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NACA 63012A AIRFOIL (n63012a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 63012A AIRFOIL (n63012a-il)
Reynolds number: 50,000
Max Cl/Cd: 28.13 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63012a-il-50000-n5.txt
Download as CSV file: xf-n63012a-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63012A AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7313   0.09134   0.08404  -0.0199   1.0000   0.0498
 -11.250  -0.7742   0.08112   0.07366  -0.0272   1.0000   0.0483
 -11.000  -0.8097   0.07444   0.06673  -0.0303   1.0000   0.0475
 -10.750  -0.8317   0.06993   0.06199  -0.0306   1.0000   0.0473
 -10.500  -0.8475   0.06621   0.05804  -0.0294   1.0000   0.0473
 -10.250  -0.8559   0.06275   0.05435  -0.0280   1.0000   0.0475
 -10.000  -0.8574   0.05960   0.05100  -0.0268   1.0000   0.0483
  -9.750  -0.8547   0.05675   0.04796  -0.0255   1.0000   0.0494
  -9.500  -0.8512   0.05387   0.04482  -0.0241   1.0000   0.0508
  -9.250  -0.8458   0.05092   0.04153  -0.0227   1.0000   0.0522
  -9.000  -0.8373   0.04794   0.03813  -0.0212   1.0000   0.0536
  -8.750  -0.8246   0.04500   0.03477  -0.0198   1.0000   0.0547
  -8.500  -0.8078   0.04228   0.03161  -0.0186   1.0000   0.0560
  -8.250  -0.7876   0.03984   0.02878  -0.0176   1.0000   0.0578
  -8.000  -0.7664   0.03782   0.02679  -0.0171   1.0000   0.0611
  -7.750  -0.7443   0.03610   0.02491  -0.0164   1.0000   0.0655
  -7.500  -0.7183   0.03439   0.02284  -0.0156   1.0000   0.0697
  -7.250  -0.6960   0.03277   0.02135  -0.0149   1.0000   0.0749
  -7.000  -0.6742   0.03148   0.01987  -0.0138   1.0000   0.0829
  -6.750  -0.6567   0.03005   0.01851  -0.0124   1.0000   0.0908
  -6.500  -0.6409   0.02872   0.01716  -0.0108   1.0000   0.1024
  -6.250  -0.6270   0.02734   0.01585  -0.0089   1.0000   0.1179
  -6.000  -0.6153   0.02586   0.01455  -0.0068   1.0000   0.1425
  -5.750  -0.6067   0.02415   0.01326  -0.0045   1.0000   0.1893
  -5.500  -0.6029   0.02224   0.01222  -0.0015   1.0000   0.2936
  -5.250  -0.5966   0.02121   0.01206   0.0024   1.0000   0.4374
  -5.000  -0.5843   0.02099   0.01205   0.0059   1.0000   0.5237
  -4.750  -0.5703   0.02103   0.01216   0.0093   1.0000   0.5809
  -4.500  -0.5558   0.02121   0.01236   0.0128   1.0000   0.6267
  -4.250  -0.5399   0.02153   0.01268   0.0163   1.0000   0.6640
  -4.000  -0.5234   0.02178   0.01284   0.0196   1.0000   0.6943
  -3.750  -0.5076   0.02186   0.01282   0.0225   1.0000   0.7198
  -3.500  -0.4882   0.02196   0.01283   0.0248   1.0000   0.7394
  -3.250  -0.4697   0.02192   0.01268   0.0268   1.0000   0.7572
  -3.000  -0.4511   0.02183   0.01247   0.0285   1.0000   0.7733
  -2.750  -0.4327   0.02171   0.01222   0.0300   1.0000   0.7882
  -2.500  -0.4142   0.02159   0.01200   0.0314   1.0000   0.8025
  -2.250  -0.3952   0.02149   0.01180   0.0326   1.0000   0.8167
  -2.000  -0.3551   0.02152   0.01166   0.0297   0.9907   0.8299
  -1.750  -0.3143   0.02156   0.01156   0.0266   0.9810   0.8429
  -1.500  -0.2722   0.02161   0.01149   0.0233   0.9717   0.8553
  -1.250  -0.2274   0.02169   0.01147   0.0197   0.9629   0.8659
  -1.000  -0.1848   0.02173   0.01143   0.0163   0.9532   0.8770
  -0.750  -0.1400   0.02177   0.01138   0.0125   0.9445   0.8884
