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Dormoy (dormoy-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Dormoy (dormoy-il)
Reynolds number: 50,000
Max Cl/Cd: 36.54 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dormoy-il-50000.txt
Download as CSV file: xf-dormoy-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Dormoy                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4042   0.10551   0.09902  -0.0148   1.0000   0.2324
  -9.750  -0.4018   0.10238   0.09598  -0.0148   1.0000   0.2438
  -9.500  -0.4225   0.10198   0.09575  -0.0162   1.0000   0.2517
  -9.250  -0.4138   0.09825   0.09207  -0.0152   1.0000   0.2650
  -9.000  -0.4120   0.09519   0.08910  -0.0143   1.0000   0.2787
  -8.750  -0.4084   0.09209   0.08608  -0.0133   1.0000   0.2921
  -8.500  -0.4056   0.08904   0.08311  -0.0120   1.0000   0.3054
  -8.250  -0.4041   0.08605   0.08021  -0.0106   1.0000   0.3186
  -8.000  -0.4066   0.08349   0.07776  -0.0088   1.0000   0.3324
  -7.750  -0.4171   0.08151   0.07595  -0.0075   1.0000   0.3478
  -7.500  -0.4058   0.07770   0.07219  -0.0052   1.0000   0.3635
  -7.250  -0.3988   0.07461   0.06918  -0.0029   1.0000   0.3809
  -7.000  -0.4067   0.07258   0.06729  -0.0002   1.0000   0.4044
  -5.750  -0.3782   0.04563   0.03879  -0.0324   1.0000   0.1387
  -5.500  -0.3605   0.04137   0.03400  -0.0322   1.0000   0.1209
  -5.250  -0.3408   0.03776   0.02979  -0.0314   1.0000   0.1094
  -5.000  -0.3191   0.03465   0.02593  -0.0304   1.0000   0.1008
  -4.750  -0.2974   0.03200   0.02288  -0.0292   1.0000   0.0959
  -4.500  -0.2725   0.02965   0.01972  -0.0279   1.0000   0.0912
  -4.250  -0.2490   0.02805   0.01774  -0.0266   1.0000   0.0898
  -4.000  -0.2250   0.02641   0.01591  -0.0254   1.0000   0.0911
  -3.750  -0.2020   0.02520   0.01468  -0.0244   1.0000   0.0977
  -3.500  -0.1786   0.02431   0.01353  -0.0231   1.0000   0.1029
  -3.250  -0.1563   0.02349   0.01270  -0.0221   1.0000   0.1100
  -3.000  -0.1340   0.02287   0.01206  -0.0211   1.0000   0.1259
  -2.750  -0.1101   0.02187   0.01146  -0.0206   1.0000   0.2013
  -2.500  -0.0669   0.01912   0.01111  -0.0219   1.0000   1.0000
  -2.250  -0.0492   0.01947   0.01099  -0.0208   1.0000   1.0000
  -2.000  -0.0317   0.01985   0.01098  -0.0198   1.0000   1.0000
  -1.750  -0.0144   0.02028   0.01108  -0.0190   1.0000   1.0000
  -1.500   0.0029   0.02075   0.01126  -0.0183   1.0000   1.0000
  -1.250   0.0200   0.02126   0.01153  -0.0177   1.0000   1.0000
  -1.000   0.0369   0.02183   0.01183  -0.0172   1.0000   1.0000
  -0.750   0.0934   0.02303   0.01275  -0.0242   0.9834   1.0000
  -0.500   0.1459   0.02402   0.01355  -0.0302   0.9658   1.0000
  -0.250   0.1961   0.02485   0.01422  -0.0355   0.9470   1.0000
   0.000   0.2515   0.02563   0.01491  -0.0415   0.9287   1.0000
   0.250   0.2953   0.02618   0.01543  -0.0452   0.9077   1.0000
   0.500   0.3542   0.02656   0.01585  -0.0510   0.8875   1.0000
   0.750   0.4042   0.02671   0.01606  -0.0549   0.8634   1.0000
   1.000   0.4614   0.02653   0.01599  -0.0593   0.8388   1.0000
   1.250   0.5165   0.02609   0.01575  -0.0626   0.8144   1.0000
   1.500   0.5662   0.02555   0.01535  -0.0646   0.7901   1.0000
   1.750   0.6051   0.02499   0.01489  -0.0644   0.7619   1.0000
   2.000   0.6376   0.02444   0.01442  -0.0630   0.7320   1.0000
   2.250   0.6674   0.02390   0.01394  -0.0612   0.7026   1.0000
   2.500   0.6955   0.02334   0.01352  -0.0591   0.6732   1.0000
   2.750   0.7216   0.02304   0.01326  -0.0573   0.6449   1.0000
   3.000   0.7463   0.02301   0.01326  -0.0556   0.6179   1.0000
   3.250   0.7701   0.02322   0.01356  -0.0541   0.5927   1.0000
   3.500   0.7944   0.02358   0.01410  -0.0530   0.5697   1.0000
   3.750   0.8182   0.02380   0.01439  -0.0515   0.5451   1.0000
   4.000   0.8367   0.02356   0.01406  -0.0485   0.5077   1.0000
   4.250   0.8569   0.02385   0.01444  -0.0466   0.4803   1.0000
   4.500   0.8745   0.02411   0.01480  -0.0443   0.4499   1.0000
   4.750   0.8816   0.02413   0.01460  -0.0401   0.3976   1.0000
   5.000   0.8908   0.02458   0.01502  -0.0366   0.3497   1.0000
   5.250   0.8975   0.02531   0.01554  -0.0328   0.2766   1.0000
   5.500   0.9027   0.02702   0.01654  -0.0294   0.1572   1.0000
   5.750   0.9107   0.02932   0.01822  -0.0270   0.0950   1.0000
   6.000   0.9182   0.03152   0.02032  -0.0245   0.0861   1.0000
   6.250   0.9232   0.03376   0.02259  -0.0217   0.0806   1.0000
   6.500   0.9301   0.03587   0.02483  -0.0191   0.0755   1.0000
   6.750   0.9426   0.03852   0.02743  -0.0171   0.0709   1.0000
   7.000   0.9802   0.04073   0.02977  -0.0168   0.0694   1.0000
   7.250   1.0276   0.04381   0.03305  -0.0177   0.0692   1.0000
   7.500   1.0692   0.04794   0.03740  -0.0185   0.0702   1.0000
   7.750   1.0895   0.05012   0.04013  -0.0167   0.0721   1.0000
   8.000   1.0977   0.05269   0.04349  -0.0139   0.0750   1.0000
   8.250   1.1053   0.05652   0.04802  -0.0117   0.0781   1.0000
   8.500   1.1140   0.06097   0.05283  -0.0101   0.0807   1.0000
   8.750   1.1261   0.06606   0.05817  -0.0092   0.0827   1.0000
   9.000   1.0989   0.06846   0.06122  -0.0052   0.0846   1.0000
   9.250   1.0688   0.07206   0.06519  -0.0021   0.0863   1.0000
   9.500   1.0416   0.07622   0.06959  -0.0007   0.0875   1.0000
   9.750   1.0142   0.08112   0.07466  -0.0013   0.0883   1.0000
  10.000   0.9861   0.08686   0.08042  -0.0035   0.0889   1.0000
  10.250   0.9548   0.09396   0.08759  -0.0077   0.0890   1.0000
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