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NACA M20 AIRFOIL (m20-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M20 AIRFOIL (m20-il)
Reynolds number: 500,000
Max Cl/Cd: 105.22 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m20-il-500000-n5.txt
Download as CSV file: xf-m20-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3616   0.09897   0.09585   0.0018   0.6656   0.0092
  -7.750  -0.3567   0.09533   0.09221  -0.0004   0.6603   0.0093
  -7.500  -0.3533   0.09155   0.08843  -0.0031   0.6550   0.0095
  -7.250  -0.3471   0.08665   0.08350  -0.0075   0.6507   0.0098
  -7.000  -0.3355   0.08284   0.07966  -0.0112   0.6456   0.0101
  -6.750  -0.3201   0.08056   0.07735  -0.0134   0.6396   0.0104
  -6.500  -0.3038   0.07795   0.07468  -0.0160   0.6342   0.0109
  -6.250  -0.2869   0.07453   0.07123  -0.0194   0.6287   0.0116
  -6.000  -0.2687   0.07039   0.06702  -0.0233   0.6237   0.0121
  -5.750  -0.2468   0.06328   0.05978  -0.0299   0.6201   0.0132
  -5.500  -0.2263   0.06145   0.05789  -0.0314   0.6144   0.0135
  -5.250  -0.2045   0.05962   0.05599  -0.0330   0.6086   0.0140
  -5.000  -0.1810   0.05689   0.05317  -0.0354   0.6034   0.0150
  -4.750  -0.1554   0.05308   0.04924  -0.0383   0.5981   0.0159
  -4.500  -0.1252   0.04755   0.04350  -0.0423   0.5936   0.0175
  -4.250  -0.1027   0.04646   0.04236  -0.0429   0.5885   0.0180
  -4.000  -0.0777   0.04463   0.04043  -0.0440   0.5828   0.0189
  -3.750  -0.0506   0.04187   0.03752  -0.0455   0.5776   0.0196
  -3.500  -0.0224   0.03890   0.03438  -0.0469   0.5726   0.0204
  -3.250   0.0120   0.03425   0.02941  -0.0485   0.5679   0.0228
  -3.000   0.0368   0.03223   0.02724  -0.0490   0.5629   0.0233
  -2.750   0.0624   0.03089   0.02579  -0.0495   0.5580   0.0239
  -2.500   0.0893   0.02912   0.02388  -0.0498   0.5526   0.0243
  -2.250   0.1165   0.02756   0.02217  -0.0502   0.5473   0.0250
  -2.000   0.1444   0.02593   0.02038  -0.0504   0.5422   0.0260
  -1.750   0.1730   0.02361   0.01781  -0.0505   0.5372   0.0261
  -1.500   0.2015   0.02150   0.01544  -0.0504   0.5327   0.0264
  -1.250   0.2299   0.01956   0.01326  -0.0503   0.5283   0.0267
  -1.000   0.2583   0.01773   0.01115  -0.0502   0.5233   0.0269
  -0.750   0.2865   0.01635   0.00951  -0.0501   0.5183   0.0276
  -0.500   0.3148   0.01496   0.00785  -0.0500   0.5136   0.0275
  -0.250   0.3431   0.01393   0.00660  -0.0499   0.5086   0.0275
   0.000   0.3714   0.01319   0.00568  -0.0499   0.5040   0.0278
   0.250   0.3996   0.01263   0.00500  -0.0500   0.4997   0.0282
   0.500   0.4278   0.01221   0.00449  -0.0500   0.4946   0.0288
   0.750   0.4559   0.01191   0.00410  -0.0501   0.4896   0.0293
   1.000   0.4839   0.01165   0.00378  -0.0502   0.4853   0.0297
   1.250   0.5119   0.01143   0.00353  -0.0503   0.4808   0.0300
   1.500   0.5398   0.01125   0.00331  -0.0503   0.4763   0.0302
   1.750   0.5676   0.01112   0.00315  -0.0504   0.4720   0.0305
   2.000   0.5949   0.01077   0.00279  -0.0504   0.4675   0.0318
   2.250   0.6226   0.01063   0.00264  -0.0504   0.4631   0.0322
   2.500   0.6503   0.01056   0.00255  -0.0505   0.4591   0.0324
   2.750   0.6782   0.01049   0.00249  -0.0506   0.4553   0.0329
   3.000   0.7061   0.01045   0.00245  -0.0507   0.4509   0.0336
   3.250   0.7340   0.01046   0.00245  -0.0509   0.4466   0.0350
   3.500   0.7618   0.01049   0.00247  -0.0510   0.4428   0.0371
   3.750   0.7899   0.01050   0.00252  -0.0512   0.4383   0.0406
   4.000   0.8176   0.01051   0.00261  -0.0514   0.4328   0.0680
   4.250   0.8450   0.01051   0.00275  -0.0515   0.4267   0.1459
   4.750   0.9259   0.00922   0.00317  -0.0579   0.4141   1.0000