  -0.500  -0.0929   0.02182   0.01138   0.0082   0.9356   0.8981
  -0.250  -0.0462   0.02184   0.01138   0.0041   0.9266   0.9076
   0.000   0.0000   0.02184   0.01136   0.0000   0.9179   0.9179
   0.250   0.0462   0.02184   0.01138  -0.0041   0.9076   0.9266
   0.500   0.0929   0.02182   0.01138  -0.0083   0.8981   0.9356
   0.750   0.1400   0.02177   0.01138  -0.0125   0.8884   0.9445
   1.000   0.1848   0.02173   0.01142  -0.0163   0.8770   0.9532
   1.250   0.2274   0.02169   0.01146  -0.0197   0.8659   0.9629
   1.500   0.2722   0.02161   0.01149  -0.0234   0.8553   0.9717
   1.750   0.3143   0.02156   0.01156  -0.0266   0.8429   0.9810
   2.000   0.3552   0.02152   0.01166  -0.0297   0.8299   0.9908
   2.250   0.3952   0.02149   0.01180  -0.0326   0.8167   1.0000
   2.500   0.4142   0.02159   0.01200  -0.0314   0.8025   1.0000
   2.750   0.4327   0.02171   0.01222  -0.0300   0.7882   1.0000
   3.000   0.4512   0.02183   0.01247  -0.0285   0.7733   1.0000
   3.250   0.4697   0.02192   0.01268  -0.0268   0.7572   1.0000
   3.500   0.4882   0.02196   0.01283  -0.0248   0.7394   1.0000
   3.750   0.5076   0.02186   0.01282  -0.0225   0.7198   1.0000
   4.000   0.5235   0.02178   0.01284  -0.0196   0.6943   1.0000
   4.250   0.5399   0.02153   0.01268  -0.0164   0.6640   1.0000
   4.500   0.5559   0.02121   0.01236  -0.0128   0.6267   1.0000
   4.750   0.5703   0.02103   0.01216  -0.0093   0.5808   1.0000
   5.000   0.5844   0.02099   0.01205  -0.0059   0.5237   1.0000
   5.250   0.5966   0.02121   0.01205  -0.0024   0.4373   1.0000
   5.500   0.6029   0.02224   0.01222   0.0015   0.2935   1.0000
   5.750   0.6068   0.02414   0.01326   0.0045   0.1892   1.0000
   6.000   0.6153   0.02586   0.01455   0.0068   0.1425   1.0000
   6.250   0.6270   0.02734   0.01585   0.0089   0.1178   1.0000
   6.500   0.6409   0.02872   0.01716   0.0108   0.1024   1.0000
   6.750   0.6567   0.03004   0.01851   0.0124   0.0908   1.0000
   7.000   0.6742   0.03148   0.01986   0.0138   0.0830   1.0000
   7.250   0.6960   0.03276   0.02134   0.0149   0.0750   1.0000
   7.500   0.7183   0.03439   0.02284   0.0156   0.0697   1.0000
   7.750   0.7443   0.03610   0.02490   0.0164   0.0655   1.0000
   8.000   0.7663   0.03782   0.02679   0.0171   0.0611   1.0000
   8.250   0.7876   0.03983   0.02877   0.0176   0.0577   1.0000
   8.500   0.8078   0.04228   0.03161   0.0186   0.0560   1.0000
   8.750   0.8246   0.04500   0.03477   0.0198   0.0547   1.0000
   9.000   0.8373   0.04794   0.03812   0.0212   0.0536   1.0000
   9.250   0.8458   0.05092   0.04153   0.0226   0.0522   1.0000
   9.500   0.8512   0.05387   0.04482   0.0241   0.0508   1.0000
   9.750   0.8548   0.05675   0.04796   0.0255   0.0494   1.0000
  10.000   0.8576   0.05960   0.05100   0.0267   0.0483   1.0000
  10.250   0.8561   0.06275   0.05435   0.0280   0.0475   1.0000
  10.500   0.8478   0.06622   0.05805   0.0293   0.0472   1.0000
  10.750   0.8320   0.06995   0.06201   0.0305   0.0473   1.0000
  11.000   0.8101   0.07446   0.06674   0.0303   0.0475   1.0000
  11.250   0.7748   0.08114   0.07368   0.0271   0.0483   1.0000
  11.500   0.7319   0.09136   0.08407   0.0197   0.0498   1.0000
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