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NACA M20 AIRFOIL (m20-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA M20 AIRFOIL (m20-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.27 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m20-il-1000000-n5.txt
Download as CSV file: xf-m20-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M20 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3799   0.09528   0.09260   0.0016   0.6219   0.0062
  -7.750  -0.3763   0.09170   0.08902  -0.0010   0.6175   0.0065
  -7.500  -0.3717   0.08679   0.08411  -0.0054   0.6133   0.0070
  -7.250  -0.3637   0.08103   0.07831  -0.0108   0.6092   0.0075
  -7.000  -0.3479   0.07822   0.07547  -0.0137   0.6046   0.0076
  -6.750  -0.3310   0.07531   0.07252  -0.0166   0.5995   0.0079
  -6.500  -0.3132   0.07222   0.06938  -0.0197   0.5940   0.0082
  -6.250  -0.2943   0.06871   0.06581  -0.0231   0.5893   0.0088
  -6.000  -0.2748   0.06188   0.05889  -0.0290   0.5854   0.0101
  -5.750  -0.2526   0.05960   0.05654  -0.0311   0.5800   0.0103
  -5.500  -0.2296   0.05722   0.05409  -0.0332   0.5753   0.0106
  -5.250  -0.2059   0.05454   0.05134  -0.0355   0.5704   0.0111
  -5.000  -0.1790   0.04738   0.04399  -0.0402   0.5663   0.0132
  -4.750  -0.1542   0.04570   0.04222  -0.0414   0.5608   0.0135
  -4.500  -0.1289   0.04399   0.04044  -0.0426   0.5555   0.0138
  -4.250  -0.1032   0.04215   0.03851  -0.0437   0.5502   0.0142
  -4.000  -0.0767   0.03989   0.03614  -0.0449   0.5457   0.0151
  -3.750  -0.0458   0.03272   0.02863  -0.0470   0.5423   0.0174
  -3.500  -0.0196   0.03159   0.02740  -0.0475   0.5367   0.0177
  -3.250   0.0067   0.03057   0.02630  -0.0480   0.5313   0.0180
  -3.000   0.0336   0.02906   0.02469  -0.0484   0.5263   0.0183
  -2.750   0.0609   0.02722   0.02270  -0.0488   0.5214   0.0188
  -2.500   0.0887   0.02499   0.02028  -0.0490   0.5169   0.0193
  -2.250   0.1170   0.02233   0.01740  -0.0490   0.5129   0.0203
  -2.000   0.1452   0.01823   0.01291  -0.0486   0.5085   0.0215
  -1.750   0.1725   0.01557   0.00989  -0.0483   0.5037   0.0220
  -1.500   0.2002   0.01430   0.00839  -0.0483   0.4991   0.0221
  -1.250   0.2282   0.01345   0.00735  -0.0483   0.4942   0.0222
  -1.000   0.2564   0.01313   0.00692  -0.0484   0.4895   0.0224
  -0.750   0.2846   0.01251   0.00616  -0.0485   0.4853   0.0224
  -0.500   0.3127   0.01175   0.00525  -0.0486   0.4805   0.0225
  -0.250   0.3402   0.01049   0.00377  -0.0486   0.4755   0.0231
   0.000   0.3682   0.01008   0.00330  -0.0486   0.4712   0.0238
   0.250   0.3965   0.00985   0.00304  -0.0488   0.4671   0.0242
   0.500   0.4247   0.00968   0.00285  -0.0489   0.4625   0.0248
   1.000   0.4810   0.00940   0.00250  -0.0492   0.4539   0.0257
   1.250   0.5092   0.00926   0.00235  -0.0493   0.4495   0.0261
   1.500   0.5372   0.00916   0.00222  -0.0494   0.4454   0.0264
   1.750   0.5654   0.00906   0.00210  -0.0495   0.4417   0.0267
   2.000   0.5935   0.00897   0.00200  -0.0497   0.4378   0.0269
   2.250   0.6217   0.00892   0.00194  -0.0499   0.4332   0.0274
   2.500   0.6498   0.00890   0.00191  -0.0500   0.4283   0.0279
   2.750   0.6781   0.00885   0.00186  -0.0502   0.4240   0.0282
   3.000   0.7062   0.00885   0.00183  -0.0504   0.4179   0.0284
   3.250   0.7343   0.00887   0.00183  -0.0506   0.4112   0.0287
   3.500   0.7625   0.00889   0.00185  -0.0508   0.4042   0.0293
   3.750   0.7906   0.00894   0.00188  -0.0510   0.3997   0.0300
   4.000   0.8189   0.00896   0.00193  -0.0513   0.3965   0.0318
   4.250   0.8471   0.00899   0.00198  -0.0515   0.3925   0.0381
   4.500   0.8751   0.00901   0.00209  -0.0517   0.3879   0.0822
