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NACA M23 AIRFOIL (m23-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M23 AIRFOIL (m23-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.57 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m23-il-1000000.txt
Download as CSV file: xf-m23-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4421   0.12130   0.11881   0.0315   0.6457   0.0095
  -9.000  -0.4367   0.11783   0.11535   0.0298   0.6413   0.0095
  -8.750  -0.4331   0.11360   0.11111   0.0292   0.6368   0.0097
  -8.500  -0.4270   0.11054   0.10801   0.0280   0.6320   0.0098
  -8.250  -0.4207   0.10756   0.10504   0.0267   0.6276   0.0099
  -8.000  -0.4144   0.10459   0.10206   0.0251   0.6228   0.0101
  -7.750  -0.4084   0.10157   0.09902   0.0233   0.6183   0.0103
  -7.500  -0.4030   0.09849   0.09594   0.0212   0.6142   0.0106
  -7.250  -0.3977   0.09543   0.09287   0.0189   0.6100   0.0111
  -7.000  -0.3852   0.09153   0.08894   0.0148   0.6059   0.0123
  -6.500  -0.3549   0.08362   0.08095   0.0060   0.5982   0.0125
  -6.250  -0.2818   0.06532   0.06276  -0.0011   0.5840   0.0128
  -6.000  -0.2706   0.06213   0.05955  -0.0022   0.5799   0.0130
  -5.750  -0.2574   0.05897   0.05634  -0.0038   0.5758   0.0134
  -5.500  -0.2429   0.05551   0.05283  -0.0057   0.5718   0.0139
  -5.250  -0.2268   0.05177   0.04906  -0.0078   0.5683   0.0149
  -4.750  -0.2137   0.05933   0.05620  -0.0114   0.5695   0.0160
  -4.500  -0.1889   0.05575   0.05252  -0.0132   0.5656   0.0160
  -3.750  -0.1263   0.04688   0.04345  -0.0159   0.5537   0.0172
  -3.500  -0.1006   0.04464   0.04112  -0.0169   0.5494   0.0184
  -3.250  -0.0632   0.04204   0.03830  -0.0183   0.5456   0.0202
  -3.000  -0.0354   0.03924   0.03535  -0.0188   0.5419   0.0203
  -2.750  -0.0103   0.03417   0.03008  -0.0190   0.5388   0.0207
  -2.500   0.0130   0.03245   0.02829  -0.0193   0.5345   0.0211
  -2.250   0.0380   0.03105   0.02681  -0.0196   0.5303   0.0216
  -2.000   0.0644   0.02958   0.02523  -0.0199   0.5266   0.0223
  -1.750   0.0921   0.02795   0.02350  -0.0200   0.5229   0.0236
  -1.500   0.1261   0.02660   0.02196  -0.0196   0.5190   0.0259
  -1.250   0.1546   0.02452   0.01968  -0.0193   0.5151   0.0260
  -1.000   0.1826   0.02244   0.01742  -0.0190   0.5116   0.0260
  -0.750   0.2073   0.01862   0.01330  -0.0185   0.5085   0.0272
  -0.500   0.2346   0.01790   0.01251  -0.0187   0.5045   0.0278
  -0.250   0.2623   0.01714   0.01164  -0.0189   0.5003   0.0287
   0.000   0.2906   0.01615   0.01052  -0.0188   0.4967   0.0304
   0.250   0.3207   0.01608   0.01035  -0.0187   0.4929   0.0335
   0.500   0.3482   0.01345   0.00733  -0.0183   0.4895   0.0350
   0.750   0.3763   0.01281   0.00661  -0.0185   0.4855   0.0363
   1.000   0.4046   0.01237   0.00614  -0.0187   0.4818   0.0376
   1.250   0.4332   0.01194   0.00565  -0.0188   0.4780   0.0393
   1.500   0.4619   0.01166   0.00530  -0.0190   0.4742   0.0418
   1.750   0.4902   0.01114   0.00467  -0.0192   0.4701   0.0477
   2.000   0.5187   0.01082   0.00437  -0.0194   0.4667   0.0502
   2.250   0.5470   0.00961   0.00297  -0.0186   0.4631   0.0320
   2.500   0.5750   0.00942   0.00275  -0.0187   0.4592   0.0327
   2.750   0.6031   0.00934   0.00263  -0.0188   0.4551   0.0333
   3.000   0.6312   0.00920   0.00251  -0.0190   0.4519   0.0335
   3.250   0.6593   0.00909   0.00241  -0.0191   0.4479   0.0337
   3.500   0.6871   0.00897   0.00226  -0.0192   0.4439   0.0345
   3.750   0.7152   0.00893   0.00219  -0.0194   0.4400   0.0353
   4.000   0.7436   0.00887   0.00217  -0.0197   0.4366   0.0363
