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NACA M2 AIRFOIL (m2-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA M2 AIRFOIL (m2-il)
Reynolds number: 500,000
Max Cl/Cd: 45.94 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m2-il-500000.txt
Download as CSV file: xf-m2-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M2 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.8926   0.05734   0.05486  -0.0160   1.0000   0.0152
 -10.250  -0.9149   0.05221   0.04948  -0.0155   1.0000   0.0151
 -10.000  -0.9346   0.04600   0.04289  -0.0144   1.0000   0.0151
  -9.750  -0.9532   0.03873   0.03505  -0.0125   1.0000   0.0152
  -9.500  -0.9549   0.03361   0.02948  -0.0108   1.0000   0.0155
  -9.250  -0.9381   0.03209   0.02783  -0.0101   1.0000   0.0160
  -9.000  -0.9190   0.03088   0.02651  -0.0096   1.0000   0.0166
  -8.750  -0.9001   0.02933   0.02479  -0.0089   1.0000   0.0172
  -8.500  -0.8807   0.02767   0.02288  -0.0081   1.0000   0.0182
  -8.250  -0.8601   0.02606   0.02095  -0.0073   1.0000   0.0193
  -8.000  -0.8363   0.02550   0.02015  -0.0067   1.0000   0.0200
  -7.750  -0.8209   0.02137   0.01565  -0.0056   1.0000   0.0212
  -7.500  -0.7971   0.02049   0.01471  -0.0053   1.0000   0.0222
  -7.250  -0.7726   0.01965   0.01378  -0.0050   1.0000   0.0235
  -7.000  -0.7475   0.01897   0.01297  -0.0046   1.0000   0.0250
  -6.750  -0.7216   0.01861   0.01248  -0.0043   1.0000   0.0263
  -6.500  -0.6991   0.01644   0.01010  -0.0036   1.0000   0.0280
  -6.250  -0.6750   0.01537   0.00900  -0.0032   1.0000   0.0296
  -6.000  -0.6497   0.01477   0.00836  -0.0028   1.0000   0.0315
  -5.750  -0.6244   0.01420   0.00772  -0.0024   1.0000   0.0334
  -5.500  -0.5991   0.01364   0.00710  -0.0020   1.0000   0.0347
  -5.250  -0.5738   0.01321   0.00660  -0.0015   1.0000   0.0355
  -5.000  -0.5518   0.01201   0.00534  -0.0006   1.0000   0.0382
  -4.750  -0.5279   0.01149   0.00480   0.0001   1.0000   0.0402
  -4.500  -0.5040   0.01107   0.00435   0.0008   1.0000   0.0420
  -4.250  -0.4800   0.01072   0.00397   0.0016   1.0000   0.0440
  -4.000  -0.4560   0.01043   0.00364   0.0023   1.0000   0.0456
  -3.750  -0.4321   0.01003   0.00322   0.0031   1.0000   0.0491
  -3.500  -0.4080   0.00973   0.00296   0.0038   1.0000   0.0548
  -3.250  -0.3838   0.00943   0.00280   0.0044   1.0000   0.0773
  -3.000  -0.3593   0.00925   0.00272   0.0050   1.0000   0.1014
  -2.750  -0.3346   0.00914   0.00261   0.0056   1.0000   0.1127
  -2.500  -0.3100   0.00900   0.00251   0.0061   1.0000   0.1223
  -2.250  -0.2852   0.00886   0.00241   0.0066   1.0000   0.1322
  -2.000  -0.2513   0.00865   0.00228   0.0051   0.9979   0.1479
  -1.750  -0.2117   0.00811   0.00207   0.0021   0.9947   0.2257
  -1.500  -0.1773   0.00670   0.00188  -0.0003   0.9910   0.5375
  -1.250  -0.1390   0.00611   0.00181  -0.0027   0.9866   0.6675
  -1.000  -0.1012   0.00577   0.00179  -0.0048   0.9813   0.7492
  -0.750  -0.0689   0.00552   0.00180  -0.0054   0.9730   0.8132
