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NACA 63-015A AIRFOIL (n63015a-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-015A AIRFOIL (n63015a-il)
Reynolds number: 200,000
Max Cl/Cd: 53.23 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63015a-il-200000.txt
Download as CSV file: xf-n63015a-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-015A AIRFOIL                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.5034   0.14403   0.14051  -0.0137   1.0000   0.0744
 -15.000  -0.6472   0.16174   0.15789   0.0121   1.0000   0.0683
 -14.750  -0.8803   0.09236   0.08807  -0.0300   1.0000   0.0377
 -14.500  -0.9014   0.08555   0.08114  -0.0331   1.0000   0.0374
 -14.250  -0.9247   0.07913   0.07456  -0.0359   1.0000   0.0372
 -14.000  -0.9474   0.07328   0.06854  -0.0381   1.0000   0.0370
 -13.750  -0.9692   0.06802   0.06308  -0.0395   1.0000   0.0368
 -13.500  -0.9891   0.06334   0.05818  -0.0401   1.0000   0.0367
 -13.250  -1.0069   0.05917   0.05378  -0.0400   1.0000   0.0367
 -13.000  -1.0221   0.05547   0.04983  -0.0392   1.0000   0.0367
 -12.750  -1.0345   0.05216   0.04627  -0.0378   1.0000   0.0368
 -12.500  -1.0433   0.04916   0.04301  -0.0360   1.0000   0.0368
 -12.250  -1.0485   0.04641   0.03998  -0.0338   1.0000   0.0370
 -12.000  -1.0498   0.04383   0.03714  -0.0316   1.0000   0.0371
 -11.750  -1.0474   0.04149   0.03452  -0.0293   1.0000   0.0373
 -11.500  -1.0416   0.03941   0.03217  -0.0272   1.0000   0.0375
 -11.250  -1.0328   0.03760   0.03008  -0.0252   1.0000   0.0379
 -11.000  -1.0094   0.03469   0.02701  -0.0254   1.0000   0.0386
 -10.750  -0.9853   0.03281   0.02513  -0.0256   1.0000   0.0397
 -10.500  -0.9677   0.03156   0.02384  -0.0247   1.0000   0.0410
 -10.250  -0.9499   0.03036   0.02255  -0.0236   1.0000   0.0425
 -10.000  -0.9308   0.02914   0.02120  -0.0227   1.0000   0.0439
  -9.750  -0.9122   0.02807   0.01997  -0.0215   1.0000   0.0451
  -9.500  -0.8879   0.02624   0.01823  -0.0215   1.0000   0.0472
  -9.250  -0.8721   0.02522   0.01724  -0.0200   1.0000   0.0493
  -9.000  -0.8573   0.02432   0.01628  -0.0183   1.0000   0.0519
  -8.750  -0.8445   0.02324   0.01518  -0.0162   1.0000   0.0550
  -8.500  -0.8332   0.02230   0.01432  -0.0140   1.0000   0.0586
  -8.250  -0.8201   0.02160   0.01354  -0.0118   1.0000   0.0630
  -8.000  -0.8149   0.02054   0.01258  -0.0085   1.0000   0.0678
  -7.750  -0.8053   0.01994   0.01193  -0.0055   1.0000   0.0743
  -7.500  -0.8035   0.01909   0.01121  -0.0015   1.0000   0.0821
  -7.250  -0.8022   0.01842   0.01061   0.0028   1.0000   0.0918
  -7.000  -0.8023   0.01783   0.01009   0.0071   1.0000   0.1044
  -6.500  -0.7633   0.01560   0.00847   0.0073   0.9917   0.1976
  -6.250  -0.7338   0.01398   0.00760   0.0051   0.9837   0.3238
  -6.000  -0.7025   0.01320   0.00728   0.0035   0.9747   0.4237
  -5.750  -0.6626   0.01295   0.00713   0.0007   0.9693   0.4794
  -5.500  -0.6272   0.01283   0.00701  -0.0010   0.9606   0.5134
  -5.250  -0.5868   0.01275   0.00695  -0.0035   0.9555   0.5419
  -5.000  -0.5551   0.01273   0.00691  -0.0042   0.9454   0.5635
  -4.750  -0.5173   0.01270   0.00686  -0.0060   0.9397   0.5819
  -4.500  -0.4886   0.01268   0.00678  -0.0060   0.9286   0.5965
  -4.250  -0.4573   0.01265   0.00669  -0.0065   0.9202   0.6106
  -4.000  -0.4286   0.01265   0.00668  -0.0064   0.9103   0.6241
  -3.750  -0.4010   0.01270   0.00672  -0.0060   0.9005   0.6371
  -3.500  -0.3727   0.01271   0.00670  -0.0056   0.8917   0.6491
  -3.250  -0.3475   0.01271   0.00665  -0.0049   0.8809   0.6606
  -3.000  -0.3199   0.01271   0.00662  -0.0045   0.8726   0.6706
  -2.750  -0.2939   0.01270   0.00658  -0.0039   0.8620   0.6796
  -2.500  -0.2678   0.01268   0.00649  -0.0034   0.8531   0.6892
  -2.250  -0.2406   0.01263   0.00642  -0.0030   0.8438   0.6963
  -2.000  -0.2146   0.01260   0.00634  -0.0025   0.8346   0.7049
  -1.750  -0.1873   0.01255   0.00626  -0.0022   0.8261   0.7120
  -1.500  -0.1610   0.01254   0.00621  -0.0018   0.8168   0.7201
  -1.250  -0.1339   0.01249   0.00612  -0.0015   0.8088   0.7276
  -1.000  -0.1074   0.01249   0.00612  -0.0012   0.7997   0.7354
  -0.750  -0.0804   0.01245   0.00603  -0.0009   0.7920   0.7433
