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NACA M21 AIRFOIL (m21-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA M21 AIRFOIL (m21-il)
Reynolds number: 500,000
Max Cl/Cd: 107.26 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m21-il-500000.txt
Download as CSV file: xf-m21-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M21 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1989   0.09551   0.09242  -0.0247   0.6925   0.0305
  -9.000  -0.1929   0.09261   0.08953  -0.0253   0.6867   0.0310
  -8.750  -0.2939   0.09822   0.09510  -0.0184   0.7024   0.0303
  -8.500  -0.2855   0.09561   0.09245  -0.0193   0.6958   0.0307
  -8.250  -0.2782   0.09289   0.08970  -0.0206   0.6898   0.0312
  -8.000  -0.2718   0.08994   0.08675  -0.0225   0.6835   0.0319
  -7.750  -0.2670   0.08674   0.08351  -0.0250   0.6778   0.0328
  -7.500  -0.2695   0.08189   0.07860  -0.0354   0.6735   0.0346
  -7.250  -0.2586   0.07717   0.07380  -0.0410   0.6684   0.0347
  -7.000  -0.2513   0.07333   0.06994  -0.0403   0.6631   0.0351
  -6.750  -0.2381   0.07091   0.06747  -0.0400   0.6579   0.0354
  -6.500  -0.2235   0.06850   0.06505  -0.0406   0.6522   0.0358
  -6.250  -0.2079   0.06598   0.06246  -0.0419   0.6468   0.0365
  -6.000  -0.1912   0.06324   0.05962  -0.0436   0.6420   0.0373
  -5.750  -0.1616   0.05846   0.05458  -0.0502   0.6377   0.0404
  -5.500  -0.1470   0.05366   0.04966  -0.0514   0.6332   0.0408
  -5.250  -0.1313   0.05134   0.04729  -0.0513   0.6283   0.0412
  -5.000  -0.1126   0.04949   0.04539  -0.0513   0.6234   0.0416
  -4.750  -0.0921   0.04756   0.04341  -0.0516   0.6182   0.0423
  -4.500  -0.0704   0.04547   0.04122  -0.0521   0.6135   0.0433
  -4.250  -0.0469   0.04316   0.03874  -0.0527   0.6091   0.0451
  -4.000  -0.0184   0.03785   0.03299  -0.0536   0.6054   0.0476
  -3.750   0.0022   0.03603   0.03114  -0.0535   0.6004   0.0481
  -3.500   0.0245   0.03474   0.02978  -0.0535   0.5958   0.0487
  -3.250   0.0480   0.03345   0.02840  -0.0535   0.5914   0.0497
  -3.000   0.0730   0.03182   0.02668  -0.0534   0.5867   0.0512
  -2.750   0.1057   0.02997   0.02432  -0.0526   0.5824   0.0550
  -2.500   0.1215   0.02282   0.01669  -0.0509   0.5792   0.0464
  -2.250   0.1455   0.01981   0.01327  -0.0500   0.5754   0.0462
  -2.000   0.1708   0.01670   0.00967  -0.0491   0.5713   0.0466
  -1.750   0.1980   0.01508   0.00772  -0.0489   0.5668   0.0477
  -1.500   0.2257   0.01455   0.00710  -0.0489   0.5624   0.0489
  -1.250   0.2540   0.01445   0.00698  -0.0490   0.5580   0.0503
  -1.000   0.2825   0.01417   0.00666  -0.0491   0.5534   0.0521
  -0.750   0.3109   0.01369   0.00604  -0.0491   0.5489   0.0540
  -0.500   0.3388   0.01314   0.00534  -0.0491   0.5447   0.0560
  -0.250   0.3672   0.01293   0.00518  -0.0492   0.5404   0.0580
   0.000   0.3956   0.01281   0.00505  -0.0493   0.5359   0.0605
   0.250   0.4239   0.01275   0.00492  -0.0494   0.5316   0.0635
   0.500   0.4515   0.01242   0.00454  -0.0494   0.5273   0.0667
   0.750   0.4798   0.01230   0.00448  -0.0495   0.5230   0.0697
   1.000   0.5080   0.01222   0.00438  -0.0496   0.5187   0.0731
   1.250   0.5357   0.01211   0.00421  -0.0496   0.5145   0.0764
   1.500   0.5630   0.01193   0.00405  -0.0496   0.5103   0.0802
   1.750   0.5909   0.01184   0.00400  -0.0497   0.5058   0.0839
   2.000   0.6190   0.01182   0.00397  -0.0498   0.5016   0.0873
   2.250   0.6455   0.01164   0.00375  -0.0496   0.4976   0.0910
