 0.01412 0.00741 -0.0335 0.2575 0.7227
8.500 1.0154 0.01550 0.00862 -0.0279 0.2131 0.7254
8.750 1.0238 0.01621 0.00929 -0.0254 0.1945 0.7268
9.000 1.0308 0.01702 0.01005 -0.0228 0.1760 0.7282
9.250 1.0374 0.01790 0.01087 -0.0203 0.1574 0.7297
9.500 1.0451 0.01879 0.01172 -0.0181 0.1416 0.7313
9.750 1.0532 0.01972 0.01263 -0.0161 0.1281 0.7329
10.000 1.0610 0.02071 0.01359 -0.0141 0.1149 0.7346
10.250 1.0690 0.02174 0.01460 -0.0123 0.1036 0.7363
10.500 1.0771 0.02281 0.01565 -0.0107 0.0927 0.7380
10.750 1.0856 0.02390 0.01673 -0.0091 0.0830 0.7396
11.000 1.0933 0.02508 0.01791 -0.0076 0.0738 0.7413
11.250 1.1000 0.02634 0.01917 -0.0061 0.0648 0.7432
11.500 1.1066 0.02765 0.02048 -0.0047 0.0572 0.7451
11.750 1.1145 0.02893 0.02179 -0.0035 0.0501 0.7471
12.000 1.1221 0.03026 0.02314 -0.0024 0.0446 0.7491
12.250 1.1286 0.03172 0.02461 -0.0013 0.0392 0.7511
12.500 1.1362 0.03314 0.02606 -0.0003 0.0347 0.7532
12.750 1.1433 0.03465 0.02760 0.0006 0.0310 0.7552
13.000 1.1501 0.03621 0.02920 0.0014 0.0276 0.7571
13.250 1.1571 0.03778 0.03083 0.0021 0.0248 0.7591
13.500 1.1634 0.03947 0.03256 0.0028 0.0223 0.7614
13.750 1.1702 0.04115 0.03431 0.0034 0.0199 0.7638
14.000 1.1758 0.04300 0.03620 0.0039 0.0179 0.7663
14.250 1.1823 0.04481 0.03808 0.0043 0.0161 0.7689
14.500 1.1880 0.04675 0.04009 0.0046 0.0147 0.7715
14.750 1.1933 0.04878 0.04219 0.0049 0.0133 0.7741
15.000 1.1984 0.05083 0.04433 0.0051 0.0122 0.7772
15.250 1.2023 0.05308 0.04665 0.0052 0.0110 0.7806
15.500 1.2071 0.05532 0.04898 0.0052 0.0099 0.7842
15.750 1.2104 0.05777 0.05150 0.0051 0.0089 0.7877
16.000 1.2140 0.06020 0.05403 0.0049 0.0081 0.7914
16.250 1.2168 0.06280 0.05676 0.0047 0.0076 0.7954
16.500 1.2194 0.06549 0.05954 0.0043 0.0072 0.7998
17.000 1.2213 0.07149 0.06575 0.0032 0.0059 0.8090
17.250 1.2216 0.07464 0.06902 0.0024 0.0055 0.8146
17.750 1.2192 0.08159 0.07620 0.0005 0.0048 0.8273
18.000 1.2173 0.08529 0.08004 -0.0006 0.0045 0.8352
18.250 1.2149 0.08908 0.08399 -0.0018 0.0043 0.8448
18.500 1.2111 0.09309 0.08815 -0.0032 0.0040 0.8568
18.750 1.2067 0.09716 0.09239 -0.0046 0.0038 0.8755
19.000 1.2032 0.10183 0.09730 -0.0070 0.0036 0.9371
19.250 1.1975 0.10650 0.10210 -0.0093 0.0035 1.0000
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Polar data table (+)
Polar graphs
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