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NACA M22 AIRFOIL (m22-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA M22 AIRFOIL (m22-il)
Reynolds number: 500,000
Max Cl/Cd: 100.27 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m22-il-500000.txt
Download as CSV file: xf-m22-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M22 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  -0.4463   0.10781   0.10503   0.0343   0.6819   0.0117
  -7.500  -0.4400   0.10467   0.10188   0.0324   0.6764   0.0119
  -7.250  -0.4346   0.10162   0.09879   0.0304   0.6715   0.0122
  -7.000  -0.4253   0.09830   0.09548   0.0278   0.6658   0.0127
  -6.750  -0.4135   0.09484   0.09197   0.0248   0.6606   0.0133
  -6.500  -0.3968   0.09148   0.08856   0.0208   0.6558   0.0140
  -6.250  -0.3757   0.08833   0.08537   0.0154   0.6504   0.0142
  -6.000  -0.3533   0.08502   0.08197   0.0101   0.6456   0.0143
  -5.750  -0.3305   0.08149   0.07835   0.0056   0.6408   0.0144
  -5.500  -0.3194   0.07612   0.07298   0.0050   0.6357   0.0146
  -5.250  -0.3085   0.07246   0.06928   0.0050   0.6307   0.0150
  -5.000  -0.2895   0.06948   0.06625   0.0031   0.6255   0.0156
  -4.750  -0.2671   0.06631   0.06301   0.0007   0.6202   0.0162
  -4.500  -0.2429   0.06313   0.05972  -0.0018   0.6155   0.0171
  -4.250  -0.2126   0.06019   0.05668  -0.0048   0.6103   0.0185
  -4.000  -0.1724   0.05789   0.05419  -0.0089   0.6052   0.0191
  -3.500  -0.1145   0.05157   0.04758  -0.0124   0.5960   0.0192
  -3.250  -0.0998   0.04635   0.04231  -0.0131   0.5914   0.0199
  -3.000  -0.0778   0.04395   0.03982  -0.0138   0.5869   0.0206
  -2.750  -0.0515   0.04167   0.03745  -0.0147   0.5820   0.0217
  -2.500  -0.0221   0.03949   0.03512  -0.0156   0.5770   0.0240
  -2.250   0.0180   0.03854   0.03390  -0.0165   0.5726   0.0258
  -2.000   0.0483   0.03641   0.03162  -0.0169   0.5680   0.0260
  -1.750   0.0774   0.03397   0.02900  -0.0171   0.5634   0.0261
  -1.500   0.0992   0.02945   0.02429  -0.0177   0.5595   0.0273
  -1.250   0.1247   0.02794   0.02270  -0.0180   0.5550   0.0283
  -1.000   0.1522   0.02650   0.02114  -0.0183   0.5503   0.0299
  -0.750   0.1818   0.02519   0.01965  -0.0184   0.5460   0.0331
  -0.500   0.2156   0.02487   0.01909  -0.0179   0.5417   0.0355
  -0.250   0.2436   0.02129   0.01521  -0.0179   0.5375   0.0369
   0.000   0.2700   0.02014   0.01400  -0.0182   0.5331   0.0383
   0.250   0.2975   0.01929   0.01300  -0.0184   0.5291   0.0400
   0.500   0.3262   0.01843   0.01205  -0.0185   0.5245   0.0435
   0.750   0.3574   0.01868   0.01208  -0.0181   0.5199   0.0479
   1.000   0.3840   0.01633   0.00956  -0.0184   0.5161   0.0511
   1.250   0.4120   0.01576   0.00895  -0.0186   0.5119   0.0544
   1.500   0.4412   0.01507   0.00806  -0.0185   0.5075   0.0636
   1.750   0.4689   0.01454   0.00753  -0.0188   0.5032   0.0683
   2.000   0.4972   0.01406   0.00694  -0.0189   0.4990   0.0794
   2.250   0.5256   0.01364   0.00649  -0.0191   0.4946   0.0918
   2.500   0.5540   0.01332   0.00613  -0.0193   0.4904   0.0989
   2.750   0.5842   0.01172   0.00415  -0.0182   0.4869   0.0465
   3.000   0.6118   0.01124   0.00369  -0.0181   0.4825   0.0445
   3.250   0.6393   0.01095   0.00339  -0.0180   0.4780   0.0432
