GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Reynolds number: 50,000 Max Cl/Cd: 32.54 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe344-il-50000.txt Download as CSV file: xf-goe344-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 344 (PFALZ 71) 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5079 0.10142 0.09436 -0.0056 1.0000 0.2086
-7.500 -0.4874 0.09636 0.08927 -0.0025 1.0000 0.2180
-7.250 -0.4982 0.09422 0.08724 -0.0059 1.0000 0.2244
-7.000 -0.4896 0.09078 0.08381 -0.0049 1.0000 0.2369
-6.750 -0.4794 0.08671 0.07978 -0.0033 1.0000 0.2470
-6.500 -0.4788 0.08363 0.07675 -0.0043 1.0000 0.2576
-6.250 -0.4781 0.08100 0.07415 -0.0059 1.0000 0.2707
-6.000 -0.4732 0.07813 0.07130 -0.0063 1.0000 0.2853
-5.750 -0.4656 0.07476 0.06795 -0.0055 1.0000 0.3006
-5.500 -0.4566 0.07109 0.06431 -0.0036 1.0000 0.3169
-5.250 -0.4470 0.06770 0.06098 -0.0006 1.0000 0.3382
-5.000 -0.4412 0.06466 0.05799 0.0016 1.0000 0.3663
-4.750 -0.4351 0.06167 0.05506 0.0047 1.0000 0.3986
-4.250 -0.4290 0.05582 0.04940 0.0146 1.0000 0.4861
-4.000 -0.4258 0.05288 0.04654 0.0208 1.0000 0.5324
-3.750 -0.4216 0.05008 0.04382 0.0256 1.0000 0.5722
-3.500 -0.2762 0.04049 0.03168 -0.0256 1.0000 0.2050
-3.250 -0.2476 0.03681 0.02747 -0.0265 1.0000 0.1883
-3.000 -0.2210 0.03385 0.02408 -0.0266 1.0000 0.1827
-2.750 -0.1954 0.03170 0.02158 -0.0263 1.0000 0.1859
-2.500 -0.1683 0.02972 0.01907 -0.0260 1.0000 0.1917
-2.250 -0.1432 0.02786 0.01707 -0.0254 1.0000 0.1977
-2.000 -0.1164 0.02631 0.01520 -0.0249 1.0000 0.2099
-1.750 -0.0910 0.02507 0.01393 -0.0243 1.0000 0.2289
-1.500 -0.0648 0.02398 0.01266 -0.0237 1.0000 0.2546
-1.250 -0.0391 0.02303 0.01172 -0.0230 1.0000 0.2870
-1.000 -0.0105 0.02215 0.01086 -0.0228 1.0000 0.3240
-0.750 0.0184 0.02128 0.01005 -0.0227 1.0000 0.3634
-0.500 0.0456 0.02036 0.00937 -0.0223 1.0000 0.4143
-0.250 0.0917 0.01760 0.00851 -0.0249 1.0000 1.0000
0.000 0.1164 0.01785 0.00817 -0.0240 1.0000 1.0000
0.250 0.1372 0.01810 0.00816 -0.0229 1.0000 1.0000
0.500 0.1573 0.01839 0.00829 -0.0218 1.0000 1.0000
0.750 0.1765 0.01874 0.00853 -0.0208 1.0000 1.0000
1.000 0.1950 0.01917 0.00889 -0.0198 1.0000 1.0000
1.250 0.2123 0.01971 0.00939 -0.0189 1.0000 1.0000
1.500 0.2284 0.02038 0.01004 -0.0181 1.0000 1.0000
1.750 0.2430 0.02122 0.01089 -0.0176 1.0000 1.0000
2.000 0.2614 0.02226 0.01195 -0.0183 0.9975 1.0000
2.250 0.3542 0.02287 0.01267 -0.0320 0.9603 1.0000
2.500 0.4406 0.02262 0.01261 -0.0430 0.9180 1.0000
2.750 0.5262 0.02160 0.01185 -0.0521 0.8720 1.0000
3.000 0.5855 0.02066 0.01105 -0.0553 0.8156 1.0000
3.250 0.6292 0.02016 0.01045 -0.0553 0.7561 1.0000
3.500 0.6611 0.02043 0.01046 -0.0538 0.7020 1.0000
3.750 0.6875 0.02113 0.01099 -0.0523 0.6550 1.0000
4.000 0.7119 0.02193 0.01167 -0.0508 0.6160 1.0000
4.250 0.7364 0.02272 0.01236 -0.0495 0.5834 1.0000
4.500 0.7602 0.02356 0.01315 -0.0481 0.5542 1.0000
4.750 0.7837 0.02443 0.01403 -0.0468 0.5272 1.0000
5.000 0.8073 0.02528 0.01481 -0.0454 0.5014 1.0000
5.250 0.8297 0.02610 0.01562 -0.0438 0.4742 1.0000
5.500 0.8510 0.02689 0.01641 -0.0421 0.4456 1.0000
5.750 0.8721 0.02763 0.01714 -0.0402 0.4160 1.0000
6.000 0.8930 0.02843 0.01790 -0.0384 0.3857 1.0000
6.250 0.9137 0.02937 0.01875 -0.0365 0.3538 1.0000
6.500 0.9343 0.03054 0.01974 -0.0347 0.3204 1.0000
6.750 0.9526 0.03211 0.02139 -0.0327 0.2861 1.0000
7.000 0.9714 0.03363 0.02289 -0.0308 0.2558 1.0000
7.250 0.9911 0.03532 0.02464 -0.0291 0.2319 1.0000
7.500 1.0102 0.03705 0.02644 -0.0274 0.2121 1.0000
7.750 1.0288 0.03926 0.02889 -0.0258 0.1972 1.0000
8.000 1.0468 0.04130 0.03109 -0.0242 0.1833 1.0000
8.250 1.0648 0.04356 0.03351 -0.0227 0.1720 1.0000
8.500 1.0723 0.04712 0.03770 -0.0204 0.1635 1.0000
8.750 1.0872 0.04973 0.04042 -0.0188 0.1546 1.0000
9.000 1.0869 0.05421 0.04552 -0.0164 0.1498 1.0000
9.250 1.1031 0.05661 0.04789 -0.0150 0.1417 1.0000
9.500 1.0915 0.06204 0.05391 -0.0126 0.1400 1.0000
9.750 1.0750 0.06785 0.06013 -0.0107 0.1398 1.0000
10.000 1.0541 0.07385 0.06642 -0.0095 0.1404 1.0000
10.250 1.0317 0.07988 0.07261 -0.0089 0.1414 1.0000
10.500 1.0107 0.08569 0.07849 -0.0086 0.1424 1.0000
10.750 0.9369 0.10200 0.09481 -0.0197 0.1574 1.0000
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Polar data table (+)
Polar graphs
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