EPPLER 330 AIRFOIL (e330-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 330 AIRFOIL (e330-il) Reynolds number: 50,000 Max Cl/Cd: 17.19 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e330-il-50000.txt Download as CSV file: xf-e330-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 330 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5206 0.11211 0.10599 0.0195 1.0000 0.2250
-9.000 -0.5241 0.10877 0.10274 0.0186 1.0000 0.2366
-8.750 -0.5446 0.10667 0.10077 0.0161 1.0000 0.2480
-8.500 -0.5144 0.10158 0.09568 0.0191 1.0000 0.2676
-8.250 -0.5088 0.09821 0.09237 0.0198 1.0000 0.2865
-8.000 -0.5235 0.09567 0.08995 0.0194 1.0000 0.3059
-7.750 -0.5088 0.09207 0.08639 0.0218 1.0000 0.3342
-7.500 -0.5064 0.08924 0.08364 0.0239 1.0000 0.3645
-7.250 -0.4886 0.08627 0.08072 0.0277 1.0000 0.4084
-7.000 -0.4510 0.08324 0.07769 0.0337 1.0000 0.4808
-5.750 -0.4174 0.06594 0.06082 0.0370 1.0000 0.5594
-5.500 -0.4772 0.06120 0.05636 0.0335 1.0000 0.5020
-5.250 -0.5303 0.05559 0.05077 0.0263 1.0000 0.4292
-5.000 -0.5166 0.04718 0.04005 0.0111 1.0000 0.1575
-4.750 -0.4996 0.04441 0.03642 0.0141 1.0000 0.1249
-4.500 -0.4867 0.04143 0.03343 0.0161 1.0000 0.1199
-4.250 -0.4838 0.04020 0.03161 0.0207 1.0000 0.1116
-4.000 -0.4837 0.03863 0.03001 0.0240 1.0000 0.1102
-3.750 -0.4818 0.03724 0.02849 0.0270 1.0000 0.1083
-3.500 -0.4758 0.03584 0.02686 0.0297 1.0000 0.1061
-3.250 -0.0381 0.02111 0.01372 -0.0218 1.0000 1.0000
-3.000 -0.0141 0.02098 0.01333 -0.0230 1.0000 1.0000
-2.750 -0.0003 0.02134 0.01358 -0.0236 1.0000 1.0000
-2.500 0.0299 0.02189 0.01387 -0.0278 0.9737 1.0000
-2.250 0.1088 0.02147 0.01290 -0.0386 0.9303 1.0000
-2.000 0.1547 0.02144 0.01246 -0.0424 0.8915 1.0000
-1.750 0.1794 0.02171 0.01244 -0.0419 0.8596 1.0000
-1.500 0.1990 0.02207 0.01256 -0.0404 0.8329 1.0000
-1.250 0.2179 0.02244 0.01269 -0.0386 0.8113 1.0000
-1.000 0.2379 0.02284 0.01293 -0.0375 0.7897 1.0000
-0.750 0.2579 0.02323 0.01316 -0.0362 0.7715 1.0000
-0.500 0.2780 0.02363 0.01342 -0.0349 0.7549 1.0000
-0.250 0.2982 0.02406 0.01370 -0.0336 0.7392 1.0000
0.000 0.3192 0.02453 0.01406 -0.0326 0.7244 1.0000
0.250 0.3408 0.02502 0.01445 -0.0318 0.7101 1.0000
0.500 0.3623 0.02556 0.01491 -0.0311 0.6964 1.0000
0.750 0.3840 0.02615 0.01546 -0.0305 0.6833 1.0000
1.000 0.4056 0.02678 0.01605 -0.0299 0.6707 1.0000
1.250 0.4272 0.02745 0.01669 -0.0293 0.6591 1.0000
1.500 0.4480 0.02806 0.01725 -0.0283 0.6485 1.0000
1.750 0.4691 0.02875 0.01792 -0.0275 0.6374 1.0000
2.000 0.4905 0.02969 0.01890 -0.0274 0.6260 1.0000
2.250 0.5111 0.03058 0.01981 -0.0269 0.6156 1.0000
2.500 0.5311 0.03120 0.02041 -0.0254 0.6068 1.0000
2.750 0.5511 0.03247 0.02178 -0.0256 0.5957 1.0000
3.000 0.5700 0.03366 0.02303 -0.0252 0.5856 1.0000
3.250 0.5898 0.03432 0.02367 -0.0236 0.5775 1.0000
3.500 0.6064 0.03605 0.02554 -0.0239 0.5668 1.0000
3.750 0.6231 0.03745 0.02704 -0.0232 0.5576 1.0000
4.000 0.6413 0.03845 0.02809 -0.0219 0.5491 1.0000
4.250 0.6525 0.04069 0.03047 -0.0220 0.5391 1.0000
4.500 0.6693 0.04182 0.03165 -0.0205 0.5309 1.0000
4.750 0.6793 0.04395 0.03389 -0.0200 0.5214 1.0000
5.000 0.6843 0.04655 0.03660 -0.0194 0.5124 1.0000
5.250 0.7045 0.04722 0.03735 -0.0173 0.5045 1.0000
5.500 0.6915 0.05159 0.04184 -0.0173 0.4957 1.0000
5.750 0.7085 0.05265 0.04295 -0.0153 0.4874 1.0000
6.000 0.6834 0.05756 0.04791 -0.0147 0.4807 1.0000
6.250 0.6965 0.05907 0.04949 -0.0128 0.4724 1.0000
6.500 0.6594 0.06421 0.05456 -0.0112 0.4687 1.0000
6.750 0.6321 0.06778 0.05807 -0.0083 0.4664 1.0000
7.000 0.6449 0.06957 0.05993 -0.0067 0.4579 1.0000
7.250 0.6190 0.07325 0.06354 -0.0044 0.4573 1.0000
7.500 0.6035 0.07680 0.06706 -0.0031 0.4575 1.0000
7.750 0.5974 0.08044 0.07074 -0.0027 0.4608 1.0000
8.000 0.4883 0.08941 0.07943 -0.0064 0.5685 1.0000
8.250 0.4957 0.09176 0.08182 -0.0054 0.5547 1.0000
8.500 0.5035 0.09431 0.08445 -0.0047 0.5427 1.0000
8.750 0.5133 0.09697 0.08717 -0.0041 0.5296 1.0000
9.000 0.5233 0.09963 0.08989 -0.0034 0.5159 1.0000
9.250 0.5422 0.10309 0.09345 -0.0033 0.5032 1.0000
9.500 0.5516 0.10577 0.09620 -0.0026 0.4893 1.0000
9.750 0.5503 0.10771 0.09820 -0.0014 0.4757 1.0000
10.000 0.5439 0.10966 0.10016 -0.0003 0.4643 1.0000
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Polar data table (+)
Polar graphs
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