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NACA M15 AIRFOIL (m15-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA M15 AIRFOIL (m15-il)
Reynolds number: 50,000
Max Cl/Cd: 29.99 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m15-il-50000-n5.txt
Download as CSV file: xf-m15-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3541   0.11169   0.10460  -0.0281   1.0000   0.1331
  -9.250  -0.3618   0.10939   0.10240  -0.0309   1.0000   0.1380
  -9.000  -0.3817   0.10755   0.10072  -0.0354   1.0000   0.1396
  -8.750  -0.3595   0.10254   0.09572  -0.0332   1.0000   0.1424
  -8.500  -0.3483   0.09930   0.09250  -0.0326   1.0000   0.1463
  -8.250  -0.3490   0.09648   0.08977  -0.0334   1.0000   0.1496
  -8.000  -0.3639   0.09430   0.08775  -0.0345   1.0000   0.1534
  -7.750  -0.4062   0.09389   0.08755  -0.0356   1.0000   0.1559
  -7.250  -0.4323   0.08277   0.07635  -0.0358   1.0000   0.0914
  -6.750  -0.4047   0.07029   0.06331  -0.0469   0.9771   0.0785
  -6.500  -0.3813   0.06632   0.05925  -0.0496   0.9678   0.0775
  -6.250  -0.3571   0.06194   0.05462  -0.0534   0.9588   0.0771
  -6.000  -0.3361   0.05786   0.05018  -0.0561   0.9477   0.0775
  -5.750  -0.3130   0.05405   0.04600  -0.0585   0.9380   0.0777
  -5.500  -0.2860   0.05050   0.04211  -0.0608   0.9299   0.0774
  -5.250  -0.2634   0.04751   0.03878  -0.0617   0.9199   0.0770
  -5.000  -0.2345   0.04443   0.03528  -0.0634   0.9126   0.0767
  -4.750  -0.2119   0.04200   0.03243  -0.0635   0.9024   0.0767
  -4.500  -0.1811   0.03949   0.02944  -0.0648   0.8958   0.0773
  -4.250  -0.1577   0.03767   0.02712  -0.0644   0.8855   0.0788
  -4.000  -0.1259   0.03597   0.02529  -0.0657   0.8793   0.0812
  -3.750  -0.1023   0.03472   0.02382  -0.0653   0.8689   0.0828
  -3.500  -0.0700   0.03317   0.02194  -0.0660   0.8621   0.0842
  -3.250  -0.0435   0.03199   0.02050  -0.0656   0.8521   0.0858
  -3.000  -0.0121   0.03078   0.01899  -0.0659   0.8440   0.0881
  -2.750   0.0178   0.02983   0.01774  -0.0659   0.8347   0.0917
  -2.500   0.0473   0.02900   0.01689  -0.0660   0.8258   0.0967
  -2.250   0.0798   0.02825   0.01599  -0.0664   0.8175   0.1031
  -2.000   0.1111   0.02756   0.01513  -0.0666   0.8087   0.1091
  -1.750   0.1408   0.02691   0.01445  -0.0666   0.8008   0.1193
  -1.500   0.1659   0.02646   0.01400  -0.0660   0.7916   0.1351
  -1.250   0.1929   0.02581   0.01344  -0.0656   0.7841   0.1622
  -1.000   0.3102   0.02220   0.01262  -0.0812   0.7812   1.0000
  -0.750   0.3313   0.02242   0.01253  -0.0799   0.7706   1.0000
  -0.500   0.3545   0.02257   0.01240  -0.0790   0.7617   1.0000
  -0.250   0.3774   0.02272   0.01231  -0.0779   0.7525   1.0000
   0.000   0.3990   0.02295   0.01235  -0.0768   0.7428   1.0000
   0.250   0.4232   0.02305   0.01225  -0.0759   0.7348   1.0000
   0.500   0.4436   0.02336   0.01242  -0.0747   0.7245   1.0000
   0.750   0.4690   0.02342   0.01229  -0.0738   0.7172   1.0000
   1.000   0.4884   0.02380   0.01259  -0.0725   0.7063   1.0000
   1.250   0.5118   0.02399   0.01265  -0.0715   0.6981   1.0000
   1.500   0.5334   0.02427   0.01284  -0.0704   0.6885   1.0000
   1.750   0.5548   0.02459   0.01307  -0.0693   0.6792   1.0000
   2.000   0.5784   0.02479   0.01318  -0.0683   0.6709   1.0000
   2.250   0.5983   0.02521   0.01356  -0.0670   0.6609   1.0000
