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NACA M22 AIRFOIL (m22-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA M22 AIRFOIL (m22-il)
Reynolds number: 50,000
Max Cl/Cd: 32.78 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m22-il-50000-n5.txt
Download as CSV file: xf-m22-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3554   0.11877   0.11356  -0.0004   0.9102   0.0437
  -8.250  -0.3512   0.11752   0.11227  -0.0035   0.8887   0.0441
  -8.000  -0.3464   0.11636   0.11107  -0.0067   0.8724   0.0443
  -7.750  -0.3379   0.11502   0.10967  -0.0105   0.8585   0.0444
  -7.500  -0.3298   0.10846   0.10313  -0.0086   0.8481   0.0451
  -7.250  -0.3227   0.10285   0.09748  -0.0061   0.8383   0.0470
  -7.000  -0.3132   0.09952   0.09411  -0.0072   0.8278   0.0494
  -6.750  -0.3024   0.09669   0.09123  -0.0093   0.8180   0.0522
  -6.500  -0.2896   0.09454   0.08900  -0.0126   0.8090   0.0554
  -6.250  -0.2676   0.09426   0.08859  -0.0197   0.7991   0.0572
  -6.000  -0.2476   0.09228   0.08651  -0.0241   0.7907   0.0578
  -5.750  -0.2440   0.08543   0.07968  -0.0208   0.7836   0.0596
  -5.500  -0.2303   0.08176   0.07595  -0.0217   0.7757   0.0624
  -5.250  -0.2127   0.07889   0.07298  -0.0238   0.7683   0.0662
  -5.000  -0.1758   0.07917   0.07293  -0.0314   0.7599   0.0709
  -4.750  -0.1688   0.07338   0.06722  -0.0298   0.7537   0.0733
  -4.500  -0.1505   0.07013   0.06388  -0.0310   0.7462   0.0799
  -4.250  -0.1156   0.06941   0.06282  -0.0360   0.7392   0.0853
  -4.000  -0.1039   0.06448   0.05792  -0.0353   0.7325   0.0889
  -3.750  -0.0744   0.06290   0.05604  -0.0380   0.7257   0.0976
  -3.500  -0.0552   0.05925   0.05232  -0.0386   0.7195   0.1027
  -3.000  -0.0066   0.05444   0.04712  -0.0409   0.7069   0.1233
  -2.750   0.0208   0.05209   0.04457  -0.0426   0.6997   0.1314
  -2.250   0.0710   0.04779   0.03985  -0.0441   0.6871   0.1604
  -1.500   0.1410   0.04175   0.03329  -0.0449   0.6690   0.2454
  -1.000   0.2240   0.03977   0.03017  -0.0474   0.6568   0.1097
  -0.750   0.2538   0.03822   0.02823  -0.0472   0.6520   0.0945
  -0.500   0.2842   0.03741   0.02708  -0.0477   0.6453   0.0974
  -0.250   0.3115   0.03611   0.02556  -0.0477   0.6396   0.0946
   0.000   0.3403   0.03498   0.02407  -0.0475   0.6350   0.0890
   0.250   0.3718   0.03440   0.02308  -0.0480   0.6279   0.0841
   0.500   0.3993   0.03341   0.02187  -0.0477   0.6232   0.0824
   0.750   0.4281   0.03283   0.02111  -0.0483   0.6167   0.0808
   1.000   0.4590   0.03226   0.02025  -0.0486   0.6111   0.0794
   1.250   0.4915   0.03163   0.01927  -0.0489   0.6068   0.0784
   1.500   0.5244   0.03146   0.01894  -0.0504   0.5992   0.0779
   1.750   0.5544   0.03100   0.01826  -0.0503   0.5947   0.0780
   2.000   0.5825   0.03093   0.01807  -0.0507   0.5885   0.0788
   2.250   0.6082   0.03082   0.01785  -0.0505   0.5828   0.0802
   2.500   0.6324   0.03053   0.01739  -0.0493   0.5790   0.0825
   2.750   0.6562   0.03097   0.01786  -0.0497   0.5717   0.0861
   3.000   0.6799   0.03104   0.01789  -0.0491   0.5670   0.0986
   3.250   0.7033   0.03115   0.01807  -0.0485   0.5623   0.1178
