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NACA M3 (nacam3-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA M3 (nacam3-il)
Reynolds number: 50,000
Max Cl/Cd: 26.62 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nacam3-il-50000-n5.txt
Download as CSV file: xf-nacam3-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M3                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7467   0.09622   0.08831  -0.0209   1.0000   0.0723
 -11.750  -0.7795   0.08618   0.07821  -0.0276   1.0000   0.0716
 -11.500  -0.8133   0.07808   0.06998  -0.0323   1.0000   0.0710
 -11.250  -0.8437   0.07199   0.06371  -0.0342   1.0000   0.0707
 -11.000  -0.8695   0.06731   0.05882  -0.0336   1.0000   0.0707
 -10.750  -0.8910   0.06351   0.05477  -0.0315   1.0000   0.0710
 -10.500  -0.9052   0.05980   0.05074  -0.0293   1.0000   0.0716
 -10.250  -0.9135   0.05627   0.04682  -0.0271   1.0000   0.0724
 -10.000  -0.9158   0.05294   0.04305  -0.0249   1.0000   0.0732
  -9.750  -0.9126   0.04984   0.03949  -0.0228   1.0000   0.0739
  -9.500  -0.8996   0.04724   0.03675  -0.0216   1.0000   0.0751
  -9.250  -0.8848   0.04520   0.03457  -0.0205   1.0000   0.0771
  -9.000  -0.8702   0.04329   0.03248  -0.0192   1.0000   0.0797
  -8.750  -0.8546   0.04129   0.03020  -0.0179   1.0000   0.0825
  -8.500  -0.8368   0.03926   0.02782  -0.0167   1.0000   0.0851
  -8.250  -0.8158   0.03735   0.02569  -0.0158   1.0000   0.0873
  -8.000  -0.7944   0.03576   0.02409  -0.0150   1.0000   0.0901
  -7.750  -0.7737   0.03437   0.02261  -0.0140   1.0000   0.0943
  -7.500  -0.7522   0.03304   0.02104  -0.0129   1.0000   0.1000
  -7.250  -0.7326   0.03176   0.01987  -0.0118   1.0000   0.1056
  -7.000  -0.7117   0.03055   0.01850  -0.0106   1.0000   0.1129
  -6.750  -0.6933   0.02933   0.01736  -0.0092   1.0000   0.1209
  -6.500  -0.6757   0.02819   0.01625  -0.0076   1.0000   0.1335
  -6.250  -0.6590   0.02706   0.01521  -0.0060   1.0000   0.1515
  -6.000  -0.6429   0.02593   0.01422  -0.0043   1.0000   0.1763
  -5.750  -0.6278   0.02484   0.01335  -0.0025   1.0000   0.2105
  -5.500  -0.6136   0.02381   0.01262  -0.0006   1.0000   0.2581
  -5.250  -0.6001   0.02287   0.01205   0.0016   1.0000   0.3182
  -5.000  -0.5863   0.02207   0.01161   0.0040   1.0000   0.3813
  -4.750  -0.5709   0.02145   0.01124   0.0063   1.0000   0.4394
  -4.500  -0.5542   0.02098   0.01097   0.0087   1.0000   0.4935
  -4.250  -0.5369   0.02063   0.01082   0.0111   1.0000   0.5451
  -4.000  -0.5190   0.02041   0.01074   0.0136   1.0000   0.5946
  -3.750  -0.5002   0.02028   0.01072   0.0161   1.0000   0.6403
  -3.500  -0.4802   0.02024   0.01074   0.0184   1.0000   0.6814
  -3.250  -0.4596   0.02025   0.01077   0.0206   1.0000   0.7188
  -3.000  -0.4371   0.02034   0.01085   0.0225   1.0000   0.7526
  -2.750  -0.4136   0.02047   0.01094   0.0241   1.0000   0.7845
  -2.500  -0.3882   0.02064   0.01106   0.0254   1.0000   0.8139
  -2.250  -0.3583   0.02086   0.01120   0.0257   1.0000   0.8400
  -2.000  -0.3286   0.02103   0.01129   0.0257   1.0000   0.8656
  -1.750  -0.2919   0.02125   0.01140   0.0242   1.0000   0.8876
  -1.500  -0.2553   0.02142   0.01147   0.0225   1.0000   0.9095
  -1.250  -0.2137   0.02157   0.01153   0.0196   1.0000   0.9289
  -1.000  -0.1656   0.02170   0.01158   0.0152   1.0000   0.9456
  -0.750  -0.1176   0.02177   0.01158   0.0106   1.0000   0.9615
