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NACA M15 AIRFOIL (m15-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA M15 AIRFOIL (m15-il)
Reynolds number: 200,000
Max Cl/Cd: 72.16 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m15-il-200000.txt
Download as CSV file: xf-m15-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M15 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2678   0.09736   0.09405  -0.0373   1.0000   0.0616
  -9.500  -0.2906   0.09344   0.09019  -0.0432   1.0000   0.0626
  -9.250  -0.3062   0.08938   0.08619  -0.0473   1.0000   0.0628
  -9.000  -0.2834   0.08489   0.08172  -0.0428   1.0000   0.0640
  -8.750  -0.2734   0.08252   0.07940  -0.0411   1.0000   0.0651
  -8.500  -0.2776   0.08065   0.07762  -0.0396   0.9982   0.0660
  -8.250  -0.2632   0.07597   0.07293  -0.0437   0.9920   0.0680
  -8.000  -0.4027   0.08091   0.07775  -0.0420   0.9969   0.0643
  -7.750  -0.3762   0.07772   0.07455  -0.0440   0.9916   0.0659
  -7.500  -0.3510   0.07319   0.06995  -0.0504   0.9833   0.0683
  -7.250  -0.3357   0.06637   0.06245  -0.0668   0.9614   0.0742
  -7.000  -0.3149   0.06007   0.05635  -0.0683   0.9540   0.0755
  -6.750  -0.2941   0.05736   0.05365  -0.0687   0.9411   0.0767
  -6.500  -0.2774   0.05493   0.05116  -0.0688   0.9260   0.0785
  -6.250  -0.2629   0.05242   0.04851  -0.0687   0.9107   0.0816
  -6.000  -0.2544   0.04811   0.04364  -0.0697   0.8951   0.0885
  -5.750  -0.2380   0.04584   0.04140  -0.0687   0.8827   0.0899
  -5.500  -0.2214   0.04392   0.03940  -0.0677   0.8712   0.0920
  -5.250  -0.2007   0.04473   0.03943  -0.0662   0.8589   0.1013
  -5.000  -0.1879   0.03901   0.03381  -0.0661   0.8472   0.1035
  -4.750  -0.1686   0.03701   0.03178  -0.0653   0.8362   0.1055
  -4.500  -0.1481   0.03535   0.02997  -0.0644   0.8266   0.1091
  -4.250  -0.1275   0.03342   0.02763  -0.0637   0.8170   0.1192
  -4.000  -0.1027   0.02540   0.01840  -0.0610   0.8108   0.0709
  -3.750  -0.0780   0.02206   0.01429  -0.0596   0.8030   0.0643
  -3.500  -0.0515   0.02092   0.01285  -0.0589   0.7955   0.0636
  -3.250  -0.0248   0.01977   0.01150  -0.0585   0.7882   0.0637
  -3.000   0.0019   0.01867   0.01030  -0.0582   0.7808   0.0648
  -2.750   0.0288   0.01802   0.00957  -0.0579   0.7743   0.0668
  -2.500   0.0562   0.01737   0.00885  -0.0576   0.7666   0.0683
  -2.250   0.0834   0.01673   0.00809  -0.0572   0.7607   0.0697
  -2.000   0.1106   0.01619   0.00751  -0.0569   0.7530   0.0716
  -1.750   0.1377   0.01575   0.00698  -0.0564   0.7464   0.0738
  -1.500   0.1635   0.01512   0.00641  -0.0560   0.7399   0.0778
  -1.250   0.1901   0.01484   0.00614  -0.0557   0.7327   0.0846
  -1.000   0.2160   0.01442   0.00573  -0.0551   0.7268   0.0942
  -0.750   0.2413   0.01393   0.00539  -0.0545   0.7189   0.1216
  -0.500   0.2640   0.01308   0.00510  -0.0537   0.7128   0.2630
  -0.250   0.3432   0.01165   0.00573  -0.0624   0.7051   0.9802
   0.000   0.4173   0.01171   0.00554  -0.0720   0.6970   1.0000
   0.250   0.4429   0.01175   0.00549  -0.0717   0.6890   1.0000
   0.500   0.4683   0.01178   0.00539  -0.0712   0.6815   1.0000
   0.750   0.4935   0.01183   0.00537  -0.0707   0.6732   1.0000
   1.000   0.5187   0.01187   0.00529  -0.0702   0.6651   1.0000
   1.250   0.5438   0.01194   0.00531  -0.0697   0.6565   1.0000
   1.500   0.5689   0.01200   0.00526  -0.0691   0.6484   1.0000
   1.750   0.5937   0.01208   0.00530  -0.0686   0.6391   1.0000
   2.000   0.6188   0.01216   0.00526  -0.0680   0.6310   1.0000
   2.250   0.6433   0.01225   0.00535  -0.0674   0.6210   1.0000
   2.500   0.6684   0.01235   0.00534  -0.0668   0.6131   1.0000
   2.750   0.6927   0.01243   0.00543  -0.0661   0.6026   1.0000
   3.000   0.7173   0.01255   0.00549  -0.0655   0.5939   1.0000
   3.250   0.7418   0.01265   0.00555  -0.0649   0.5845   1.0000
   3.500   0.7660   0.01278   0.00568  -0.0642   0.5751   1.0000
   3.750   0.7907   0.01289   0.00572  -0.0636   0.5668   1.0000
   4.000   0.8146   0.01304   0.00589  -0.0629   0.5572   1.0000