   3.500   0.7260   0.03168   0.01875  -0.0487   0.5554   0.1472
   3.750   0.7837   0.03044   0.01872  -0.0545   0.5510   1.0000
   4.000   0.8059   0.03148   0.01971  -0.0548   0.5442   1.0000
   4.250   0.8285   0.03211   0.02030  -0.0543   0.5389   1.0000
   4.500   0.8522   0.03236   0.02049  -0.0533   0.5356   1.0000
   4.750   0.8713   0.03392   0.02221  -0.0539   0.5274   1.0000
   5.000   0.8940   0.03443   0.02275  -0.0532   0.5231   1.0000
   5.250   0.9141   0.03552   0.02393  -0.0530   0.5175   1.0000
   5.500   0.9329   0.03679   0.02534  -0.0529   0.5110   1.0000
   5.750   0.9562   0.03716   0.02584  -0.0520   0.5075   1.0000
   6.000   0.9691   0.03936   0.02824  -0.0524   0.4993   1.0000
   6.250   0.9897   0.04017   0.02921  -0.0517   0.4948   1.0000
   6.500   1.0142   0.04039   0.02959  -0.0506   0.4919   1.0000
   6.750   1.0181   0.04364   0.03308  -0.0512   0.4819   1.0000
   7.000   1.0550   0.03977   0.02939  -0.0473   0.4660   1.0000
   7.250   1.0840   0.03683   0.02660  -0.0439   0.4440   1.0000
   7.500   1.1082   0.03468   0.02460  -0.0410   0.4159   1.0000
   7.750   1.1235   0.03427   0.02437  -0.0392   0.3805   1.0000
   8.000   1.1318   0.03500   0.02521  -0.0377   0.3275   1.0000
   8.250   1.1220   0.03723   0.02618  -0.0352   0.1746   1.0000
   8.500   1.1001   0.04178   0.03021  -0.0343   0.0967   1.0000
   8.750   1.0800   0.04651   0.03461  -0.0337   0.0698   1.0000
   9.000   1.0682   0.05063   0.03865  -0.0334   0.0550   1.0000
   9.500   1.0553   0.05805   0.04618  -0.0329   0.0452   1.0000
   9.750   1.0506   0.06166   0.04993  -0.0328   0.0430   1.0000
  10.000   1.0455   0.06537   0.05377  -0.0328   0.0413   1.0000
  10.250   1.0399   0.06921   0.05772  -0.0328   0.0399   1.0000
  10.500   1.0340   0.07309   0.06169  -0.0329   0.0389   1.0000
  10.750   1.0313   0.07658   0.06535  -0.0329   0.0377   1.0000
  11.000   1.0292   0.08004   0.06895  -0.0329   0.0362   1.0000
  11.250   1.0279   0.08340   0.07244  -0.0329   0.0346   1.0000
  11.500   1.0272   0.08662   0.07574  -0.0327   0.0330   1.0000
  11.750   1.0274   0.08958   0.07874  -0.0323   0.0317   1.0000
  12.000   1.0315   0.09171   0.08088  -0.0312   0.0307   1.0000
  12.250   1.0434   0.09270   0.08203  -0.0291   0.0301   1.0000
  12.500   1.0630   0.09246   0.08205  -0.0258   0.0295   1.0000
  12.750   1.0928   0.09117   0.08103  -0.0213   0.0284   1.0000
  13.000   1.1226   0.09089   0.08107  -0.0174   0.0265   1.0000
  13.250   1.1453   0.09231   0.08279  -0.0148   0.0255   1.0000
  13.500   1.1574   0.09523   0.08603  -0.0136   0.0254   1.0000
  13.750   1.1597   0.09917   0.09028  -0.0136   0.0255   1.0000
  14.000   1.1560   0.10371   0.09511  -0.0144   0.0256   1.0000
  14.250   1.1486   0.10869   0.10036  -0.0158   0.0258   1.0000
  14.500   1.1389   0.11414   0.10606  -0.0178   0.0260   1.0000
  14.750   1.1276   0.12003   0.11217  -0.0204   0.0262   1.0000
  15.000   1.1152   0.12636   0.11872  -0.0235   0.0264   1.0000
  15.250   1.1023   0.13314   0.12568  -0.0272   0.0266   1.0000
  15.500   1.0893   0.14038   0.13309  -0.0314   0.0269   1.0000
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