LA2573A (la2573a-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: LA2573A (la2573a-il) Reynolds number: 50,000 Max Cl/Cd: 13.45 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-la2573a-il-50000-n5.txt Download as CSV file: xf-la2573a-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LA2573A
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4220 0.10877 0.10141 0.0164 0.6125 0.1582
-8.250 -0.4202 0.10553 0.09817 0.0145 0.6090 0.1616
-7.750 -0.4538 0.08910 0.08161 -0.0013 0.6072 0.0912
-7.250 -0.4726 0.07887 0.07113 -0.0065 0.6028 0.0819
-7.000 -0.4649 0.07540 0.06764 -0.0072 0.5987 0.0807
-6.750 -0.4602 0.07172 0.06384 -0.0080 0.5951 0.0798
-6.500 -0.4551 0.06805 0.06000 -0.0086 0.5918 0.0794
-6.250 -0.4483 0.06455 0.05627 -0.0089 0.5887 0.0794
-6.000 -0.4393 0.06122 0.05267 -0.0089 0.5860 0.0793
-5.750 -0.4273 0.05803 0.04920 -0.0089 0.5831 0.0792
-5.500 -0.4129 0.05496 0.04587 -0.0089 0.5797 0.0787
-5.250 -0.3969 0.05209 0.04269 -0.0087 0.5763 0.0782
-5.000 -0.3795 0.04948 0.03974 -0.0082 0.5729 0.0779
-4.750 -0.3608 0.04712 0.03701 -0.0075 0.5697 0.0779
-4.500 -0.3409 0.04512 0.03463 -0.0067 0.5667 0.0789
-4.250 -0.3193 0.04328 0.03240 -0.0061 0.5636 0.0804
-4.000 -0.2955 0.04155 0.03028 -0.0059 0.5599 0.0817
-3.750 -0.2707 0.03998 0.02833 -0.0056 0.5565 0.0825
-3.500 -0.2450 0.03860 0.02675 -0.0054 0.5533 0.0832
-3.250 -0.2188 0.03744 0.02547 -0.0052 0.5502 0.0845
-3.000 -0.1928 0.03651 0.02439 -0.0048 0.5473 0.0867
-2.750 -0.1659 0.03567 0.02333 -0.0045 0.5445 0.0897
-2.500 -0.1363 0.03495 0.02241 -0.0049 0.5406 0.0923
-2.250 -0.1066 0.03421 0.02166 -0.0054 0.5372 0.0944
-2.000 -0.0769 0.03367 0.02112 -0.0057 0.5340 0.0977
-1.750 -0.0463 0.03324 0.02058 -0.0059 0.5309 0.1028
-1.500 -0.0154 0.03276 0.02005 -0.0062 0.5280 0.1076
-1.250 0.0134 0.03238 0.01960 -0.0060 0.5256 0.1130
-1.000 0.0423 0.03232 0.01959 -0.0068 0.5219 0.1208
-0.750 0.0691 0.03231 0.01964 -0.0072 0.5184 0.1305
-0.500 0.0935 0.03224 0.01967 -0.0070 0.5151 0.1434
-0.250 0.1167 0.03208 0.01963 -0.0065 0.5120 0.1666
0.000 0.1362 0.03141 0.01953 -0.0054 0.5094 0.2419
0.500 0.3263 0.03095 0.02078 -0.0268 0.5010 1.0000
0.750 0.3489 0.03180 0.02155 -0.0271 0.4970 1.0000
1.000 0.3705 0.03252 0.02217 -0.0269 0.4935 1.0000
1.250 0.3914 0.03315 0.02269 -0.0263 0.4905 1.0000
1.500 0.4121 0.03373 0.02314 -0.0254 0.4881 1.0000
1.750 0.4325 0.03426 0.02353 -0.0243 0.4861 1.0000
2.000 0.4516 0.03570 0.02501 -0.0250 0.4817 1.0000
2.250 0.4691 0.03717 0.02652 -0.0255 0.4768 1.0000
2.500 0.4864 0.03830 0.02762 -0.0250 0.4731 1.0000
2.750 0.5041 0.03917 0.02843 -0.0241 0.4700 1.0000
3.000 0.5226 0.03982 0.02900 -0.0227 0.4675 1.0000
3.250 0.5420 0.04031 0.02940 -0.0211 0.4655 1.0000
3.500 0.5433 0.04360 0.03286 -0.0226 0.4579 1.0000
3.750 0.5535 0.04516 0.03443 -0.0219 0.4534 1.0000
4.000 0.5680 0.04613 0.03536 -0.0205 0.4501 1.0000
4.250 0.5853 0.04680 0.03598 -0.0188 0.4475 1.0000
4.750 0.5779 0.05218 0.04142 -0.0179 0.4351 1.0000
5.000 0.5889 0.05338 0.04260 -0.0165 0.4312 1.0000
5.250 0.6068 0.05407 0.04324 -0.0148 0.4285 1.0000
5.500 0.6271 0.05461 0.04374 -0.0131 0.4264 1.0000
5.750 0.5863 0.05966 0.04882 -0.0131 0.4155 1.0000
6.000 0.5998 0.06072 0.04985 -0.0117 0.4118 1.0000
6.250 0.6222 0.06132 0.05044 -0.0104 0.4092 1.0000
6.500 0.5891 0.06508 0.05415 -0.0089 0.4006 1.0000
6.750 0.5981 0.06654 0.05561 -0.0079 0.3958 1.0000
7.000 0.6189 0.06737 0.05643 -0.0069 0.3927 1.0000
7.250 0.6085 0.07022 0.05927 -0.0064 0.3856 1.0000
7.500 0.6139 0.07207 0.06114 -0.0058 0.3799 1.0000
7.750 0.6342 0.07298 0.06205 -0.0049 0.3763 1.0000
8.000 0.6292 0.07570 0.06478 -0.0048 0.3695 1.0000
8.250 0.6364 0.07754 0.06664 -0.0044 0.3635 1.0000
8.500 0.6584 0.07833 0.06747 -0.0036 0.3601 1.0000
9.000 0.6638 0.08287 0.07206 -0.0034 0.3469 1.0000
9.250 0.6896 0.08334 0.07256 -0.0024 0.3438 1.0000
9.500 0.6747 0.08716 0.07642 -0.0033 0.3342 1.0000
9.750 0.6974 0.08779 0.07710 -0.0024 0.3301 1.0000
10.000 0.6900 0.09117 0.08052 -0.0031 0.3217 1.0000
10.250 0.7085 0.09209 0.08149 -0.0025 0.3165 1.0000
10.500 0.7083 0.09490 0.08435 -0.0029 0.3090 1.0000
10.750 0.7221 0.09625 0.08576 -0.0025 0.3028 1.0000
11.000 0.7270 0.09856 0.08812 -0.0027 0.2956 1.0000
11.250 0.7380 0.10015 0.08980 -0.0025 0.2886 1.0000
11.500 0.7431 0.10241 0.09210 -0.0028 0.2809 1.0000
11.750 0.7567 0.10360 0.09337 -0.0024 0.2738 1.0000
12.000 0.7576 0.10635 0.09617 -0.0030 0.2649 1.0000
12.250 0.7785 0.10645 0.09637 -0.0020 0.2586 1.0000
12.750 0.8043 0.10844 0.09850 -0.0013 0.2431 1.0000
13.000 0.7976 0.11235 0.10247 -0.0027 0.2317 1.0000
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Polar data table (+)
Polar graphs
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