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NACA 63012A AIRFOIL (n63012a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 63012A AIRFOIL (n63012a-il)
Reynolds number: 500,000
Max Cl/Cd: 58.08 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63012a-il-500000.txt
Download as CSV file: xf-n63012a-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.9092   0.07303   0.07015  -0.0230   1.0000   0.0165
 -13.000  -0.9268   0.06723   0.06418  -0.0266   1.0000   0.0164
 -12.750  -0.9420   0.06241   0.05919  -0.0290   1.0000   0.0164
 -12.500  -0.9564   0.05815   0.05476  -0.0304   1.0000   0.0163
 -12.250  -0.9708   0.05427   0.05070  -0.0309   1.0000   0.0163
 -11.750  -1.0007   0.04656   0.04258  -0.0288   1.0000   0.0162
 -11.500  -1.0121   0.04425   0.04004  -0.0262   1.0000   0.0163
 -11.250  -1.0268   0.04021   0.03568  -0.0230   1.0000   0.0164
 -11.000  -1.0327   0.03593   0.03106  -0.0205   1.0000   0.0166
 -10.750  -1.0257   0.03330   0.02825  -0.0189   1.0000   0.0170
 -10.500  -1.0135   0.03154   0.02636  -0.0176   1.0000   0.0173
 -10.250  -0.9998   0.02976   0.02440  -0.0162   1.0000   0.0175
 -10.000  -0.9841   0.02813   0.02262  -0.0150   1.0000   0.0178
  -9.750  -0.9668   0.02662   0.02097  -0.0139   1.0000   0.0182
  -9.500  -0.9484   0.02520   0.01938  -0.0129   1.0000   0.0185
  -9.250  -0.9292   0.02384   0.01790  -0.0119   1.0000   0.0189
  -9.000  -0.9093   0.02261   0.01654  -0.0109   1.0000   0.0194
  -8.750  -0.8887   0.02165   0.01546  -0.0099   1.0000   0.0200
  -8.500  -0.8675   0.02088   0.01459  -0.0090   1.0000   0.0206
  -8.250  -0.8462   0.02018   0.01378  -0.0081   1.0000   0.0210
  -8.000  -0.8304   0.01826   0.01178  -0.0064   1.0000   0.0217
  -7.750  -0.8128   0.01727   0.01077  -0.0049   1.0000   0.0224
  -7.500  -0.7944   0.01657   0.01005  -0.0034   1.0000   0.0231
  -7.250  -0.7763   0.01595   0.00941  -0.0018   1.0000   0.0240
  -7.000  -0.7585   0.01537   0.00878  -0.0001   1.0000   0.0249
  -6.750  -0.7407   0.01487   0.00824   0.0016   1.0000   0.0260
  -6.500  -0.7234   0.01445   0.00778   0.0034   1.0000   0.0270
  -6.250  -0.7119   0.01361   0.00693   0.0062   1.0000   0.0290
  -6.000  -0.6781   0.01306   0.00635   0.0045   0.9968   0.0318
  -5.750  -0.6420   0.01241   0.00567   0.0023   0.9928   0.0363
  -5.500  -0.6062   0.01189   0.00515   0.0003   0.9877   0.0438
  -5.250  -0.5695   0.01121   0.00458  -0.0021   0.9837   0.0629
  -5.000  -0.5372   0.01050   0.00410  -0.0035   0.9761   0.1061
  -4.750  -0.5053   0.00959   0.00361  -0.0052   0.9690   0.1928
  -4.500  -0.4792   0.00856   0.00313  -0.0056   0.9575   0.3164
  -4.250  -0.4542   0.00782   0.00283  -0.0055   0.9445   0.4242
  -4.000  -0.4284   0.00745   0.00267  -0.0051   0.9311   0.4884
  -3.750  -0.4026   0.00725   0.00254  -0.0046   0.9175   0.5273
  -3.500  -0.3767   0.00712   0.00243  -0.0041   0.9039   0.5542
  -3.250  -0.3505   0.00704   0.00233  -0.0036   0.8908   0.5763
  -3.000  -0.3246   0.00696   0.00226  -0.0031   0.8782   0.5976
  -2.750  -0.2984   0.00691   0.00219  -0.0026   0.8657   0.6173
  -2.500  -0.2719   0.00688   0.00214  -0.0022   0.8534   0.6366
  -2.250  -0.2454   0.00685   0.00210  -0.0018   0.8420   0.6530
  -2.000  -0.2187   0.00684   0.00207  -0.0014   0.8314   0.6681
  -1.750  -0.1917   0.00684   0.00203  -0.0012   0.8205   0.6817
  -1.500  -0.1647   0.00682   0.00201  -0.0009   0.8100   0.6941
  -1.250  -0.1375   0.00681   0.00198  -0.0007   0.8002   0.7047
  -1.000  -0.1100   0.00681   0.00194  -0.0005   0.7901   0.7143
  -0.750  -0.0825   0.00680   0.00193  -0.0004   0.7802   0.7240
