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NACA 63(2)A-015 (naca632a015-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 63(2)A-015 (naca632a015-il)
Reynolds number: 50,000
Max Cl/Cd: 29.65 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca632a015-il-50000-n5.txt
Download as CSV file: xf-naca632a015-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(2)A-015                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4934   0.10538   0.09780  -0.0415   1.0000   0.0535
 -11.500  -0.4937   0.10091   0.09337  -0.0429   1.0000   0.0530
 -11.250  -0.4991   0.09596   0.08844  -0.0449   1.0000   0.0523
 -11.000  -0.5099   0.09075   0.08324  -0.0474   1.0000   0.0516
 -10.750  -0.5265   0.08552   0.07800  -0.0497   1.0000   0.0509
 -10.500  -0.5466   0.08076   0.07319  -0.0513   1.0000   0.0504
 -10.250  -0.5666   0.07678   0.06915  -0.0516   1.0000   0.0497
 -10.000  -0.5883   0.07328   0.06556  -0.0506   1.0000   0.0493
  -9.750  -0.6086   0.07044   0.06264  -0.0481   1.0000   0.0489
  -9.500  -0.6281   0.06782   0.05992  -0.0446   1.0000   0.0485
  -9.250  -0.6431   0.06512   0.05706  -0.0412   1.0000   0.0482
  -9.000  -0.6548   0.06253   0.05430  -0.0377   1.0000   0.0479
  -8.750  -0.6641   0.05995   0.05152  -0.0340   1.0000   0.0477
  -8.500  -0.6702   0.05753   0.04889  -0.0304   1.0000   0.0476
  -8.250  -0.6744   0.05520   0.04635  -0.0267   1.0000   0.0476
  -8.000  -0.6766   0.05303   0.04396  -0.0231   1.0000   0.0477
  -7.750  -0.6773   0.05107   0.04182  -0.0195   1.0000   0.0481
  -7.500  -0.6771   0.04933   0.03988  -0.0158   1.0000   0.0491
  -7.250  -0.6765   0.04765   0.03798  -0.0122   1.0000   0.0501
  -7.000  -0.6746   0.04603   0.03610  -0.0086   1.0000   0.0511
  -6.750  -0.6712   0.04441   0.03417  -0.0050   1.0000   0.0523
  -6.500  -0.6620   0.04275   0.03216  -0.0023   0.9992   0.0531
  -6.250  -0.6268   0.04019   0.02931  -0.0042   0.9914   0.0546
  -6.000  -0.5894   0.03820   0.02724  -0.0066   0.9839   0.0576
  -5.750  -0.5519   0.03652   0.02528  -0.0084   0.9758   0.0618
  -5.500  -0.5068   0.03472   0.02342  -0.0112   0.9706   0.0660
  -5.250  -0.4666   0.03347   0.02211  -0.0131   0.9629   0.0726
  -5.000  -0.4236   0.03219   0.02086  -0.0156   0.9571   0.0805
  -4.750  -0.3910   0.03129   0.01979  -0.0165   0.9476   0.0885
  -4.500  -0.3613   0.03006   0.01858  -0.0176   0.9389   0.0967
  -4.250  -0.3358   0.02903   0.01746  -0.0179   0.9285   0.1060
  -4.000  -0.3121   0.02807   0.01639  -0.0179   0.9182   0.1167
  -3.750  -0.2841   0.02683   0.01516  -0.0188   0.9098   0.1360
  -3.500  -0.2730   0.02497   0.01400  -0.0174   0.8982   0.2084
  -3.250  -0.2669   0.02378   0.01466  -0.0125   0.8889   0.5815
  -3.000  -0.2459   0.02428   0.01521  -0.0095   0.8790   0.6574
  -2.750  -0.2217   0.02485   0.01570  -0.0071   0.8699   0.7041
  -2.500  -0.1913   0.02577   0.01660  -0.0049   0.8621   0.7494
  -2.250  -0.1378   0.02706   0.01777  -0.0058   0.8581   0.7895
  -2.000  -0.1106   0.02708   0.01761  -0.0057   0.8475   0.7992
  -1.750  -0.0721   0.02687   0.01719  -0.0078   0.8411   0.8071
  -1.500  -0.0458   0.02686   0.01706  -0.0078   0.8303   0.8153
  -1.250  -0.0089   0.02666   0.01668  -0.0095   0.8239   0.8236
  -1.000   0.0190   0.02673   0.01666  -0.0098   0.8133   0.8317
  -0.750   0.0546   0.02655   0.01634  -0.0113   0.8068   0.8403
  -0.500   0.0835   0.02668   0.01640  -0.0119   0.7963   0.8482
  -0.250   0.1185   0.02653   0.01613  -0.0132   0.7898   0.8572
   0.000   0.1489   0.02670   0.01627  -0.0141   0.7792   0.8649
   0.250   0.1841   0.02657   0.01604  -0.0154   0.7726   0.8741
   0.500   0.2164   0.02677   0.01622  -0.0167   0.7617   0.8817
