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NACA M23 AIRFOIL (m23-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA M23 AIRFOIL (m23-il)
Reynolds number: 500,000
Max Cl/Cd: 106.55 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m23-il-500000.txt
Download as CSV file: xf-m23-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M23 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4010   0.10645   0.10351   0.0229   0.6651   0.0157
  -7.750  -0.3959   0.10343   0.10047   0.0195   0.6609   0.0159
  -7.500  -0.3925   0.10050   0.09755   0.0158   0.6561   0.0160
  -7.250  -0.3822   0.09714   0.09416   0.0111   0.6515   0.0160
  -7.000  -0.3693   0.09363   0.09058   0.0066   0.6474   0.0161
  -6.750  -0.3617   0.08865   0.08559   0.0069   0.6428   0.0162
  -6.500  -0.3521   0.08514   0.08206   0.0070   0.6377   0.0165
  -6.250  -0.3389   0.08202   0.07889   0.0052   0.6333   0.0169
  -6.000  -0.3232   0.07882   0.07564   0.0028   0.6289   0.0173
  -5.750  -0.3058   0.07553   0.07231   0.0003   0.6242   0.0178
  -5.500  -0.2866   0.07219   0.06890  -0.0024   0.6198   0.0187
  -5.250  -0.2546   0.06908   0.06564  -0.0075   0.6157   0.0201
  -5.000  -0.2243   0.06574   0.06216  -0.0117   0.6112   0.0203
  -4.750  -0.1986   0.06228   0.05858  -0.0140   0.6068   0.0204
  -4.500  -0.1880   0.05734   0.05359  -0.0142   0.6031   0.0208
  -4.250  -0.1701   0.05456   0.05077  -0.0146   0.5987   0.0212
  -4.000  -0.1479   0.05197   0.04811  -0.0156   0.5939   0.0218
  -3.750  -0.1234   0.04942   0.04544  -0.0168   0.5897   0.0229
  -3.500  -0.0950   0.04689   0.04277  -0.0181   0.5857   0.0247
  -3.250  -0.0534   0.04512   0.04074  -0.0198   0.5814   0.0260
  -3.000  -0.0254   0.04240   0.03784  -0.0204   0.5772   0.0260
  -2.750  -0.0085   0.03779   0.03310  -0.0207   0.5736   0.0269
  -2.500   0.0145   0.03589   0.03114  -0.0210   0.5693   0.0275
  -2.250   0.0399   0.03410   0.02926  -0.0213   0.5648   0.0284
  -2.000   0.0670   0.03236   0.02737  -0.0215   0.5609   0.0300
  -1.750   0.1031   0.03144   0.02617  -0.0214   0.5570   0.0334
  -1.500   0.1329   0.02973   0.02428  -0.0212   0.5527   0.0337
  -1.250   0.1554   0.02574   0.02009  -0.0212   0.5488   0.0351
  -1.000   0.1811   0.02453   0.01877  -0.0214   0.5450   0.0360
  -0.750   0.2081   0.02342   0.01755  -0.0215   0.5411   0.0375
  -0.500   0.2367   0.02226   0.01627  -0.0215   0.5368   0.0405
  -0.250   0.2694   0.02213   0.01588  -0.0210   0.5326   0.0439
   0.000   0.2942   0.01922   0.01274  -0.0210   0.5290   0.0466
   0.250   0.3217   0.01851   0.01199  -0.0213   0.5251   0.0490
   0.500   0.3526   0.01890   0.01222  -0.0211   0.5207   0.0561
   0.750   0.3789   0.01671   0.00988  -0.0212   0.5169   0.0599
   1.000   0.4067   0.01626   0.00934  -0.0214   0.5130   0.0639
   1.250   0.4354   0.01561   0.00858  -0.0215   0.5091   0.0735
   1.500   0.4636   0.01517   0.00813  -0.0217   0.5049   0.0790
   1.750   0.4920   0.01461   0.00744  -0.0218   0.5011   0.0885
   2.000   0.5205   0.01423   0.00701  -0.0219   0.4972   0.0945
   2.250   0.5492   0.01363   0.00635  -0.0220   0.4931   0.1028