  -0.500  -0.0551   0.00680   0.00191  -0.0002   0.7710   0.7328
  -0.250  -0.0275   0.00681   0.00189  -0.0001   0.7610   0.7426
   0.000   0.0000   0.00679   0.00190   0.0000   0.7516   0.7516
   0.250   0.0275   0.00681   0.00189   0.0001   0.7426   0.7610
   0.500   0.0551   0.00680   0.00191   0.0002   0.7328   0.7710
   0.750   0.0826   0.00680   0.00193   0.0004   0.7239   0.7801
   1.000   0.1101   0.00681   0.00194   0.0005   0.7143   0.7901
   1.250   0.1375   0.00681   0.00198   0.0007   0.7047   0.8002
   1.500   0.1647   0.00682   0.00201   0.0009   0.6941   0.8099
   1.750   0.1918   0.00684   0.00203   0.0011   0.6817   0.8205
   2.000   0.2188   0.00684   0.00207   0.0014   0.6681   0.8314
   2.250   0.2455   0.00685   0.00210   0.0018   0.6531   0.8420
   2.500   0.2721   0.00688   0.00214   0.0022   0.6366   0.8534
   2.750   0.2985   0.00691   0.00219   0.0026   0.6173   0.8656
   3.000   0.3247   0.00696   0.00226   0.0030   0.5975   0.8782
   3.250   0.3506   0.00704   0.00233   0.0036   0.5763   0.8908
   3.500   0.3768   0.00712   0.00243   0.0041   0.5541   0.9039
   3.750   0.4027   0.00725   0.00254   0.0046   0.5273   0.9175
   4.000   0.4285   0.00745   0.00267   0.0051   0.4883   0.9311
   4.250   0.4542   0.00782   0.00283   0.0055   0.4242   0.9445
   4.500   0.4792   0.00856   0.00313   0.0056   0.3154   0.9575
   4.750   0.5052   0.00959   0.00361   0.0052   0.1930   0.9691
   5.000   0.5373   0.01050   0.00410   0.0035   0.1062   0.9762
   5.250   0.5696   0.01121   0.00458   0.0020   0.0629   0.9838
   5.500   0.6063   0.01189   0.00515  -0.0003   0.0438   0.9878
   5.750   0.6420   0.01241   0.00567  -0.0023   0.0362   0.9929
   6.000   0.6782   0.01306   0.00635  -0.0045   0.0318   0.9969
   6.250   0.7113   0.01360   0.00692  -0.0061   0.0291   1.0000
   6.500   0.7229   0.01443   0.00776  -0.0033   0.0270   1.0000
   6.750   0.7403   0.01487   0.00824  -0.0015   0.0260   1.0000
   7.000   0.7582   0.01536   0.00877   0.0002   0.0249   1.0000
   7.250   0.7760   0.01594   0.00940   0.0019   0.0240   1.0000
   7.500   0.7943   0.01656   0.01005   0.0034   0.0231   1.0000
   7.750   0.8129   0.01727   0.01077   0.0049   0.0224   1.0000
   8.000   0.8306   0.01826   0.01179   0.0063   0.0217   1.0000
   8.250   0.8464   0.02022   0.01382   0.0080   0.0210   1.0000
   8.500   0.8679   0.02088   0.01459   0.0089   0.0206   1.0000
   8.750   0.8892   0.02165   0.01546   0.0098   0.0200   1.0000
   9.000   0.9098   0.02262   0.01655   0.0108   0.0194   1.0000
   9.250   0.9298   0.02386   0.01791   0.0117   0.0189   1.0000
   9.500   0.9491   0.02521   0.01940   0.0127   0.0185   1.0000
   9.750   0.9675   0.02665   0.02099   0.0138   0.0182   1.0000
  10.000   0.9850   0.02814   0.02262   0.0148   0.0178   1.0000
  10.250   1.0006   0.02980   0.02444   0.0160   0.0175   1.0000
  10.500   1.0145   0.03157   0.02638   0.0173   0.0173   1.0000
  10.750   1.0267   0.03334   0.02829   0.0187   0.0169   1.0000
  11.000   1.0335   0.03602   0.03115   0.0203   0.0166   1.0000
  11.250   1.0273   0.04034   0.03583   0.0228   0.0164   1.0000
  11.500   1.0125   0.04440   0.04021   0.0260   0.0163   1.0000
  11.750   1.0017   0.04664   0.04267   0.0285   0.0162   1.0000
  12.000   0.9856   0.05044   0.04669   0.0300   0.0162   1.0000
  12.500   0.9575   0.05828   0.05490   0.0300   0.0163   1.0000
  12.750   0.9433   0.06254   0.05933   0.0286   0.0164   1.0000
  13.000   0.9281   0.06739   0.06434   0.0261   0.0164   1.0000
  13.250   0.9102   0.07327   0.07040   0.0225   0.0165   1.0000
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