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NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(1)-212 MOD A (n64212ma-il)
Reynolds number: 50,000
Max Cl/Cd: 29.91 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64212ma-il-50000.txt
Download as CSV file: xf-n64212ma-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212 MOD A                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3344   0.10021   0.09332  -0.0145   1.0000   0.3162
  -8.250  -0.3280   0.09785   0.09104  -0.0131   1.0000   0.3404
  -8.000  -0.3343   0.09668   0.08999  -0.0117   1.0000   0.3661
  -7.750  -0.3022   0.09285   0.08618  -0.0092   1.0000   0.4006
  -7.500  -0.2846   0.09053   0.08392  -0.0067   1.0000   0.4402
  -7.250  -0.2659   0.08825   0.08170  -0.0041   1.0000   0.4828
  -7.000  -0.2455   0.08566   0.07918  -0.0020   1.0000   0.5242
  -6.750  -0.2282   0.08311   0.07670  -0.0002   1.0000   0.5623
  -6.500  -0.2397   0.08398   0.07771   0.0043   1.0000   0.5986
  -6.250  -0.2022   0.07953   0.07328   0.0042   1.0000   0.6421
  -6.000  -0.1658   0.07478   0.06856   0.0032   1.0000   0.6801
  -5.750  -0.1631   0.07368   0.06758   0.0060   1.0000   0.7155
  -5.500  -0.1600   0.07240   0.06642   0.0082   1.0000   0.7372
  -5.250  -0.1562   0.06974   0.06387   0.0089   1.0000   0.7386
  -4.250  -0.2517   0.06668   0.06138   0.0247   1.0000   0.6754
  -4.000  -0.3513   0.06731   0.06226   0.0328   1.0000   0.6047
  -3.750  -0.4199   0.06593   0.06105   0.0378   1.0000   0.5642
  -3.500  -0.4344   0.04374   0.03682  -0.0153   1.0000   0.2880
  -3.250  -0.3954   0.04185   0.03399  -0.0184   1.0000   0.2320
  -3.000  -0.3665   0.04001   0.03159  -0.0190   1.0000   0.2043
  -2.750  -0.3403   0.03885   0.02993  -0.0189   1.0000   0.1893
  -2.500  -0.3157   0.03747   0.02815  -0.0187   1.0000   0.1796
  -2.250  -0.2917   0.03684   0.02712  -0.0181   1.0000   0.1731
  -2.000  -0.2694   0.03540   0.02557  -0.0176   1.0000   0.1682
  -1.750  -0.2462   0.03445   0.02436  -0.0170   1.0000   0.1627
  -1.500  -0.2230   0.03411   0.02364  -0.0162   1.0000   0.1582
  -1.250  -0.2013   0.03363   0.02299  -0.0154   1.0000   0.1566
  -1.000  -0.1801   0.03302   0.02230  -0.0146   1.0000   0.1572
  -0.750  -0.1597   0.03226   0.02159  -0.0137   1.0000   0.1588
  -0.500  -0.1397   0.03178   0.02117  -0.0126   1.0000   0.1608
  -0.250  -0.1201   0.03151   0.02091  -0.0113   1.0000   0.1622
   0.000  -0.1003   0.03135   0.02075  -0.0102   1.0000   0.1643
   0.250  -0.0802   0.03128   0.02067  -0.0094   1.0000   0.1680
   0.500  -0.0192   0.03192   0.02134  -0.0159   0.9818   0.1819
   0.750   0.0367   0.03223   0.02171  -0.0216   0.9628   0.2035
   1.000   0.0778   0.03062   0.02258  -0.0231   0.9423   0.7182
   1.250   0.1423   0.03098   0.02316  -0.0245   0.9110   1.0000
   1.500   0.2287   0.03155   0.02327  -0.0326   0.8756   1.0000
   1.750   0.2731   0.03165   0.02320  -0.0347   0.8513   1.0000
   2.000   0.3248   0.03167   0.02310  -0.0377   0.8298   1.0000
   2.250   0.3815   0.03134   0.02272  -0.0408   0.8082   1.0000
   2.500   0.4373   0.03058   0.02195  -0.0431   0.7850   1.0000
   2.750   0.4809   0.02964   0.02102  -0.0431   0.7604   1.0000
   3.000   0.5220   0.02835   0.01975  -0.0421   0.7326   1.0000
   3.250   0.5662   0.02667   0.01811  -0.0409   0.7038   1.0000
   3.500   0.6038   0.02488   0.01634  -0.0384   0.6678   1.0000
   3.750   0.6363   0.02286   0.01422  -0.0346   0.6105   1.0000
   4.000   0.6545   0.02188   0.01271  -0.0296   0.5021   1.0000
   4.250   0.6707   0.02251   0.01237  -0.0264   0.4138   1.0000
   4.500   0.6916   0.02373   0.01291  -0.0250   0.3733   1.0000
   4.750   0.7196   0.02496   0.01376  -0.0249   0.3492   1.0000
   5.000   0.7487   0.02608   0.01475  -0.0250   0.3337   1.0000
   5.250   0.7796   0.02723   0.01572  -0.0254   0.3235   1.0000
   5.500   0.8081   0.02834   0.01685  -0.0256   0.3157   1.0000
   5.750   0.8385   0.02954   0.01794  -0.0260   0.3097   1.0000
   6.000   0.8665   0.03086   0.01929  -0.0263   0.3053   1.0000
   6.250   0.8914   0.03218   0.02079  -0.0261   0.3015   1.0000
   6.500   0.9162   0.03359   0.02235  -0.0260   0.2980   1.0000
   6.750   0.9407   0.03507   0.02396  -0.0259   0.2947   1.0000
   7.000   0.9653   0.03664   0.02560  -0.0259   0.2917   1.0000
   7.250   0.9904   0.03840   0.02740  -0.0259   0.2889   1.0000
   7.500   1.0092   0.04036   0.02959  -0.0254   0.2868   1.0000
   7.750   1.0236   0.04246   0.03206  -0.0246   0.2847   1.0000
   8.000   1.0355   0.04479   0.03472  -0.0236   0.2825   1.0000
   8.250   1.0447   0.04734   0.03758  -0.0226   0.2801   1.0000
   8.500   1.0523   0.05001   0.04051  -0.0216   0.2772   1.0000
   8.750   1.0656   0.05236   0.04300  -0.0209   0.2732   1.0000
   9.000   1.0894   0.05445   0.04506  -0.0207   0.2670   1.0000
   9.250   1.0741   0.05844   0.04946  -0.0187   0.2649   1.0000
   9.500   1.0481   0.06342   0.05475  -0.0169   0.2639   1.0000
   9.750   1.0102   0.06961   0.06110  -0.0156   0.2652   1.0000
  10.000   0.9722   0.07678   0.06834  -0.0158   0.2671   1.0000
  10.250   1.0235   0.07419   0.06577  -0.0134   0.2473   1.0000
  10.500   0.9839   0.08192   0.07358  -0.0144   0.2484   1.0000
  10.750   0.6861   0.13480   0.12624  -0.0562   0.4441   1.0000
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