   2.500   0.6233   0.02535   0.01361  -0.0662   0.6534   1.0000
   2.750   0.6417   0.02588   0.01413  -0.0648   0.6430   1.0000
   3.000   0.6678   0.02599   0.01416  -0.0641   0.6363   1.0000
   3.250   0.6850   0.02662   0.01481  -0.0626   0.6254   1.0000
   3.500   0.7099   0.02681   0.01495  -0.0618   0.6183   1.0000
   3.750   0.7278   0.02743   0.01562  -0.0604   0.6082   1.0000
   4.000   0.7507   0.02777   0.01594  -0.0595   0.6005   1.0000
   4.250   0.7701   0.02832   0.01652  -0.0582   0.5913   1.0000
   4.500   0.7912   0.02880   0.01703  -0.0572   0.5833   1.0000
   4.750   0.8116   0.02930   0.01757  -0.0560   0.5747   1.0000
   5.000   0.8310   0.02989   0.01821  -0.0548   0.5663   1.0000
   5.250   0.8524   0.03035   0.01872  -0.0538   0.5584   1.0000
   5.500   0.8701   0.03106   0.01951  -0.0525   0.5497   1.0000
   5.750   0.8926   0.03145   0.01995  -0.0516   0.5422   1.0000
   6.000   0.9084   0.03228   0.02088  -0.0501   0.5332   1.0000
   6.250   0.9328   0.03253   0.02120  -0.0493   0.5261   1.0000
   6.500   0.9461   0.03350   0.02229  -0.0477   0.5165   1.0000
   6.750   0.9741   0.03346   0.02231  -0.0471   0.5097   1.0000
   7.000   0.9849   0.03453   0.02351  -0.0452   0.4992   1.0000
   7.250   1.0108   0.03456   0.02363  -0.0444   0.4914   1.0000
   7.500   1.0269   0.03522   0.02441  -0.0428   0.4814   1.0000
   7.750   1.0426   0.03594   0.02525  -0.0413   0.4717   1.0000
   8.000   1.0707   0.03583   0.02525  -0.0406   0.4639   1.0000
   8.250   1.0792   0.03706   0.02663  -0.0385   0.4534   1.0000
   8.500   1.1081   0.03695   0.02661  -0.0380   0.4456   1.0000
   8.750   1.1174   0.03811   0.02795  -0.0360   0.4353   1.0000
   9.000   1.1319   0.03896   0.02895  -0.0344   0.4258   1.0000
   9.250   1.1589   0.03896   0.02909  -0.0337   0.4168   1.0000
   9.500   1.1598   0.04064   0.03096  -0.0310   0.4059   1.0000
   9.750   1.1803   0.04103   0.03149  -0.0298   0.3962   1.0000
  10.000   1.1959   0.04166   0.03228  -0.0281   0.3856   1.0000
  10.250   1.1889   0.04354   0.03434  -0.0247   0.3740   1.0000
  10.500   1.1931   0.04447   0.03538  -0.0221   0.3607   1.0000
  10.750   1.1945   0.04545   0.03644  -0.0195   0.3455   1.0000
  11.000   1.1918   0.04686   0.03793  -0.0171   0.3295   1.0000
  11.250   1.1872   0.04865   0.03980  -0.0151   0.3129   1.0000
  11.500   1.1831   0.05069   0.04191  -0.0136   0.2964   1.0000
  11.750   1.1805   0.05284   0.04415  -0.0124   0.2802   1.0000
  12.000   1.1795   0.05491   0.04627  -0.0113   0.2632   1.0000
  12.250   1.1764   0.05736   0.04877  -0.0105   0.2455   1.0000
  12.500   1.1691   0.06059   0.05206  -0.0101   0.2275   1.0000
  12.750   1.1634   0.06362   0.05508  -0.0097   0.2081   1.0000
  13.000   1.1578   0.06661   0.05794  -0.0092   0.1883   1.0000
  13.250   1.1478   0.07051   0.06183  -0.0093   0.1696   1.0000
  13.500   1.1376   0.07457   0.06581  -0.0095   0.1516   1.0000
  13.750   1.1275   0.07881   0.06996  -0.0099   0.1355   1.0000
  14.000   1.1179   0.08316   0.07423  -0.0104   0.1213   1.0000
  14.250   1.1096   0.08750   0.07851  -0.0111   0.1094   1.0000
  14.500   1.1029   0.09167   0.08262  -0.0117   0.0998   1.0000
  14.750   1.0976   0.09564   0.08647  -0.0124   0.0923   1.0000
  15.000   1.0939   0.09961   0.09049  -0.0131   0.0852   1.0000
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