EPPLER 473 AIRFOIL (e473-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 473 AIRFOIL (e473-il) Reynolds number: 50,000 Max Cl/Cd: 21.38 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e473-il-50000-n5.txt Download as CSV file: xf-e473-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 473 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6120 0.10851 0.09922 -0.0069 1.0000 0.1922
-11.750 -0.6087 0.10539 0.09608 -0.0076 1.0000 0.1964
-11.500 -0.6419 0.09720 0.08789 -0.0117 1.0000 0.2035
-11.250 -0.6203 0.09682 0.08748 -0.0104 1.0000 0.2063
-11.000 -0.6139 0.09429 0.08492 -0.0106 1.0000 0.2106
-10.750 -0.6627 0.08412 0.07479 -0.0158 1.0000 0.2188
-10.500 -0.6384 0.08425 0.07488 -0.0141 1.0000 0.2215
-10.250 -0.7509 0.06587 0.05653 -0.0244 1.0000 0.2339
-10.000 -0.7088 0.06808 0.05873 -0.0215 1.0000 0.2359
-9.750 -0.6860 0.06820 0.05883 -0.0197 1.0000 0.2390
-9.500 -0.8071 0.05505 0.04560 -0.0205 1.0000 0.2473
-9.250 -0.8351 0.05103 0.04143 -0.0176 1.0000 0.2518
-9.000 -0.8145 0.05051 0.04093 -0.0164 1.0000 0.2555
-8.750 -0.8162 0.04840 0.03871 -0.0142 1.0000 0.2602
-8.500 -0.8464 0.04426 0.03416 -0.0102 1.0000 0.2664
-8.250 -0.8206 0.04398 0.03398 -0.0093 1.0000 0.2698
-8.000 -0.8054 0.04300 0.03295 -0.0077 1.0000 0.2740
-7.750 -0.8014 0.04122 0.03099 -0.0054 1.0000 0.2793
-7.500 -0.7983 0.03932 0.02886 -0.0029 1.0000 0.2845
-7.250 -0.7768 0.03877 0.02836 -0.0017 1.0000 0.2884
-7.000 -0.7621 0.03773 0.02724 0.0000 1.0000 0.2930
-6.750 -0.7545 0.03615 0.02542 0.0022 1.0000 0.2986
-6.500 -0.7378 0.03521 0.02443 0.0037 1.0000 0.3029
-6.250 -0.7182 0.03455 0.02380 0.0051 1.0000 0.3071
-6.000 -0.7029 0.03358 0.02271 0.0067 1.0000 0.3123
-5.750 -0.6913 0.03233 0.02123 0.0087 1.0000 0.3179
-5.500 -0.6698 0.03179 0.02079 0.0099 1.0000 0.3217
-5.250 -0.6511 0.03113 0.02014 0.0113 1.0000 0.3264
-5.000 -0.6353 0.03028 0.01915 0.0129 1.0000 0.3320
-4.750 -0.6181 0.02952 0.01833 0.0144 1.0000 0.3367
-4.500 -0.5984 0.02901 0.01791 0.0158 1.0000 0.3411
-4.250 -0.5807 0.02842 0.01730 0.0172 1.0000 0.3463
-4.000 -0.5653 0.02775 0.01647 0.0189 1.0000 0.3523
-3.750 -0.5466 0.02734 0.01620 0.0202 1.0000 0.3564
-3.500 -0.5089 0.02690 0.01579 0.0178 0.9876 0.3629
-3.250 -0.4611 0.02629 0.01510 0.0135 0.9596 0.3711
-3.000 -0.4157 0.02578 0.01470 0.0103 0.9268 0.3780
-2.750 -0.3695 0.02517 0.01399 0.0070 0.8915 0.3868
-2.500 -0.3185 0.02465 0.01355 0.0031 0.8500 0.3946
-2.250 -0.2676 0.02415 0.01287 -0.0006 0.7999 0.4048
-2.000 -0.2229 0.02382 0.01244 -0.0029 0.7440 0.4129
-1.500 -0.1600 0.02355 0.01171 -0.0030 0.6485 0.4303
-1.250 -0.1335 0.02351 0.01141 -0.0024 0.6121 0.4405
