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GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 344 (PFALZ 71) AIRFOIL (goe344-il)
Reynolds number: 50,000
Max Cl/Cd: 34.44 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe344-il-50000-n5.txt
Download as CSV file: xf-goe344-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5069   0.11712   0.10972  -0.0078   1.0000   0.1137
  -9.000  -0.5132   0.11446   0.10715  -0.0105   1.0000   0.1142
  -8.750  -0.5180   0.11141   0.10418  -0.0127   1.0000   0.1143
  -8.250  -0.4992   0.09914   0.09186  -0.0137   1.0000   0.0848
  -8.000  -0.4944   0.09518   0.08793  -0.0139   1.0000   0.0823
  -7.750  -0.4927   0.09132   0.08408  -0.0157   1.0000   0.0815
  -7.500  -0.4901   0.08737   0.08015  -0.0176   1.0000   0.0809
  -7.250  -0.4864   0.08321   0.07599  -0.0196   1.0000   0.0796
  -6.750  -0.4777   0.07106   0.06356  -0.0293   1.0000   0.0724
  -6.500  -0.4674   0.06684   0.05924  -0.0301   1.0000   0.0721
  -6.250  -0.4562   0.06222   0.05449  -0.0316   1.0000   0.0733
  -6.000  -0.4431   0.06092   0.05326  -0.0296   1.0000   0.0766
  -5.750  -0.4286   0.05718   0.04935  -0.0304   1.0000   0.0779
  -5.500  -0.4125   0.05270   0.04460  -0.0315   1.0000   0.0776
  -5.250  -0.3949   0.04845   0.04004  -0.0323   1.0000   0.0776
  -5.000  -0.3760   0.04460   0.03584  -0.0327   1.0000   0.0782
  -4.750  -0.3559   0.04152   0.03239  -0.0327   1.0000   0.0811
  -4.500  -0.3343   0.03812   0.02845  -0.0328   1.0000   0.0843
  -4.250  -0.3116   0.03493   0.02470  -0.0325   1.0000   0.0856
  -4.000  -0.2884   0.03231   0.02161  -0.0320   1.0000   0.0870
  -3.750  -0.2657   0.03065   0.01979  -0.0313   1.0000   0.0891
  -3.500  -0.2421   0.02911   0.01800  -0.0307   1.0000   0.0918
  -3.250  -0.2177   0.02771   0.01628  -0.0300   1.0000   0.0973
  -3.000  -0.1931   0.02656   0.01492  -0.0294   1.0000   0.1035
  -2.750  -0.1682   0.02553   0.01372  -0.0288   1.0000   0.1098
  -2.500  -0.1422   0.02440   0.01234  -0.0282   1.0000   0.1166
  -2.250  -0.1163   0.02361   0.01137  -0.0276   1.0000   0.1274
  -2.000  -0.0905   0.02304   0.01073  -0.0271   1.0000   0.1430
  -1.750  -0.0641   0.02246   0.01016  -0.0268   1.0000   0.1610
  -1.500  -0.0384   0.02198   0.00969  -0.0264   1.0000   0.1832
  -1.250  -0.0132   0.02154   0.00932  -0.0260   1.0000   0.2057
  -1.000   0.0115   0.02118   0.00903  -0.0254   1.0000   0.2291
  -0.750   0.0357   0.02085   0.00878  -0.0248   1.0000   0.2526
  -0.500   0.0595   0.02056   0.00862  -0.0242   1.0000   0.2821
  -0.250   0.0831   0.02023   0.00851  -0.0236   1.0000   0.3228
   0.000   0.1062   0.01963   0.00840  -0.0232   1.0000   0.4021
   0.250   0.1407   0.01829   0.00838  -0.0242   1.0000   1.0000
   0.500   0.1705   0.01858   0.00847  -0.0251   0.9953   1.0000
   0.750   0.2256   0.01872   0.00841  -0.0309   0.9753   1.0000
   1.000   0.2726   0.01873   0.00833  -0.0348   0.9530   1.0000