   2.500   0.6729   0.01157   0.00373  -0.0496   0.4934   0.0953
   2.750   0.7006   0.01151   0.00370  -0.0497   0.4889   0.0991
   3.000   0.7281   0.01150   0.00367  -0.0497   0.4845   0.1021
   3.250   0.7547   0.01146   0.00362  -0.0496   0.4805   0.1082
   3.500   0.7824   0.01143   0.00364  -0.0497   0.4764   0.1134
   3.750   0.8099   0.01140   0.00365  -0.0497   0.4719   0.1201
   4.000   0.8371   0.01142   0.00368  -0.0498   0.4676   0.1312
   4.250   0.8541   0.01039   0.00380  -0.0482   0.4637   0.6872
   4.500   0.9864   0.01026   0.00442  -0.0707   0.4562   1.0000
   4.750   1.0116   0.01038   0.00450  -0.0704   0.4519   1.0000
   5.000   1.0367   0.01053   0.00461  -0.0701   0.4476   1.0000
   5.250   1.0620   0.01062   0.00473  -0.0697   0.4432   1.0000
   5.500   1.0870   0.01073   0.00485  -0.0694   0.4389   1.0000
   5.750   1.1116   0.01091   0.00498  -0.0690   0.4348   1.0000
   6.000   1.1363   0.01106   0.00514  -0.0686   0.4306   1.0000
   6.250   1.1610   0.01117   0.00530  -0.0682   0.4260   1.0000
   6.500   1.1853   0.01133   0.00545  -0.0678   0.4216   1.0000
   6.750   1.2091   0.01157   0.00565  -0.0673   0.4173   1.0000
   7.000   1.2333   0.01167   0.00583  -0.0668   0.4120   1.0000
   7.250   1.2568   0.01182   0.00598  -0.0663   0.4057   1.0000
   7.500   1.2798   0.01202   0.00618  -0.0656   0.3995   1.0000
   7.750   1.3032   0.01216   0.00638  -0.0651   0.3932   1.0000
   8.000   1.3253   0.01242   0.00659  -0.0643   0.3871   1.0000
   8.250   1.3482   0.01257   0.00682  -0.0637   0.3804   1.0000
   8.500   1.3698   0.01281   0.00705  -0.0628   0.3734   1.0000
   8.750   1.3916   0.01302   0.00732  -0.0621   0.3664   1.0000
   9.000   1.4119   0.01330   0.00759  -0.0610   0.3577   1.0000
   9.250   1.4327   0.01354   0.00788  -0.0601   0.3492   1.0000
   9.500   1.4511   0.01390   0.00822  -0.0588   0.3398   1.0000
   9.750   1.4694   0.01424   0.00858  -0.0575   0.3278   1.0000
  10.000   1.4852   0.01468   0.00900  -0.0558   0.3133   1.0000
  10.250   1.4962   0.01531   0.00956  -0.0534   0.2924   1.0000
  10.500   1.4978   0.01630   0.01040  -0.0497   0.2607   1.0000
  10.750   1.4826   0.01775   0.01164  -0.0434   0.2258   1.0000
  11.000   1.4606   0.02025   0.01388  -0.0380   0.1832   1.0000
  11.250   1.4370   0.02376   0.01714  -0.0342   0.1401   1.0000
  11.500   1.4089   0.02825   0.02138  -0.0313   0.0953   1.0000
  11.750   1.3824   0.03300   0.02596  -0.0293   0.0594   1.0000
  12.000   1.3625   0.03737   0.03023  -0.0278   0.0374   1.0000
  12.250   1.3546   0.04070   0.03358  -0.0269   0.0304   1.0000
  12.500   1.3493   0.04382   0.03675  -0.0262   0.0273   1.0000
  12.750   1.3481   0.04659   0.03961  -0.0257   0.0257   1.0000
  13.000   1.3451   0.04964   0.04273  -0.0252   0.0244   1.0000
  13.250   1.3399   0.05303   0.04619  -0.0249   0.0233   1.0000
  13.500   1.3348   0.05652   0.04976  -0.0247   0.0224   1.0000
  13.750   1.3336   0.05959   0.05292  -0.0246   0.0217   1.0000
  14.000   1.3310   0.06289   0.05631  -0.0246   0.0211   1.0000
  14.250   1.3273   0.06638   0.05989  -0.0246   0.0205   1.0000
  14.500   1.3228   0.07003   0.06361  -0.0248   0.0200   1.0000
  14.750   1.3169   0.07389   0.06756  -0.0250   0.0195   1.0000
  15.000   1.3097   0.07799   0.07173  -0.0253   0.0191   1.0000
  15.250   1.3000   0.08248   0.07631  -0.0257   0.0187   1.0000
  15.500   1.2910   0.08691   0.08082  -0.0261   0.0184   1.0000
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