-1.000 -0.1064 0.02347 0.01127 -0.0019 0.5822 0.4494
-0.750 -0.0799 0.02345 0.01110 -0.0014 0.5562 0.4604
-0.500 -0.0531 0.02343 0.01101 -0.0009 0.5346 0.4720
-0.250 -0.0263 0.02342 0.01096 -0.0005 0.5158 0.4849
0.000 0.0000 0.02342 0.01094 0.0000 0.4995 0.4995
0.250 0.0263 0.02342 0.01096 0.0005 0.4849 0.5158
0.500 0.0531 0.02343 0.01101 0.0009 0.4720 0.5346
0.750 0.0799 0.02345 0.01110 0.0014 0.4605 0.5563
1.000 0.1064 0.02347 0.01127 0.0019 0.4494 0.5822
1.250 0.1334 0.02350 0.01141 0.0024 0.4404 0.6120
1.500 0.1600 0.02355 0.01171 0.0030 0.4302 0.6484
2.000 0.2229 0.02382 0.01244 0.0029 0.4129 0.7440
2.250 0.2676 0.02415 0.01287 0.0006 0.4048 0.8000
2.500 0.3185 0.02464 0.01355 -0.0031 0.3946 0.8500
2.750 0.3694 0.02516 0.01399 -0.0070 0.3868 0.8914
3.000 0.4158 0.02578 0.01470 -0.0103 0.3780 0.9269
3.250 0.4610 0.02629 0.01510 -0.0135 0.3712 0.9596
3.500 0.5089 0.02689 0.01579 -0.0178 0.3629 0.9876
3.750 0.5466 0.02733 0.01619 -0.0202 0.3564 1.0000
4.000 0.5653 0.02775 0.01647 -0.0189 0.3523 1.0000
4.250 0.5807 0.02843 0.01730 -0.0172 0.3463 1.0000
4.500 0.5983 0.02901 0.01790 -0.0158 0.3411 1.0000
4.750 0.6181 0.02952 0.01833 -0.0144 0.3367 1.0000
5.000 0.6353 0.03028 0.01915 -0.0129 0.3320 1.0000
5.250 0.6511 0.03113 0.02014 -0.0113 0.3264 1.0000
5.500 0.6698 0.03178 0.02078 -0.0099 0.3217 1.0000
5.750 0.6913 0.03233 0.02123 -0.0087 0.3179 1.0000
6.000 0.7029 0.03357 0.02271 -0.0067 0.3123 1.0000
6.250 0.7182 0.03454 0.02379 -0.0051 0.3071 1.0000
6.500 0.7378 0.03521 0.02443 -0.0037 0.3029 1.0000
6.750 0.7544 0.03615 0.02542 -0.0022 0.2986 1.0000
7.000 0.7621 0.03772 0.02723 0.0000 0.2930 1.0000
7.250 0.7769 0.03875 0.02834 0.0017 0.2883 1.0000
7.500 0.7983 0.03932 0.02886 0.0029 0.2845 1.0000
7.750 0.8014 0.04121 0.03098 0.0054 0.2793 1.0000
8.000 0.8054 0.04301 0.03296 0.0077 0.2740 1.0000
8.250 0.8208 0.04397 0.03396 0.0092 0.2698 1.0000
8.500 0.8469 0.04423 0.03413 0.0101 0.2665 1.0000
8.750 0.8164 0.04840 0.03870 0.0141 0.2602 1.0000
9.000 0.8149 0.05049 0.04091 0.0163 0.2554 1.0000
9.250 0.8353 0.05103 0.04144 0.0176 0.2518 1.0000
9.500 0.8068 0.05509 0.04564 0.0205 0.2473 1.0000
9.750 0.6866 0.06819 0.05882 0.0197 0.2390 1.0000
10.000 0.7091 0.06811 0.05876 0.0214 0.2359 1.0000
10.250 0.7518 0.06583 0.05649 0.0244 0.2339 1.0000
10.500 0.6391 0.08426 0.07489 0.0140 0.2215 1.0000
10.750 0.6642 0.08399 0.07466 0.0158 0.2187 1.0000
11.250 0.6214 0.09678 0.08744 0.0103 0.2063 1.0000
11.500 0.6439 0.09701 0.08771 0.0117 0.2034 1.0000
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Polar data table (+)
Polar graphs
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