EPPLER 472 AIRFOIL (e472-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER 472 AIRFOIL (e472-il) Reynolds number: 50,000 Max Cl/Cd: 17.46 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e472-il-50000.txt Download as CSV file: xf-e472-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 472 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5697 0.14406 0.13544 0.0217 1.0000 0.2965
-11.750 -0.5466 0.13932 0.13064 0.0220 1.0000 0.3042
-11.500 -0.5781 0.14035 0.13177 0.0205 1.0000 0.3119
-11.250 -0.5351 0.13315 0.12445 0.0214 1.0000 0.3206
-11.000 -0.5581 0.13279 0.12418 0.0204 1.0000 0.3293
-10.750 -0.5234 0.12707 0.11837 0.0210 1.0000 0.3382
-10.500 -0.5414 0.12588 0.11725 0.0204 1.0000 0.3467
-10.250 -0.5125 0.12113 0.11243 0.0208 1.0000 0.3568
-10.000 -0.5130 0.11836 0.10968 0.0207 1.0000 0.3664
-9.750 -0.5218 0.11712 0.10848 0.0210 1.0000 0.3792
-9.500 -0.4931 0.11212 0.10342 0.0211 1.0000 0.3873
-9.000 -0.4915 0.10740 0.09875 0.0218 1.0000 0.4122
-8.750 -0.4715 0.10358 0.09490 0.0222 1.0000 0.4238
-8.500 -0.4679 0.10084 0.09219 0.0226 1.0000 0.4360
-8.000 -0.4678 0.09660 0.08801 0.0243 1.0000 0.4645
-7.750 -0.4438 0.09289 0.08427 0.0246 1.0000 0.4786
-7.500 -0.4319 0.09007 0.08147 0.0253 1.0000 0.4945
-7.250 -0.6389 0.06912 0.06074 0.0031 1.0000 0.3123
-7.000 -0.6386 0.06460 0.05616 0.0028 1.0000 0.3099
-6.750 -0.6434 0.05984 0.05133 0.0025 1.0000 0.3078
-6.500 -0.6516 0.05481 0.04616 0.0023 1.0000 0.3057
-6.250 -0.6568 0.05042 0.04155 0.0028 1.0000 0.3070
-6.000 -0.6597 0.04641 0.03721 0.0037 1.0000 0.3102
-5.750 -0.6492 0.04370 0.03437 0.0049 1.0000 0.3143
-5.500 -0.6332 0.04169 0.03230 0.0062 1.0000 0.3189
-5.250 -0.6219 0.03932 0.02969 0.0076 1.0000 0.3245
-5.000 -0.6099 0.03705 0.02716 0.0090 1.0000 0.3306
-4.750 -0.5902 0.03566 0.02578 0.0103 1.0000 0.3371
-4.500 -0.5753 0.03374 0.02358 0.0116 1.0000 0.3434
-4.250 -0.5560 0.03232 0.02214 0.0130 1.0000 0.3504
-4.000 -0.5373 0.03102 0.02072 0.0143 1.0000 0.3590
-3.750 -0.5180 0.02967 0.01928 0.0156 1.0000 0.3666
-3.500 -0.4973 0.02854 0.01811 0.0168 1.0000 0.3750
-3.250 -0.4770 0.02744 0.01697 0.0180 1.0000 0.3846
-3.000 -0.4564 0.02647 0.01589 0.0192 1.0000 0.3954
-2.750 -0.4344 0.02554 0.01506 0.0204 1.0000 0.4053
-2.500 -0.4129 0.02465 0.01413 0.0215 1.0000 0.4170
-2.250 -0.3915 0.02389 0.01335 0.0226 1.0000 0.4310
-2.000 -0.3691 0.02316 0.01276 0.0237 1.0000 0.4452
-1.750 -0.3465 0.02246 0.01218 0.0247 1.0000 0.4610
-1.500 -0.3242 0.02183 0.01165 0.0257 1.0000 0.4805
-1.250 -0.3010 0.02122 0.01125 0.0266 1.0000 0.5031
-1.000 -0.2785 0.02067 0.01092 0.0276 1.0000 0.5308
-0.750 -0.2569 0.02013 0.01067 0.0288 1.0000 0.5669
-0.500 -0.2369 0.01956 0.01057 0.0303 1.0000 0.6171
-0.250 -0.2185 0.01888 0.01065 0.0326 1.0000 0.7008
0.000 0.0000 0.01901 0.01158 0.0000 1.0000 1.0000
0.250 0.2185 0.01888 0.01065 -0.0326 0.7006 1.0000
0.500 0.2370 0.01956 0.01057 -0.0303 0.6170 1.0000
0.750 0.2568 0.02013 0.01067 -0.0288 0.5666 1.0000
1.000 0.2785 0.02067 0.01092 -0.0276 0.5308 1.0000
1.250 0.3010 0.02122 0.01125 -0.0266 0.5032 1.0000
1.500 0.3242 0.02183 0.01165 -0.0257 0.4805 1.0000
1.750 0.3465 0.02246 0.01218 -0.0247 0.4611 1.0000
2.000 0.3690 0.02316 0.01276 -0.0237 0.4453 1.0000
2.250 0.3915 0.02389 0.01334 -0.0226 0.4311 1.0000
2.500 0.4129 0.02465 0.01413 -0.0215 0.4170 1.0000
2.750 0.4344 0.02554 0.01506 -0.0204 0.4053 1.0000
3.000 0.4564 0.02647 0.01589 -0.0192 0.3953 1.0000
3.250 0.4770 0.02744 0.01695 -0.0180 0.3845 1.0000
3.500 0.4973 0.02854 0.01810 -0.0168 0.3750 1.0000
3.750 0.5179 0.02967 0.01928 -0.0156 0.3666 1.0000
4.000 0.5373 0.03102 0.02071 -0.0143 0.3590 1.0000
4.250 0.5560 0.03232 0.02214 -0.0130 0.3505 1.0000
4.500 0.5753 0.03374 0.02358 -0.0116 0.3433 1.0000
4.750 0.5901 0.03565 0.02578 -0.0103 0.3371 1.0000
5.000 0.6098 0.03705 0.02716 -0.0090 0.3306 1.0000
5.250 0.6219 0.03932 0.02969 -0.0076 0.3245 1.0000
5.500 0.6332 0.04169 0.03230 -0.0062 0.3189 1.0000
5.750 0.6491 0.04371 0.03438 -0.0050 0.3144 1.0000
6.000 0.6599 0.04639 0.03718 -0.0037 0.3103 1.0000
6.250 0.6569 0.05042 0.04155 -0.0028 0.3071 1.0000
6.500 0.6516 0.05483 0.04617 -0.0023 0.3057 1.0000
6.750 0.6435 0.05984 0.05132 -0.0025 0.3077 1.0000
7.000 0.6394 0.06456 0.05612 -0.0028 0.3100 1.0000
7.250 0.6399 0.06905 0.06068 -0.0031 0.3122 1.0000
7.500 0.4328 0.09008 0.08148 -0.0254 0.4948 1.0000
7.750 0.4464 0.09302 0.08442 -0.0248 0.4794 1.0000
8.000 0.4679 0.09655 0.08796 -0.0244 0.4644 1.0000
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Polar data table (+)
Polar graphs
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