  -0.500  -0.0436   0.00542   0.00193  -0.0041   0.9627   0.8733
  -0.250  -0.0212   0.00545   0.00202  -0.0021   0.9492   0.9108
   0.000   0.0000   0.00546   0.00205   0.0000   0.9326   0.9326
   0.250   0.0212   0.00545   0.00203   0.0021   0.9109   0.9493
   0.500   0.0437   0.00542   0.00193   0.0041   0.8737   0.9627
   0.750   0.0690   0.00552   0.00180   0.0053   0.8140   0.9730
   1.000   0.1012   0.00577   0.00179   0.0048   0.7492   0.9813
   1.250   0.1390   0.00611   0.00181   0.0027   0.6676   0.9866
   1.500   0.1773   0.00670   0.00188   0.0003   0.5375   0.9910
   1.750   0.2118   0.00811   0.00207  -0.0021   0.2252   0.9947
   2.000   0.2513   0.00865   0.00228  -0.0051   0.1479   0.9979
   2.250   0.2851   0.00886   0.00241  -0.0066   0.1321   1.0000
   2.500   0.3099   0.00900   0.00251  -0.0061   0.1224   1.0000
   2.750   0.3346   0.00914   0.00261  -0.0056   0.1127   1.0000
   3.000   0.3592   0.00925   0.00272  -0.0050   0.1014   1.0000
   3.250   0.3837   0.00942   0.00280  -0.0044   0.0775   1.0000
   3.500   0.4079   0.00973   0.00296  -0.0038   0.0549   1.0000
   3.750   0.4321   0.01003   0.00322  -0.0031   0.0491   1.0000
   4.000   0.4559   0.01043   0.00364  -0.0023   0.0456   1.0000
   4.250   0.4800   0.01072   0.00397  -0.0016   0.0440   1.0000
   4.500   0.5039   0.01107   0.00435  -0.0008   0.0420   1.0000
   4.750   0.5278   0.01149   0.00480  -0.0001   0.0402   1.0000
   5.000   0.5517   0.01201   0.00534   0.0006   0.0382   1.0000
   5.250   0.5738   0.01319   0.00658   0.0015   0.0355   1.0000
   5.500   0.5991   0.01365   0.00710   0.0020   0.0347   1.0000
   5.750   0.6244   0.01420   0.00772   0.0024   0.0334   1.0000
   6.000   0.6497   0.01477   0.00835   0.0028   0.0315   1.0000
   6.250   0.6750   0.01537   0.00899   0.0031   0.0296   1.0000
   6.500   0.6991   0.01644   0.01009   0.0036   0.0280   1.0000
   6.750   0.7216   0.01860   0.01248   0.0043   0.0263   1.0000
   7.000   0.7475   0.01899   0.01299   0.0046   0.0251   1.0000
   7.250   0.7726   0.01968   0.01381   0.0050   0.0235   1.0000
   7.500   0.7971   0.02050   0.01472   0.0053   0.0223   1.0000
   7.750   0.8210   0.02138   0.01566   0.0056   0.0212   1.0000
   8.000   0.8364   0.02549   0.02013   0.0067   0.0200   1.0000
   8.250   0.8601   0.02606   0.02096   0.0073   0.0193   1.0000
   8.500   0.8808   0.02763   0.02284   0.0081   0.0182   1.0000
   8.750   0.9003   0.02931   0.02476   0.0089   0.0172   1.0000
   9.000   0.9192   0.03086   0.02648   0.0095   0.0166   1.0000
   9.250   0.9383   0.03208   0.02782   0.0101   0.0160   1.0000
   9.500   0.9551   0.03359   0.02946   0.0108   0.0155   1.0000
   9.750   0.9533   0.03876   0.03507   0.0125   0.0152   1.0000
  10.000   0.9343   0.04609   0.04298   0.0144   0.0151   1.0000
  10.250   0.9151   0.05224   0.04951   0.0154   0.0151   1.0000
  10.500   0.8925   0.05744   0.05496   0.0159   0.0152   1.0000
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