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GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 403 AIRFOIL (goe403-il)
Reynolds number: 500,000
Max Cl/Cd: 98.56 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe403-il-500000.txt
Download as CSV file: xf-goe403-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 403 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3415   0.08984   0.08773  -0.0273   1.0000   0.0182
  -7.500  -0.3446   0.08760   0.08554  -0.0268   1.0000   0.0182
  -7.250  -0.3462   0.08510   0.08309  -0.0268   1.0000   0.0183
  -7.000  -0.3454   0.08239   0.08042  -0.0278   1.0000   0.0183
  -6.750  -0.3466   0.07989   0.07796  -0.0280   1.0000   0.0184
  -6.500  -0.3143   0.07396   0.07200  -0.0377   0.9959   0.0184
  -6.250  -0.2939   0.06523   0.06326  -0.0472   0.9899   0.0193
  -6.000  -0.2646   0.06116   0.05915  -0.0530   0.9852   0.0200
  -5.750  -0.2327   0.05690   0.05484  -0.0596   0.9797   0.0207
  -5.500  -0.1985   0.05238   0.05024  -0.0667   0.9730   0.0222
  -5.250  -0.1470   0.03898   0.03651  -0.0825   0.9651   0.0175
  -5.000  -0.1071   0.02014   0.01650  -0.0938   0.9557   0.0172
  -4.750  -0.0778   0.01624   0.01188  -0.0951   0.9449   0.0190
  -4.500  -0.0475   0.01482   0.01025  -0.0961   0.9349   0.0213
  -4.250  -0.0166   0.01391   0.00908  -0.0968   0.9242   0.0239
  -4.000   0.0135   0.01328   0.00822  -0.0970   0.9124   0.0267
  -3.750   0.0407   0.01190   0.00655  -0.0970   0.9001   0.0312
  -3.250   0.0956   0.01117   0.00552  -0.0965   0.8757   0.0377
  -3.000   0.1225   0.01082   0.00498  -0.0962   0.8643   0.0399
  -2.750   0.1483   0.00983   0.00383  -0.0957   0.8537   0.0428
  -2.500   0.1748   0.00954   0.00346  -0.0953   0.8435   0.0460
  -2.250   0.2013   0.00924   0.00305  -0.0948   0.8332   0.0487
  -2.000   0.2278   0.00899   0.00271  -0.0944   0.8227   0.0506
  -1.750   0.2544   0.00879   0.00242  -0.0940   0.8125   0.0518
  -1.500   0.2806   0.00846   0.00201  -0.0935   0.8024   0.0550
  -1.250   0.3071   0.00828   0.00180  -0.0931   0.7917   0.0605
  -1.000   0.3335   0.00809   0.00164  -0.0927   0.7801   0.0795
  -0.750   0.3600   0.00794   0.00156  -0.0923   0.7680   0.1169
  -0.500   0.3865   0.00787   0.00149  -0.0919   0.7547   0.1361
  -0.250   0.4128   0.00779   0.00142  -0.0915   0.7398   0.1564
   0.000   0.4389   0.00769   0.00137  -0.0911   0.7231   0.1896
   0.250   0.4644   0.00748   0.00136  -0.0907   0.7030   0.2789
   0.500   0.5008   0.00585   0.00140  -0.0929   0.6794   1.0000
   1.000   0.5508   0.00616   0.00138  -0.0915   0.6266   1.0000
   1.250   0.5760   0.00634   0.00141  -0.0909   0.6026   1.0000
   1.500   0.6013   0.00653   0.00147  -0.0903   0.5829   1.0000
   1.750   0.6269   0.00670   0.00154  -0.0898   0.5658   1.0000
   2.000   0.6526   0.00688   0.00162  -0.0893   0.5508   1.0000
   2.250   0.6777   0.00710   0.00172  -0.0888   0.5309   1.0000
   2.500   0.7028   0.00730   0.00183  -0.0882   0.5072   1.0000
   2.750   0.7285   0.00748   0.00193  -0.0878   0.4915   1.0000
   3.000   0.7541   0.00766   0.00205  -0.0873   0.4751   1.0000
   3.250   0.7786   0.00790   0.00214  -0.0867   0.4398   1.0000
   3.500   0.8026   0.00822   0.00227  -0.0860   0.3962   1.0000
   3.750   0.8230   0.00894   0.00252  -0.0848   0.3020   1.0000
   4.000   0.8343   0.01094   0.00343  -0.0826   0.0908   1.0000
   4.250   0.8549   0.01186   0.00408  -0.0813   0.0205   1.0000
   4.500   0.8798   0.01221   0.00454  -0.0807   0.0180   1.0000
   4.750   0.9035   0.01273   0.00521  -0.0798   0.0167   1.0000
   5.000   0.9266   0.01331   0.00591  -0.0788   0.0162   1.0000
   5.250   0.9486   0.01402   0.00672  -0.0776   0.0161   1.0000
   5.500   0.9704   0.01468   0.00746  -0.0766   0.0150   1.0000
   5.750   0.9908   0.01551   0.00837  -0.0752   0.0142   1.0000
   6.000   1.0094   0.01652   0.00948  -0.0735   0.0139   1.0000
   6.250   1.0267   0.01772   0.01076  -0.0716   0.0138   1.0000
   6.500   1.0429   0.01929   0.01241  -0.0694   0.0146   1.0000
   7.000   1.0957   0.02266   0.01591  -0.0666   0.0288   1.0000
   7.250   1.1169   0.02496   0.01833  -0.0657   0.0237   1.0000
   7.500   1.1394   0.02625   0.01973  -0.0648   0.0214   1.0000
   7.750   1.1615   0.02803   0.02153  -0.0641   0.0194   1.0000
   8.250   1.1968   0.03284   0.02680  -0.0614   0.0147   1.0000
   8.500   1.2147   0.03452   0.02870  -0.0599   0.0135   1.0000
   8.750   1.2302   0.03658   0.03097  -0.0583   0.0126   1.0000
   9.000   1.2436   0.03891   0.03348  -0.0566   0.0119   1.0000
   9.250   1.2560   0.04166   0.03633  -0.0553   0.0112   1.0000
   9.500   1.2665   0.04533   0.04014  -0.0539   0.0107   1.0000
   9.750   1.2490   0.05662   0.05191  -0.0509   0.0099   1.0000
  10.000   1.2467   0.05981   0.05536  -0.0481   0.0098   1.0000
  10.250   1.2407   0.06293   0.05871  -0.0452   0.0098   1.0000
  10.500   1.2297   0.06595   0.06196  -0.0421   0.0098   1.0000
  10.750   1.2150   0.06852   0.06469  -0.0384   0.0098   1.0000
  11.000   1.1966   0.07124   0.06758  -0.0354   0.0098   1.0000
  11.250   1.1795   0.07447   0.07095  -0.0337   0.0098   1.0000
  11.500   1.1620   0.07814   0.07477  -0.0331   0.0098   1.0000
  11.750   1.1446   0.08229   0.07906  -0.0335   0.0098   1.0000
  12.000   1.1255   0.08702   0.08393  -0.0349   0.0098   1.0000
  12.250   1.1082   0.09219   0.08924  -0.0371   0.0098   1.0000
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