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NACA M20 AIRFOIL (m20-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA M20 AIRFOIL (m20-il)
Reynolds number: 500,000
Max Cl/Cd: 108.66 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m20-il-500000.txt
Download as CSV file: xf-m20-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3595   0.10245   0.09965   0.0043   0.7335   0.0177
  -7.750  -0.3524   0.09933   0.09651   0.0015   0.7262   0.0184
  -7.500  -0.3474   0.09642   0.09357  -0.0025   0.7193   0.0186
  -7.250  -0.3381   0.09314   0.09027  -0.0080   0.7128   0.0187
  -7.000  -0.2534   0.07507   0.07223  -0.0153   0.6887   0.0190
  -6.750  -0.2464   0.07157   0.06872  -0.0156   0.6829   0.0193
  -6.500  -0.2384   0.06816   0.06529  -0.0170   0.6770   0.0196
  -6.250  -0.2291   0.06484   0.06191  -0.0188   0.6719   0.0202
  -6.000  -0.2180   0.06127   0.05833  -0.0211   0.6663   0.0209
  -5.750  -0.2052   0.05751   0.05451  -0.0238   0.6610   0.0219
  -5.500  -0.1823   0.05374   0.05062  -0.0298   0.6565   0.0234
  -5.250  -0.1594   0.04966   0.04643  -0.0344   0.6512   0.0236
  -5.000  -0.1390   0.04572   0.04238  -0.0368   0.6459   0.0236
  -4.750  -0.1281   0.03997   0.03655  -0.0380   0.6416   0.0241
  -4.500  -0.1138   0.03695   0.03353  -0.0379   0.6357   0.0245
  -4.250  -0.0955   0.03421   0.03071  -0.0387   0.6302   0.0251
  -4.000  -0.0923   0.04828   0.04445  -0.0404   0.6363   0.0254
  -3.750  -0.0670   0.04581   0.04186  -0.0418   0.6306   0.0265
  -3.500  -0.0386   0.04331   0.03919  -0.0434   0.6252   0.0284
  -3.250   0.0028   0.04158   0.03721  -0.0453   0.6192   0.0301
  -3.000   0.0312   0.03898   0.03440  -0.0460   0.6139   0.0302
  -2.750   0.0491   0.03432   0.02963  -0.0468   0.6089   0.0313
  -2.500   0.0733   0.03262   0.02786  -0.0472   0.6030   0.0321
  -2.250   0.0991   0.03102   0.02611  -0.0475   0.5978   0.0331
  -2.000   0.1267   0.02931   0.02428  -0.0479   0.5920   0.0347
  -1.750   0.1619   0.02854   0.02324  -0.0478   0.5862   0.0388
  -1.500   0.1891   0.02487   0.01920  -0.0478   0.5817   0.0398
  -1.250   0.2140   0.02316   0.01745  -0.0481   0.5759   0.0410
  -1.000   0.2403   0.02216   0.01635  -0.0483   0.5705   0.0424
  -0.750   0.2679   0.02113   0.01518  -0.0484   0.5653   0.0447
  -0.500   0.2997   0.02112   0.01495  -0.0480   0.5594   0.0500
  -0.250   0.3258   0.01839   0.01195  -0.0482   0.5545   0.0526
   0.000   0.3530   0.01770   0.01123  -0.0484   0.5492   0.0548
   0.250   0.3812   0.01703   0.01046  -0.0485   0.5438   0.0585
   0.500   0.4117   0.01783   0.01099  -0.0481   0.5388   0.0634
   0.750   0.4378   0.01541   0.00853  -0.0485   0.5337   0.0683
   1.000   0.4678   0.01381   0.00663  -0.0480   0.5287   0.0565
   1.250   0.4952   0.01383   0.00661  -0.0483   0.5238   0.0695
   1.500   0.5252   0.01175   0.00417  -0.0474   0.5195   0.0438
   1.750   0.5531   0.01137   0.00376  -0.0473   0.5144   0.0438
   2.000   0.5805   0.01108   0.00339  -0.0472   0.5098   0.0435
   2.250   0.6081   0.01085   0.00316  -0.0472   0.5049   0.0439