   0.750   0.2487   0.02671   0.01611  -0.0176   0.7538   0.8911
   1.000   0.2876   0.02680   0.01619  -0.0199   0.7431   0.8979
   1.250   0.3163   0.02683   0.01619  -0.0203   0.7326   0.9080
   1.500   0.3620   0.02663   0.01595  -0.0234   0.7225   0.9138
   1.750   0.3884   0.02666   0.01599  -0.0234   0.7091   0.9245
   2.000   0.4276   0.02653   0.01585  -0.0255   0.6953   0.9314
   2.250   0.4592   0.02638   0.01569  -0.0261   0.6818   0.9413
   2.500   0.4990   0.02612   0.01543  -0.0282   0.6682   0.9487
   2.750   0.5331   0.02592   0.01523  -0.0293   0.6550   0.9578
   3.000   0.5678   0.02583   0.01517  -0.0309   0.6399   0.9669
   3.250   0.6024   0.02574   0.01513  -0.0325   0.6249   0.9760
   3.500   0.6371   0.02563   0.01509  -0.0341   0.6094   0.9854
   3.750   0.6733   0.02550   0.01499  -0.0361   0.5929   0.9948
   4.000   0.6991   0.02543   0.01496  -0.0362   0.5767   1.0000
   4.250   0.7096   0.02548   0.01505  -0.0334   0.5619   1.0000
   4.500   0.7200   0.02554   0.01511  -0.0305   0.5467   1.0000
   4.750   0.7302   0.02561   0.01519  -0.0275   0.5309   1.0000
   5.000   0.7405   0.02572   0.01529  -0.0246   0.5148   1.0000
   5.250   0.7508   0.02587   0.01544  -0.0216   0.4982   1.0000
   5.500   0.7612   0.02606   0.01561  -0.0186   0.4809   1.0000
   5.750   0.7721   0.02629   0.01581  -0.0157   0.4634   1.0000
   6.000   0.7837   0.02656   0.01604  -0.0129   0.4458   1.0000
   6.250   0.7960   0.02689   0.01633  -0.0103   0.4288   1.0000
   6.500   0.8086   0.02727   0.01665  -0.0078   0.4121   1.0000
   6.750   0.8215   0.02771   0.01704  -0.0054   0.3961   1.0000
   7.000   0.8345   0.02822   0.01751  -0.0030   0.3809   1.0000
   7.250   0.8476   0.02879   0.01806  -0.0008   0.3668   1.0000
   7.500   0.8612   0.02940   0.01863   0.0014   0.3534   1.0000
   7.750   0.8758   0.03003   0.01921   0.0034   0.3411   1.0000
   8.000   0.8919   0.03063   0.01975   0.0051   0.3292   1.0000
   8.250   0.9038   0.03142   0.02058   0.0073   0.3171   1.0000
   8.500   0.9167   0.03223   0.02143   0.0092   0.3059   1.0000
   8.750   0.9327   0.03298   0.02214   0.0108   0.2954   1.0000
   9.000   0.9453   0.03385   0.02308   0.0127   0.2850   1.0000
   9.250   0.9568   0.03481   0.02412   0.0147   0.2751   1.0000
   9.500   0.9749   0.03559   0.02484   0.0159   0.2655   1.0000
   9.750   0.9798   0.03673   0.02616   0.0185   0.2559   1.0000
  10.000   0.9912   0.03769   0.02715   0.0204   0.2468   1.0000
  10.250   0.9978   0.03869   0.02821   0.0228   0.2372   1.0000
  10.500   0.9998   0.03993   0.02955   0.0255   0.2280   1.0000
  10.750   1.0111   0.04079   0.03034   0.0271   0.2185   1.0000
  11.000   1.0059   0.04246   0.03223   0.0299   0.2098   1.0000
  11.250   1.0132   0.04364   0.03341   0.0315   0.2013   1.0000
  11.500   1.0110   0.04546   0.03542   0.0335   0.1931   1.0000
  11.750   1.0160   0.04697   0.03698   0.0349   0.1855   1.0000
  12.000   1.0128   0.04912   0.03929   0.0363   0.1780   1.0000
  12.250   1.0166   0.05087   0.04109   0.0373   0.1709   1.0000
  12.500   1.0092   0.05363   0.04405   0.0383   0.1643   1.0000
  12.750   1.0146   0.05530   0.04571   0.0391   0.1576   1.0000
  13.000   0.9993   0.05923   0.04990   0.0393   0.1522   1.0000
  13.250   1.0045   0.06109   0.05180   0.0398   0.1463   1.0000
  13.500   0.9892   0.06544   0.05634   0.0394   0.1419   1.0000
  13.750   0.9659   0.07108   0.06220   0.0381   0.1380   1.0000
  14.000   0.9846   0.07124   0.06226   0.0390   0.1318   1.0000
  14.250   0.9450   0.07970   0.07099   0.0360   0.1296   1.0000
  14.500   0.8663   0.09619   0.08770   0.0281   0.1285   1.0000
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