   5.250   0.9782   0.00946   0.00341  -0.0576   0.4039   1.0000
   5.500   1.0041   0.00962   0.00356  -0.0574   0.3941   1.0000
   5.750   1.0298   0.00981   0.00371  -0.0572   0.3840   1.0000
   6.000   1.0552   0.01003   0.00388  -0.0571   0.3678   1.0000
   6.250   1.0806   0.01027   0.00409  -0.0569   0.3522   1.0000
   6.500   1.1049   0.01065   0.00437  -0.0567   0.3248   1.0000
   6.750   1.1251   0.01165   0.00497  -0.0562   0.2540   1.0000
   7.000   1.1379   0.01362   0.00630  -0.0550   0.1458   1.0000
   7.500   1.1676   0.01645   0.00856  -0.0527   0.0197   1.0000
   7.750   1.1894   0.01693   0.00910  -0.0521   0.0176   1.0000
   8.000   1.2102   0.01750   0.00971  -0.0514   0.0155   1.0000
   8.250   1.2290   0.01822   0.01049  -0.0505   0.0133   1.0000
   8.500   1.2476   0.01891   0.01125  -0.0497   0.0123   1.0000
   8.750   1.2656   0.01961   0.01204  -0.0487   0.0115   1.0000
   9.000   1.2817   0.02041   0.01291  -0.0476   0.0108   1.0000
   9.250   1.2958   0.02131   0.01387  -0.0463   0.0101   1.0000
   9.500   1.3057   0.02232   0.01495  -0.0446   0.0096   1.0000
   9.750   1.3086   0.02384   0.01654  -0.0426   0.0090   1.0000
  10.000   1.3117   0.02574   0.01854  -0.0414   0.0086   1.0000
  10.250   1.3199   0.02740   0.02030  -0.0408   0.0082   1.0000
  10.500   1.3254   0.02941   0.02242  -0.0402   0.0080   1.0000
  10.750   1.3296   0.03165   0.02475  -0.0398   0.0077   1.0000
  11.000   1.3327   0.03402   0.02722  -0.0394   0.0074   1.0000
  11.250   1.3348   0.03652   0.02980  -0.0390   0.0072   1.0000
  11.500   1.3362   0.03912   0.03249  -0.0387   0.0070   1.0000
  11.750   1.3370   0.04179   0.03524  -0.0383   0.0068   1.0000
  12.000   1.3370   0.04456   0.03809  -0.0380   0.0066   1.0000
  12.250   1.3363   0.04743   0.04103  -0.0377   0.0065   1.0000
  12.500   1.3345   0.05041   0.04409  -0.0374   0.0063   1.0000
  12.750   1.3311   0.05360   0.04737  -0.0372   0.0062   1.0000
  13.000   1.3245   0.05714   0.05099  -0.0368   0.0060   1.0000
  13.250   1.3238   0.06015   0.05409  -0.0367   0.0059   1.0000
  13.500   1.3254   0.06296   0.05699  -0.0366   0.0057   1.0000
  13.750   1.3266   0.06581   0.05993  -0.0365   0.0055   1.0000
  14.000   1.3280   0.06865   0.06287  -0.0365   0.0054   1.0000
  14.250   1.3290   0.07157   0.06588  -0.0364   0.0052   1.0000
  14.500   1.3301   0.07445   0.06885  -0.0364   0.0051   1.0000
  14.750   1.3312   0.07735   0.07184  -0.0363   0.0049   1.0000
  15.000   1.3327   0.08022   0.07480  -0.0363   0.0048   1.0000
  15.250   1.3341   0.08316   0.07783  -0.0364   0.0047   1.0000
  15.500   1.3355   0.08613   0.08089  -0.0365   0.0046   1.0000
  15.750   1.3367   0.08918   0.08404  -0.0368   0.0045   1.0000
  16.000   1.3373   0.09235   0.08730  -0.0372   0.0044   1.0000
  16.250   1.3378   0.09558   0.09063  -0.0377   0.0043   1.0000
  16.500   1.3376   0.09897   0.09410  -0.0382   0.0043   1.0000
  16.750   1.3371   0.10241   0.09764  -0.0389   0.0042   1.0000
  17.000   1.3354   0.10606   0.10138  -0.0396   0.0041   1.0000
  17.250   1.3327   0.10981   0.10525  -0.0403   0.0040   1.0000
  17.500   1.3273   0.11398   0.10956  -0.0411   0.0040   1.0000
  17.750   1.3224   0.11834   0.11407  -0.0422   0.0039   1.0000
  18.000   1.3164   0.12306   0.11896  -0.0436   0.0039   1.0000
  18.250   1.3089   0.12813   0.12421  -0.0454   0.0039   1.0000
  18.500   1.3000   0.13361   0.12988  -0.0475   0.0038   1.0000
  18.750   1.2893   0.13966   0.13611  -0.0501   0.0038   1.0000
  19.000   1.2775   0.14619   0.14283  -0.0531   0.0038   1.0000
  19.250   1.2645   0.15325   0.15009  -0.0568   0.0037   1.0000
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