   4.250   0.7720   0.00886   0.00216  -0.0199   0.4325   0.0394
   4.500   0.8004   0.00890   0.00219  -0.0202   0.4284   0.0440
   4.750   0.8282   0.00883   0.00234  -0.0205   0.4244   0.1610
   5.000   0.8471   0.00728   0.00258  -0.0187   0.4185   0.9803
   5.250   0.9197   0.00764   0.00290  -0.0291   0.4087   0.9956
   5.500   0.9805   0.00787   0.00309  -0.0368   0.3983   0.9997
   5.750   1.0096   0.00795   0.00318  -0.0374   0.3895   1.0000
   6.000   1.0359   0.00809   0.00327  -0.0374   0.3780   1.0000
   6.250   1.0620   0.00826   0.00339  -0.0374   0.3639   1.0000
   6.500   1.0880   0.00855   0.00359  -0.0375   0.3402   1.0000
   6.750   1.1127   0.00949   0.00412  -0.0380   0.2670   1.0000
   7.000   1.1266   0.01362   0.00687  -0.0393   0.0193   1.0000
   7.250   1.1495   0.01408   0.00735  -0.0389   0.0158   1.0000
   7.500   1.1721   0.01452   0.00785  -0.0385   0.0146   1.0000
   7.750   1.1941   0.01498   0.00835  -0.0379   0.0138   1.0000
   8.000   1.2152   0.01552   0.00894  -0.0373   0.0129   1.0000
   8.250   1.2350   0.01614   0.00960  -0.0366   0.0120   1.0000
   8.500   1.2513   0.01710   0.01065  -0.0356   0.0110   1.0000
   8.750   1.2644   0.01821   0.01188  -0.0341   0.0104   1.0000
   9.000   1.2800   0.01891   0.01263  -0.0329   0.0102   1.0000
   9.250   1.2924   0.01979   0.01357  -0.0314   0.0099   1.0000
   9.500   1.3010   0.02087   0.01472  -0.0296   0.0096   1.0000
   9.750   1.2994   0.02250   0.01643  -0.0275   0.0093   1.0000
  10.000   1.2976   0.02437   0.01838  -0.0255   0.0091   1.0000
  10.250   1.3003   0.02644   0.02052  -0.0248   0.0089   1.0000
  10.500   1.3035   0.02865   0.02281  -0.0243   0.0086   1.0000
  10.750   1.3068   0.03091   0.02513  -0.0239   0.0084   1.0000
  11.000   1.3089   0.03333   0.02760  -0.0236   0.0081   1.0000
  11.250   1.3074   0.03612   0.03045  -0.0232   0.0079   1.0000
  11.500   1.3005   0.03947   0.03387  -0.0227   0.0076   1.0000
  11.750   1.2873   0.04336   0.03785  -0.0219   0.0074   1.0000
  12.000   1.2771   0.04677   0.04133  -0.0208   0.0073   1.0000
  12.250   1.2827   0.04887   0.04349  -0.0206   0.0072   1.0000
  12.500   1.2873   0.05109   0.04578  -0.0203   0.0071   1.0000
  12.750   1.2911   0.05340   0.04815  -0.0200   0.0069   1.0000
  13.000   1.2951   0.05567   0.05049  -0.0196   0.0068   1.0000
  13.250   1.2992   0.05791   0.05279  -0.0192   0.0067   1.0000
  13.500   1.3036   0.06008   0.05502  -0.0187   0.0066   1.0000
  13.750   1.3088   0.06215   0.05715  -0.0181   0.0064   1.0000
  14.000   1.3145   0.06417   0.05923  -0.0176   0.0063   1.0000
  14.250   1.3200   0.06621   0.06133  -0.0170   0.0061   1.0000
  14.500   1.3254   0.06830   0.06349  -0.0165   0.0060   1.0000
  14.750   1.3306   0.07046   0.06572  -0.0161   0.0058   1.0000
  15.000   1.3356   0.07269   0.06803  -0.0158   0.0057   1.0000
  15.250   1.3399   0.07510   0.07049  -0.0158   0.0056   1.0000
  15.500   1.3431   0.07765   0.07311  -0.0157   0.0055   1.0000
  15.750   1.3459   0.08030   0.07583  -0.0157   0.0054   1.0000
  16.000   1.3475   0.08320   0.07880  -0.0161   0.0052   1.0000
  16.250   1.3487   0.08605   0.08172  -0.0162   0.0051   1.0000
  16.500   1.3469   0.08849   0.08431  -0.0136   0.0049   1.0000
  16.750   1.3361   0.09310   0.08915  -0.0124   0.0049   1.0000
  17.000   1.3290   0.09797   0.09415  -0.0154   0.0048   1.0000
  17.250   1.3209   0.10274   0.09907  -0.0167   0.0048   1.0000
  17.500   1.3114   0.10786   0.10435  -0.0184   0.0048   1.0000
  17.750   1.2999   0.11340   0.11005  -0.0202   0.0048   1.0000
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