   4.250   0.8394   0.01317   0.00594  -0.0623   0.5497   1.0000
   4.500   0.8629   0.01332   0.00614  -0.0615   0.5399   1.0000
   4.750   0.8873   0.01347   0.00625  -0.0608   0.5319   1.0000
   5.000   0.9108   0.01358   0.00638  -0.0600   0.5217   1.0000
   5.250   0.9342   0.01372   0.00652  -0.0592   0.5115   1.0000
   5.500   0.9583   0.01388   0.00659  -0.0585   0.5030   1.0000
   5.750   0.9814   0.01408   0.00687  -0.0577   0.4938   1.0000
   6.000   1.0056   0.01431   0.00706  -0.0570   0.4864   1.0000
   6.250   1.0286   0.01454   0.00735  -0.0562   0.4775   1.0000
   6.500   1.0526   0.01481   0.00760  -0.0556   0.4701   1.0000
   6.750   1.0755   0.01508   0.00794  -0.0548   0.4617   1.0000
   7.000   1.0992   0.01538   0.00823  -0.0541   0.4540   1.0000
   7.250   1.1218   0.01566   0.00857  -0.0532   0.4453   1.0000
   7.500   1.1449   0.01599   0.00894  -0.0525   0.4368   1.0000
   7.750   1.1673   0.01627   0.00918  -0.0516   0.4258   1.0000
   8.000   1.1870   0.01649   0.00946  -0.0502   0.4119   1.0000
   8.250   1.2064   0.01673   0.00973  -0.0488   0.3970   1.0000
   8.500   1.2252   0.01698   0.01003  -0.0473   0.3817   1.0000
   8.750   1.2436   0.01725   0.01033  -0.0458   0.3658   1.0000
   9.000   1.2618   0.01756   0.01070  -0.0443   0.3504   1.0000
   9.250   1.2793   0.01791   0.01109  -0.0427   0.3342   1.0000
   9.500   1.2951   0.01834   0.01154  -0.0409   0.3162   1.0000
   9.750   1.3097   0.01881   0.01206  -0.0390   0.2942   1.0000
  10.000   1.3202   0.01948   0.01268  -0.0365   0.2685   1.0000
  10.250   1.3258   0.02039   0.01348  -0.0335   0.2378   1.0000
  10.500   1.3231   0.02159   0.01452  -0.0292   0.2051   1.0000
  10.750   1.3149   0.02337   0.01609  -0.0250   0.1694   1.0000
  11.000   1.3024   0.02580   0.01825  -0.0212   0.1237   1.0000
  11.250   1.2868   0.02886   0.02099  -0.0180   0.0863   1.0000
  11.500   1.2759   0.03189   0.02390  -0.0157   0.0707   1.0000
  11.750   1.2697   0.03473   0.02676  -0.0141   0.0625   1.0000
  12.000   1.2612   0.03794   0.02998  -0.0128   0.0577   1.0000
  12.250   1.2597   0.04062   0.03276  -0.0119   0.0537   1.0000
  12.500   1.2543   0.04372   0.03591  -0.0111   0.0509   1.0000
  12.750   1.2466   0.04708   0.03930  -0.0103   0.0487   1.0000
  13.000   1.2474   0.04966   0.04199  -0.0097   0.0464   1.0000
  13.250   1.2468   0.05239   0.04480  -0.0092   0.0443   1.0000
  13.500   1.2447   0.05527   0.04769  -0.0087   0.0426   1.0000
  13.750   1.2430   0.05796   0.05034  -0.0076   0.0410   1.0000
  14.000   1.2475   0.06023   0.05275  -0.0071   0.0398   1.0000
  14.250   1.2523   0.06245   0.05505  -0.0064   0.0385   1.0000
  14.500   1.2575   0.06462   0.05727  -0.0059   0.0372   1.0000
  14.750   1.2636   0.06667   0.05933  -0.0052   0.0360   1.0000
  15.000   1.2775   0.06745   0.05999  -0.0030   0.0344   1.0000
  15.250   1.2810   0.07004   0.06277  -0.0030   0.0336   1.0000
  15.500   1.2861   0.07244   0.06531  -0.0027   0.0328   1.0000
  15.750   1.2926   0.07468   0.06768  -0.0022   0.0320   1.0000
  16.000   1.2991   0.07693   0.07004  -0.0017   0.0313   1.0000
  16.250   1.3038   0.07943   0.07266  -0.0014   0.0307   1.0000
  16.500   1.3086   0.08195   0.07529  -0.0012   0.0301   1.0000
  16.750   1.3149   0.08429   0.07769  -0.0008   0.0295   1.0000
  17.000   1.3308   0.08593   0.07934   0.0011   0.0286   1.0000
  17.250   1.3203   0.09040   0.08405  -0.0002   0.0284   1.0000
  17.500   1.3095   0.09514   0.08903  -0.0017   0.0282   1.0000
  17.750   1.2978   0.10021   0.09434  -0.0035   0.0280   1.0000
  18.000   1.2854   0.10562   0.09998  -0.0056   0.0278   1.0000
  18.250   1.2716   0.11144   0.10603  -0.0082   0.0277   1.0000
  18.500   1.2568   0.11762   0.11244  -0.0111   0.0277   1.0000
  18.750   1.2405   0.12434   0.11939  -0.0145   0.0277   1.0000
  19.000   1.2229   0.13158   0.12683  -0.0186   0.0277   1.0000
  19.250   1.2042   0.13938   0.13484  -0.0232   0.0279   1.0000
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