  -0.500  -0.0537   0.01246   0.00606  -0.0006   0.7830   0.7509
  -0.250  -0.0268   0.01243   0.00599  -0.0003   0.7755   0.7592
   0.000   0.0000   0.01245   0.00604   0.0000   0.7667   0.7667
   0.250   0.0268   0.01243   0.00598   0.0003   0.7592   0.7755
   0.500   0.0537   0.01246   0.00606   0.0006   0.7509   0.7830
   0.750   0.0804   0.01245   0.00603   0.0009   0.7433   0.7920
   1.000   0.1074   0.01249   0.00612   0.0012   0.7354   0.7997
   1.250   0.1339   0.01249   0.00612   0.0015   0.7276   0.8088
   1.500   0.1610   0.01254   0.00622   0.0018   0.7201   0.8168
   1.750   0.1873   0.01255   0.00626   0.0022   0.7120   0.8261
   2.000   0.2146   0.01260   0.00634   0.0025   0.7049   0.8346
   2.250   0.2406   0.01263   0.00642   0.0030   0.6964   0.8438
   2.500   0.2678   0.01268   0.00649   0.0034   0.6892   0.8531
   2.750   0.2939   0.01270   0.00658   0.0039   0.6796   0.8620
   3.000   0.3199   0.01271   0.00662   0.0045   0.6706   0.8726
   3.250   0.3475   0.01271   0.00665   0.0049   0.6606   0.8809
   3.500   0.3727   0.01271   0.00670   0.0056   0.6491   0.8917
   3.750   0.4010   0.01270   0.00672   0.0060   0.6371   0.9005
   4.000   0.4285   0.01265   0.00668   0.0064   0.6241   0.9103
   4.250   0.4573   0.01265   0.00669   0.0065   0.6106   0.9202
   4.500   0.4886   0.01268   0.00678   0.0060   0.5965   0.9286
   4.750   0.5173   0.01270   0.00685   0.0060   0.5819   0.9397
   5.000   0.5551   0.01273   0.00691   0.0042   0.5635   0.9455
   5.250   0.5868   0.01275   0.00695   0.0035   0.5418   0.9556
   5.500   0.6272   0.01282   0.00701   0.0010   0.5134   0.9606
   5.750   0.6625   0.01294   0.00713  -0.0007   0.4794   0.9694
   6.000   0.7026   0.01320   0.00728  -0.0035   0.4237   0.9748
   6.250   0.7339   0.01398   0.00759  -0.0051   0.3236   0.9837
   6.500   0.7634   0.01559   0.00847  -0.0073   0.1976   0.9917
   6.750   0.7955   0.01712   0.00950  -0.0100   0.1270   0.9989
   7.000   0.8021   0.01782   0.01008  -0.0071   0.1044   1.0000
   7.250   0.8021   0.01842   0.01060  -0.0027   0.0918   1.0000
   7.500   0.8034   0.01909   0.01120   0.0015   0.0821   1.0000
   7.750   0.8053   0.01994   0.01193   0.0055   0.0743   1.0000
   8.000   0.8149   0.02054   0.01258   0.0085   0.0678   1.0000
   8.250   0.8202   0.02159   0.01354   0.0118   0.0630   1.0000
   8.500   0.8333   0.02230   0.01432   0.0140   0.0586   1.0000
   8.750   0.8447   0.02324   0.01518   0.0162   0.0549   1.0000
   9.000   0.8576   0.02432   0.01628   0.0182   0.0519   1.0000
   9.250   0.8725   0.02522   0.01724   0.0200   0.0493   1.0000
   9.500   0.8883   0.02624   0.01823   0.0214   0.0472   1.0000
   9.750   0.9126   0.02807   0.01997   0.0214   0.0451   1.0000
  10.000   0.9313   0.02915   0.02120   0.0226   0.0439   1.0000
  10.250   0.9503   0.03037   0.02256   0.0236   0.0424   1.0000
  10.500   0.9682   0.03157   0.02385   0.0246   0.0410   1.0000
  10.750   0.9858   0.03282   0.02514   0.0255   0.0397   1.0000
  11.000   1.0100   0.03470   0.02703   0.0253   0.0386   1.0000
  11.250   1.0333   0.03761   0.03010   0.0251   0.0379   1.0000
  11.500   1.0421   0.03943   0.03219   0.0271   0.0375   1.0000
  11.750   1.0479   0.04151   0.03455   0.0292   0.0373   1.0000
  12.000   1.0503   0.04386   0.03717   0.0315   0.0371   1.0000
  12.250   1.0491   0.04644   0.04002   0.0337   0.0370   1.0000
  12.500   1.0439   0.04919   0.04304   0.0359   0.0368   1.0000
  12.750   1.0350   0.05220   0.04631   0.0377   0.0368   1.0000
  13.000   1.0228   0.05551   0.04987   0.0391   0.0367   1.0000
  13.250   1.0076   0.05922   0.05383   0.0399   0.0367   1.0000
  13.500   0.9897   0.06340   0.05824   0.0399   0.0367   1.0000
  13.750   0.9698   0.06810   0.06316   0.0393   0.0368   1.0000
  14.000   0.9482   0.07337   0.06863   0.0379   0.0370   1.0000
  14.250   0.9252   0.07924   0.07469   0.0356   0.0372   1.0000
  14.500   0.9022   0.08567   0.08127   0.0328   0.0374   1.0000
  14.750   0.8809   0.09252   0.08824   0.0297   0.0377   1.0000
  15.000   0.6488   0.16188   0.15803  -0.0124   0.0683   1.0000
  15.250   0.5024   0.14366   0.14014   0.0139   0.0744   1.0000
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