EPPLER 473 AIRFOIL (e473-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 473 AIRFOIL (e473-il) Reynolds number: 50,000 Max Cl/Cd: 15.79 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e473-il-50000.txt Download as CSV file: xf-e473-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4221 0.11729 0.10818 0.0153 1.0000 0.4395
-9.750 -0.4024 0.11319 0.10406 0.0149 1.0000 0.4464
-9.500 -0.4208 0.11302 0.10394 0.0161 1.0000 0.4592
-9.250 -0.3810 0.10797 0.09882 0.0153 1.0000 0.4691
-9.000 -0.3834 0.10595 0.09683 0.0159 1.0000 0.4797
-8.750 -0.3761 0.10401 0.09489 0.0165 1.0000 0.4928
-8.500 -0.3540 0.10035 0.09122 0.0162 1.0000 0.5023
-8.250 -0.3546 0.09852 0.08942 0.0171 1.0000 0.5154
-8.000 -0.3609 0.09776 0.08869 0.0188 1.0000 0.5303
-7.750 -0.3233 0.09311 0.08402 0.0174 1.0000 0.5388
-7.500 -0.3190 0.09111 0.08204 0.0183 1.0000 0.5524
-7.250 -0.3182 0.08960 0.08057 0.0198 1.0000 0.5680
-7.000 -0.3102 0.08795 0.07894 0.0209 1.0000 0.5839
-6.750 -0.2772 0.08398 0.07497 0.0195 1.0000 0.5929
-6.500 -0.2680 0.08191 0.07294 0.0204 1.0000 0.6077
-6.250 -0.4693 0.06871 0.05987 0.0134 1.0000 0.4410
-6.000 -0.4673 0.06533 0.05652 0.0139 1.0000 0.4394
-5.750 -0.4786 0.06149 0.05273 0.0149 1.0000 0.4365
-5.500 -0.5071 0.05664 0.04792 0.0160 1.0000 0.4336
-5.250 -0.5333 0.05211 0.04338 0.0176 1.0000 0.4345
-5.000 -0.5545 0.04796 0.03916 0.0195 1.0000 0.4370
-4.750 -0.5719 0.04406 0.03509 0.0214 1.0000 0.4402
-4.500 -0.5589 0.04247 0.03355 0.0231 1.0000 0.4445
-4.250 -0.5471 0.04104 0.03215 0.0249 1.0000 0.4500
-4.000 -0.5466 0.03885 0.02984 0.0268 1.0000 0.4556
-3.750 -0.5424 0.03697 0.02788 0.0287 1.0000 0.4606
-3.500 -0.5291 0.03600 0.02699 0.0306 1.0000 0.4657
-3.250 -0.5229 0.03473 0.02568 0.0325 1.0000 0.4713
-3.000 -0.5216 0.03336 0.02417 0.0346 1.0000 0.4773
-2.750 -0.5140 0.03292 0.02389 0.0367 1.0000 0.4822
-2.500 -0.5132 0.03253 0.02353 0.0385 0.9995 0.4873
-2.250 -0.4108 0.03178 0.02278 0.0231 0.9543 0.5020
-2.000 -0.3206 0.03051 0.02150 0.0115 0.9078 0.5172
-1.750 -0.2388 0.02908 0.02003 0.0025 0.8610 0.5325
-1.500 -0.1762 0.02806 0.01889 -0.0023 0.8118 0.5472
-1.250 -0.1329 0.02752 0.01821 -0.0035 0.7664 0.5589
-1.000 -0.1039 0.02716 0.01764 -0.0030 0.7292 0.5706
-0.750 -0.0803 0.02697 0.01727 -0.0019 0.6975 0.5841
-0.500 -0.0520 0.02689 0.01715 -0.0013 0.6717 0.5975
-0.250 -0.0261 0.02682 0.01706 -0.0006 0.6486 0.6122
0.000 0.0000 0.02679 0.01701 0.0000 0.6291 0.6290
0.250 0.0261 0.02683 0.01706 0.0006 0.6122 0.6486
0.500 0.0520 0.02689 0.01715 0.0013 0.5975 0.6715
0.750 0.0804 0.02697 0.01727 0.0019 0.5842 0.6975
1.000 0.1039 0.02716 0.01764 0.0030 0.5706 0.7292
1.250 0.1328 0.02752 0.01821 0.0036 0.5589 0.7664
1.500 0.1760 0.02805 0.01888 0.0023 0.5471 0.8116
1.750 0.2387 0.02908 0.02003 -0.0025 0.5325 0.8610
2.000 0.3205 0.03051 0.02151 -0.0115 0.5173 0.9078
2.250 0.4108 0.03179 0.02278 -0.0231 0.5020 0.9543
2.500 0.5135 0.03252 0.02352 -0.0386 0.4872 0.9997
2.750 0.5140 0.03291 0.02387 -0.0367 0.4821 1.0000
3.000 0.5215 0.03336 0.02417 -0.0346 0.4773 1.0000
3.250 0.5228 0.03472 0.02567 -0.0325 0.4714 1.0000
3.500 0.5290 0.03599 0.02698 -0.0306 0.4656 1.0000
3.750 0.5423 0.03697 0.02787 -0.0287 0.4607 1.0000
4.000 0.5466 0.03884 0.02984 -0.0268 0.4555 1.0000
4.250 0.5471 0.04104 0.03215 -0.0249 0.4500 1.0000
4.500 0.5587 0.04247 0.03356 -0.0231 0.4446 1.0000
4.750 0.5721 0.04405 0.03507 -0.0214 0.4402 1.0000
5.000 0.5545 0.04795 0.03915 -0.0195 0.4370 1.0000
5.250 0.5335 0.05209 0.04336 -0.0176 0.4344 1.0000
5.500 0.5072 0.05663 0.04791 -0.0160 0.4337 1.0000
5.750 0.4787 0.06149 0.05273 -0.0149 0.4365 1.0000
6.000 0.4670 0.06534 0.05653 -0.0139 0.4393 1.0000
6.250 0.4691 0.06869 0.05985 -0.0135 0.4410 1.0000
7.500 0.3195 0.09107 0.08199 -0.0184 0.5525 1.0000
7.750 0.3241 0.09310 0.08400 -0.0175 0.5387 1.0000
8.000 0.3639 0.09792 0.08885 -0.0190 0.5304 1.0000
8.250 0.3550 0.09848 0.08938 -0.0172 0.5155 1.0000
8.500 0.3546 0.10033 0.09120 -0.0163 0.5025 1.0000
8.750 0.3785 0.10412 0.09500 -0.0167 0.4931 1.0000
9.000 0.3841 0.10593 0.09680 -0.0160 0.4797 1.0000
9.250 0.3820 0.10796 0.09881 -0.0154 0.4693 1.0000
9.500 0.4212 0.11297 0.10388 -0.0162 0.4593 1.0000
9.750 0.4031 0.11318 0.10404 -0.0150 0.4465 1.0000
10.000 0.4244 0.11741 0.10829 -0.0154 0.4397 1.0000
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Polar data table (+)
Polar graphs
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