   4.750   0.9029   0.00904   0.00222  -0.0520   0.3833   0.1319
   5.000   0.9217   0.00757   0.00249  -0.0505   0.3742   0.9747
   5.250   0.9815   0.00786   0.00271  -0.0581   0.3564   1.0000
   5.500   1.0072   0.00804   0.00285  -0.0580   0.3431   1.0000
   5.750   1.0323   0.00837   0.00305  -0.0578   0.3175   1.0000
   6.000   1.0563   0.00889   0.00337  -0.0576   0.2793   1.0000
   6.250   1.0757   0.01019   0.00416  -0.0570   0.1885   1.0000
   6.500   1.0932   0.01166   0.00514  -0.0563   0.0958   1.0000
   6.750   1.1112   0.01287   0.00604  -0.0553   0.0268   1.0000
   7.000   1.1345   0.01327   0.00642  -0.0549   0.0186   1.0000
   7.250   1.1578   0.01363   0.00678  -0.0545   0.0156   1.0000
   7.500   1.1809   0.01404   0.00720  -0.0540   0.0127   1.0000
   7.750   1.2043   0.01438   0.00756  -0.0536   0.0118   1.0000
   8.000   1.2272   0.01477   0.00798  -0.0532   0.0108   1.0000
   8.250   1.2494   0.01523   0.00844  -0.0527   0.0097   1.0000
   8.500   1.2706   0.01578   0.00904  -0.0521   0.0086   1.0000
   8.750   1.2926   0.01621   0.00949  -0.0516   0.0081   1.0000
   9.000   1.3138   0.01670   0.01001  -0.0511   0.0075   1.0000
   9.250   1.3341   0.01724   0.01058  -0.0504   0.0070   1.0000
   9.500   1.3533   0.01785   0.01121  -0.0497   0.0066   1.0000
   9.750   1.3696   0.01865   0.01207  -0.0486   0.0061   1.0000
  10.000   1.3854   0.01941   0.01290  -0.0475   0.0058   1.0000
  10.250   1.3995   0.02020   0.01375  -0.0462   0.0056   1.0000
  10.500   1.4080   0.02118   0.01479  -0.0443   0.0054   1.0000
  10.750   1.4166   0.02240   0.01608  -0.0431   0.0052   1.0000
  11.000   1.4264   0.02376   0.01750  -0.0423   0.0050   1.0000
  11.250   1.4362   0.02524   0.01904  -0.0418   0.0047   1.0000
  11.500   1.4456   0.02684   0.02071  -0.0414   0.0045   1.0000
  11.750   1.4531   0.02869   0.02261  -0.0411   0.0044   1.0000
  12.000   1.4577   0.03087   0.02487  -0.0407   0.0042   1.0000
  12.250   1.4583   0.03351   0.02760  -0.0403   0.0040   1.0000
  12.500   1.4571   0.03636   0.03054  -0.0399   0.0039   1.0000
  12.750   1.4597   0.03882   0.03308  -0.0396   0.0039   1.0000
  13.000   1.4604   0.04147   0.03582  -0.0393   0.0038   1.0000
  13.250   1.4600   0.04428   0.03872  -0.0391   0.0038   1.0000
  13.500   1.4586   0.04722   0.04175  -0.0388   0.0037   1.0000
  13.750   1.4563   0.05027   0.04489  -0.0386   0.0036   1.0000
  14.000   1.4537   0.05342   0.04813  -0.0385   0.0036   1.0000
  14.250   1.4516   0.05663   0.05143  -0.0385   0.0035   1.0000
  14.500   1.4492   0.05994   0.05483  -0.0386   0.0034   1.0000
  14.750   1.4468   0.06332   0.05830  -0.0388   0.0034   1.0000
  15.000   1.4448   0.06668   0.06174  -0.0390   0.0033   1.0000
  15.250   1.4423   0.07013   0.06527  -0.0393   0.0032   1.0000
  15.500   1.4397   0.07366   0.06888  -0.0396   0.0032   1.0000
  15.750   1.4376   0.07718   0.07248  -0.0400   0.0031   1.0000
  16.000   1.4356   0.08065   0.07603  -0.0405   0.0031   1.0000
  16.250   1.4334   0.08421   0.07967  -0.0410   0.0030   1.0000
  16.500   1.4310   0.08786   0.08340  -0.0415   0.0030   1.0000
  16.750   1.4290   0.09146   0.08707  -0.0422   0.0029   1.0000
  17.000   1.4267   0.09514   0.09083  -0.0429   0.0029   1.0000
  17.250   1.4244   0.09883   0.09460  -0.0436   0.0028   1.0000
  17.500   1.4219   0.10260   0.09845  -0.0444   0.0028   1.0000
  17.750   1.4187   0.10653   0.10246  -0.0454   0.0027   1.0000
  18.000   1.4155   0.11045   0.10646  -0.0463   0.0027   1.0000
  18.250   1.4107   0.11466   0.11075  -0.0475   0.0026   1.0000
  18.500   1.4055   0.11890   0.11509  -0.0486   0.0026   1.0000
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