   2.500   0.5796   0.01155   0.00387  -0.0205   0.4898   0.0430
   2.750   0.6070   0.01135   0.00362  -0.0204   0.4860   0.0433
   3.000   0.6347   0.01123   0.00352  -0.0205   0.4821   0.0442
   3.250   0.6621   0.01100   0.00330  -0.0205   0.4779   0.0454
   3.500   0.6898   0.01090   0.00320  -0.0205   0.4740   0.0463
   3.750   0.7176   0.01091   0.00316  -0.0206   0.4703   0.0485
   4.000   0.7458   0.01089   0.00319  -0.0208   0.4663   0.0539
   4.250   0.7735   0.01078   0.00330  -0.0210   0.4620   0.1419
   4.500   0.8744   0.00963   0.00387  -0.0375   0.4561   1.0000
   4.750   0.9009   0.00972   0.00396  -0.0374   0.4522   1.0000
   5.000   0.9272   0.00978   0.00404  -0.0373   0.4473   1.0000
   5.250   0.9531   0.00989   0.00408  -0.0372   0.4410   1.0000
   5.500   0.9793   0.00992   0.00419  -0.0371   0.4347   1.0000
   5.750   1.0052   0.01002   0.00424  -0.0369   0.4271   1.0000
   6.000   1.0312   0.01006   0.00433  -0.0368   0.4181   1.0000
   6.250   1.0570   0.01020   0.00444  -0.0367   0.4106   1.0000
   6.500   1.0828   0.01029   0.00457  -0.0366   0.3997   1.0000
   6.750   1.1084   0.01043   0.00470  -0.0365   0.3851   1.0000
   7.000   1.1337   0.01064   0.00488  -0.0364   0.3647   1.0000
   7.250   1.1579   0.01119   0.00522  -0.0364   0.3200   1.0000
   7.500   1.1662   0.01516   0.00784  -0.0370   0.0963   1.0000
   7.750   1.1778   0.01726   0.00954  -0.0362   0.0223   1.0000
   8.000   1.1974   0.01790   0.01027  -0.0354   0.0201   1.0000
   8.250   1.2155   0.01863   0.01110  -0.0345   0.0189   1.0000
   8.500   1.2312   0.01952   0.01208  -0.0334   0.0178   1.0000
   8.750   1.2434   0.02060   0.01326  -0.0320   0.0169   1.0000
   9.000   1.2495   0.02206   0.01483  -0.0301   0.0160   1.0000
   9.250   1.2429   0.02424   0.01714  -0.0278   0.0154   1.0000
   9.500   1.2315   0.02699   0.02002  -0.0255   0.0150   1.0000
   9.750   1.2335   0.02914   0.02225  -0.0247   0.0148   1.0000
  10.000   1.2353   0.03146   0.02466  -0.0241   0.0145   1.0000
  10.250   1.2357   0.03400   0.02729  -0.0235   0.0143   1.0000
  10.500   1.2351   0.03668   0.03005  -0.0230   0.0141   1.0000
  10.750   1.2339   0.03942   0.03288  -0.0225   0.0139   1.0000
  11.000   1.2323   0.04221   0.03575  -0.0220   0.0137   1.0000
  11.250   1.2308   0.04498   0.03860  -0.0214   0.0135   1.0000
  11.500   1.2296   0.04767   0.04137  -0.0208   0.0133   1.0000
  11.750   1.2293   0.05025   0.04401  -0.0201   0.0131   1.0000
  12.000   1.2305   0.05260   0.04643  -0.0192   0.0130   1.0000
  12.250   1.2339   0.05478   0.04866  -0.0184   0.0127   1.0000
  12.500   1.2388   0.05680   0.05072  -0.0177   0.0123   1.0000
  12.750   1.2445   0.05870   0.05263  -0.0169   0.0119   1.0000
  13.000   1.2514   0.06037   0.05432  -0.0159   0.0115   1.0000
  13.250   1.2615   0.06153   0.05550  -0.0143   0.0114   1.0000
  13.500   1.2745   0.06232   0.05633  -0.0122   0.0112   1.0000
  13.750   1.2894   0.06307   0.05714  -0.0101   0.0112   1.0000
  14.000   1.3038   0.06422   0.05841  -0.0082   0.0114   1.0000
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