   2.500   0.6359   0.01068   0.00301  -0.0472   0.5001   0.0453
   2.750   0.6635   0.01061   0.00290  -0.0472   0.4958   0.0473
   3.000   0.6914   0.01057   0.00285  -0.0473   0.4914   0.0494
   3.250   0.7194   0.01050   0.00280  -0.0474   0.4866   0.0537
   3.500   0.7472   0.01047   0.00284  -0.0475   0.4822   0.0771
   3.750   0.8100   0.00885   0.00315  -0.0557   0.4766   1.0000
   4.000   0.8364   0.00893   0.00321  -0.0555   0.4715   1.0000
   4.250   0.8624   0.00905   0.00328  -0.0553   0.4666   1.0000
   4.500   0.8886   0.00917   0.00338  -0.0551   0.4621   1.0000
   4.750   0.9149   0.00926   0.00349  -0.0549   0.4574   1.0000
   5.000   0.9410   0.00939   0.00359  -0.0547   0.4528   1.0000
   5.250   0.9670   0.00949   0.00370  -0.0545   0.4454   1.0000
   5.750   1.0189   0.00967   0.00386  -0.0541   0.4263   1.0000
   6.000   1.0448   0.00980   0.00399  -0.0540   0.4172   1.0000
   6.250   1.0705   0.00994   0.00411  -0.0538   0.4030   1.0000
   6.500   1.0960   0.01011   0.00427  -0.0536   0.3893   1.0000
   6.750   1.1214   0.01032   0.00445  -0.0534   0.3695   1.0000
   7.000   1.1442   0.01088   0.00479  -0.0530   0.3201   1.0000
   7.250   1.1458   0.01443   0.00699  -0.0511   0.0956   1.0000
   7.500   1.1583   0.01615   0.00838  -0.0496   0.0292   1.0000
   7.750   1.1781   0.01690   0.00922  -0.0487   0.0248   1.0000
   8.000   1.1983   0.01754   0.00994  -0.0479   0.0231   1.0000
   8.250   1.2168   0.01831   0.01077  -0.0469   0.0213   1.0000
   8.500   1.2321   0.01931   0.01187  -0.0457   0.0198   1.0000
   8.750   1.2403   0.02083   0.01351  -0.0437   0.0186   1.0000
   9.000   1.2473   0.02223   0.01503  -0.0416   0.0181   1.0000
   9.250   1.2527   0.02349   0.01637  -0.0395   0.0177   1.0000
   9.500   1.2565   0.02518   0.01816  -0.0380   0.0173   1.0000
   9.750   1.2608   0.02714   0.02022  -0.0371   0.0168   1.0000
  10.000   1.2652   0.02925   0.02242  -0.0364   0.0162   1.0000
  10.250   1.2696   0.03143   0.02467  -0.0359   0.0156   1.0000
  10.500   1.2729   0.03373   0.02704  -0.0354   0.0151   1.0000
  10.750   1.2743   0.03623   0.02960  -0.0347   0.0147   1.0000
  11.000   1.2747   0.03880   0.03222  -0.0340   0.0144   1.0000
  11.250   1.2740   0.04141   0.03488  -0.0331   0.0141   1.0000
  11.500   1.2730   0.04389   0.03739  -0.0317   0.0138   1.0000
  11.750   1.2751   0.04578   0.03928  -0.0292   0.0135   1.0000
  12.000   1.2861   0.04687   0.04039  -0.0264   0.0132   1.0000
  12.250   1.2952   0.04855   0.04219  -0.0256   0.0131   1.0000
  12.500   1.3067   0.05000   0.04371  -0.0243   0.0129   1.0000
  12.750   1.3173   0.05159   0.04541  -0.0231   0.0127   1.0000
  13.000   1.3264   0.05338   0.04730  -0.0222   0.0123   1.0000
  13.250   1.3355   0.05521   0.04925  -0.0212   0.0119   1.0000
  13.500   1.3475   0.05694   0.05110  -0.0197   0.0118   1.0000
  13.750   1.3602   0.05890   0.05322  -0.0180   0.0118   1.0000
  14.000   1.3705   0.06146   0.05596  -0.0163   0.0120   1.0000
  14.250   1.3783   0.06484   0.05954  -0.0147   0.0125   1.0000
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