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GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
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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