   1.250   0.3174   0.01868   0.00822  -0.0381   0.9289   1.0000
   1.500   0.3646   0.01855   0.00807  -0.0415   0.9054   1.0000
   1.750   0.4073   0.01840   0.00793  -0.0439   0.8766   1.0000
   2.000   0.4434   0.01830   0.00784  -0.0449   0.8391   1.0000
   2.250   0.4817   0.01817   0.00769  -0.0461   0.7971   1.0000
   2.500   0.5218   0.01807   0.00747  -0.0473   0.7507   1.0000
   2.750   0.5567   0.01816   0.00736  -0.0475   0.7021   1.0000
   3.000   0.5847   0.01847   0.00748  -0.0467   0.6545   1.0000
   3.250   0.6095   0.01889   0.00770  -0.0454   0.6089   1.0000
   3.500   0.6333   0.01936   0.00799  -0.0441   0.5678   1.0000
   3.750   0.6567   0.01987   0.00836  -0.0428   0.5311   1.0000
   4.000   0.6802   0.02042   0.00878  -0.0417   0.4990   1.0000
   4.250   0.7045   0.02098   0.00926  -0.0408   0.4701   1.0000
   4.500   0.7290   0.02155   0.00980  -0.0400   0.4447   1.0000
   4.750   0.7536   0.02214   0.01034  -0.0393   0.4218   1.0000
   5.000   0.7783   0.02273   0.01093  -0.0386   0.4004   1.0000
   5.250   0.8025   0.02335   0.01158  -0.0378   0.3795   1.0000
   5.750   0.8486   0.02464   0.01287  -0.0359   0.3357   1.0000
   6.000   0.8702   0.02531   0.01347  -0.0348   0.3130   1.0000
   6.250   0.8915   0.02597   0.01428  -0.0337   0.2891   1.0000
   6.500   0.9123   0.02666   0.01499  -0.0325   0.2673   1.0000
   6.750   0.9330   0.02737   0.01586  -0.0313   0.2437   1.0000
   7.000   0.9526   0.02814   0.01664  -0.0299   0.2216   1.0000
   7.250   0.9724   0.02903   0.01772  -0.0287   0.1977   1.0000
   7.500   0.9908   0.03000   0.01866  -0.0273   0.1767   1.0000
   7.750   1.0100   0.03120   0.01995  -0.0259   0.1583   1.0000
   8.000   1.0285   0.03248   0.02129  -0.0246   0.1436   1.0000
   8.250   1.0464   0.03381   0.02268  -0.0232   0.1310   1.0000
   8.500   1.0641   0.03527   0.02414  -0.0219   0.1219   1.0000
   8.750   1.0823   0.03701   0.02621  -0.0205   0.1130   1.0000
   9.000   1.0984   0.03867   0.02795  -0.0191   0.1050   1.0000
   9.250   1.1140   0.04053   0.03003  -0.0176   0.0977   1.0000
   9.500   1.1280   0.04259   0.03227  -0.0161   0.0912   1.0000
   9.750   1.1393   0.04453   0.03444  -0.0143   0.0842   1.0000
  10.000   1.1495   0.04688   0.03697  -0.0126   0.0788   1.0000
  10.250   1.1553   0.04944   0.03991  -0.0106   0.0734   1.0000
  10.500   1.1645   0.05159   0.04209  -0.0090   0.0692   1.0000
  10.750   1.1620   0.05499   0.04595  -0.0065   0.0661   1.0000
  11.000   1.1543   0.05845   0.04983  -0.0041   0.0633   1.0000
  11.250   1.1431   0.06169   0.05335  -0.0015   0.0613   1.0000
  11.500   1.1311   0.06518   0.05705   0.0004   0.0598   1.0000
  11.750   1.1171   0.06918   0.06126   0.0012   0.0588   1.0000
  12.000   1.0988   0.07410   0.06639   0.0007   0.0582   1.0000
  12.250   1.0628   0.08247   0.07507  -0.0035   0.0593   1.0000
  12.500   1.0022   0.09868   0.09151  -0.0150   0.0638   1.0000
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