   3.500   0.6668   0.01080   0.00321  -0.0180   0.4739   0.0427
   3.750   0.6946   0.01069   0.00312  -0.0181   0.4698   0.0431
   4.000   0.7226   0.01061   0.00307  -0.0183   0.4653   0.0449
   4.250   0.7506   0.01060   0.00305  -0.0184   0.4610   0.0478
   4.500   0.7787   0.01062   0.00309  -0.0186   0.4560   0.0559
   4.750   0.8059   0.01032   0.00321  -0.0188   0.4457   0.2838
   5.000   0.8770   0.00913   0.00343  -0.0288   0.4307   1.0000
   5.250   0.9033   0.00919   0.00348  -0.0286   0.4188   1.0000
   5.500   0.9295   0.00929   0.00355  -0.0286   0.4001   1.0000
   5.750   0.9556   0.00953   0.00367  -0.0286   0.3664   1.0000
   6.000   0.9803   0.01159   0.00473  -0.0303   0.1909   1.0000
   6.250   1.0022   0.01424   0.00658  -0.0317   0.0223   1.0000
   6.500   1.0268   0.01470   0.00714  -0.0315   0.0204   1.0000
   6.750   1.0508   0.01529   0.00786  -0.0313   0.0188   1.0000
   7.000   1.0738   0.01607   0.00874  -0.0311   0.0175   1.0000
   7.250   1.0953   0.01710   0.00989  -0.0308   0.0163   1.0000
   7.500   1.1110   0.01898   0.01195  -0.0305   0.0148   1.0000
   7.750   1.1254   0.02056   0.01365  -0.0297   0.0144   1.0000
   8.000   1.1413   0.02168   0.01485  -0.0289   0.0140   1.0000
   8.250   1.1531   0.02311   0.01638  -0.0278   0.0137   1.0000
   8.500   1.1610   0.02482   0.01818  -0.0267   0.0135   1.0000
   8.750   1.1637   0.02684   0.02027  -0.0255   0.0135   1.0000
   9.000   1.1644   0.02878   0.02226  -0.0233   0.0135   1.0000
   9.250   1.1696   0.03060   0.02410  -0.0206   0.0139   1.0000
   9.500   1.1862   0.03155   0.02504  -0.0188   0.0155   1.0000
   9.750   1.2023   0.03269   0.02625  -0.0171   0.0160   1.0000
  10.000   1.1179   0.02139   0.01554  -0.0086   0.0188   1.0000
  10.250   1.1720   0.02400   0.01818  -0.0060   0.0204   1.0000
  10.500   1.1844   0.02590   0.02020  -0.0047   0.0190   1.0000
  10.750   1.1972   0.02819   0.02257  -0.0035   0.0177   1.0000
  11.000   1.2208   0.03108   0.02547  -0.0028   0.0165   1.0000
  11.250   1.3358   0.05296   0.04741  -0.0107   0.0144   1.0000
  11.500   1.3347   0.05465   0.04933  -0.0087   0.0143   1.0000
  11.750   1.3265   0.05495   0.04981  -0.0061   0.0140   1.0000
  12.000   1.3180   0.05584   0.05084  -0.0042   0.0135   1.0000
  12.250   1.3123   0.05793   0.05311  -0.0032   0.0131   1.0000
  12.500   1.3058   0.06071   0.05608  -0.0026   0.0127   1.0000
  12.750   1.2982   0.06391   0.05946  -0.0024   0.0124   1.0000
  13.000   1.2890   0.06747   0.06319  -0.0024   0.0121   1.0000
  13.250   1.2780   0.07137   0.06726  -0.0027   0.0119   1.0000
  13.500   1.2654   0.07558   0.07162  -0.0034   0.0118   1.0000
  13.750   1.2514   0.08012   0.07632  -0.0044   0.0117   1.0000
  14.000   1.2363   0.08496   0.08133  -0.0057   0.0116   1.0000
  14.250   1.2201   0.09015   0.08667  -0.0075   0.0115   1.0000
  14.500   1.2031   0.09566   0.09233  -0.0096   0.0115   1.0000
  14.750   1.1857   0.10161   0.09842  -0.0122   0.0115   1.0000
  15.000   1.1682   0.10804   0.10500  -0.0153   0.0115   1.0000
  15.250   1.1503   0.11500   0.11209  -0.0189   0.0116   1.0000
  15.500   1.1326   0.12244   0.11967  -0.0230   0.0116   1.0000
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