  -0.500  -0.0706   0.02179   0.01157   0.0059   1.0000   0.9770
  -0.250  -0.0237   0.02179   0.01155   0.0010   1.0000   0.9922
   0.000   0.0000   0.02178   0.01154   0.0000   1.0000   1.0000
   0.250   0.0237   0.02179   0.01155  -0.0010   0.9922   1.0000
   0.500   0.0706   0.02179   0.01157  -0.0059   0.9770   1.0000
   0.750   0.1176   0.02177   0.01158  -0.0106   0.9615   1.0000
   1.000   0.1655   0.02170   0.01157  -0.0152   0.9456   1.0000
   1.250   0.2136   0.02157   0.01153  -0.0196   0.9289   1.0000
   1.500   0.2553   0.02141   0.01147  -0.0225   0.9095   1.0000
   1.750   0.2918   0.02125   0.01140  -0.0242   0.8876   1.0000
   2.000   0.3286   0.02103   0.01128  -0.0257   0.8656   1.0000
   2.250   0.3583   0.02085   0.01119  -0.0256   0.8400   1.0000
   2.500   0.3882   0.02063   0.01105  -0.0253   0.8139   1.0000
   2.750   0.4136   0.02047   0.01094  -0.0241   0.7845   1.0000
   3.000   0.4370   0.02034   0.01084  -0.0225   0.7527   1.0000
   3.250   0.4595   0.02025   0.01077  -0.0206   0.7188   1.0000
   3.500   0.4801   0.02024   0.01074  -0.0184   0.6814   1.0000
   3.750   0.5001   0.02028   0.01072  -0.0161   0.6403   1.0000
   4.000   0.5189   0.02040   0.01074  -0.0136   0.5946   1.0000
   4.250   0.5368   0.02063   0.01082  -0.0111   0.5452   1.0000
   4.500   0.5541   0.02098   0.01097  -0.0086   0.4936   1.0000
   4.750   0.5709   0.02145   0.01124  -0.0063   0.4395   1.0000
   5.000   0.5863   0.02207   0.01160  -0.0040   0.3814   1.0000
   5.250   0.6001   0.02287   0.01205  -0.0016   0.3182   1.0000
   5.500   0.6135   0.02381   0.01262   0.0006   0.2581   1.0000
   5.750   0.6278   0.02483   0.01334   0.0025   0.2106   1.0000
   6.000   0.6429   0.02593   0.01422   0.0043   0.1763   1.0000
   6.250   0.6590   0.02706   0.01520   0.0060   0.1515   1.0000
   6.500   0.6757   0.02819   0.01625   0.0076   0.1335   1.0000
   6.750   0.6934   0.02933   0.01736   0.0092   0.1209   1.0000
   7.000   0.7117   0.03055   0.01850   0.0106   0.1129   1.0000
   7.250   0.7327   0.03176   0.01987   0.0118   0.1056   1.0000
   7.500   0.7522   0.03304   0.02104   0.0129   0.1000   1.0000
   7.750   0.7738   0.03437   0.02261   0.0140   0.0943   1.0000
   8.000   0.7945   0.03576   0.02409   0.0150   0.0901   1.0000
   8.250   0.8159   0.03735   0.02569   0.0157   0.0873   1.0000
   8.500   0.8369   0.03926   0.02781   0.0167   0.0851   1.0000
   8.750   0.8548   0.04129   0.03020   0.0179   0.0825   1.0000
   9.000   0.8703   0.04329   0.03248   0.0192   0.0797   1.0000
   9.250   0.8850   0.04520   0.03457   0.0205   0.0770   1.0000
   9.500   0.8998   0.04725   0.03675   0.0216   0.0751   1.0000
   9.750   0.9128   0.04985   0.03950   0.0228   0.0739   1.0000
  10.000   0.9160   0.05295   0.04306   0.0248   0.0732   1.0000
  10.250   0.9137   0.05629   0.04683   0.0270   0.0724   1.0000
  10.500   0.9055   0.05982   0.05076   0.0292   0.0716   1.0000
  10.750   0.8912   0.06353   0.05480   0.0314   0.0710   1.0000
  11.000   0.8699   0.06734   0.05886   0.0335   0.0707   1.0000
  11.250   0.8441   0.07203   0.06376   0.0340   0.0706   1.0000
  11.500   0.8137   0.07815   0.07006   0.0321   0.0710   1.0000
  11.750   0.7800   0.08628   0.07831   0.0274   0.0716   1.0000
  12.000   0.7472   0.09639   0.08848   0.0206   0.0723   1.0000
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