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NACA 63(2)-615 (naca632615-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 63(2)-615 (naca632615-il)
Reynolds number: 100,000
Max Cl/Cd: 55.01 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca632615-il-100000.txt
Download as CSV file: xf-naca632615-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(2)-615                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3340   0.10499   0.10009  -0.0477   1.0000   0.1568
 -10.000  -0.3954   0.10382   0.09920  -0.0498   1.0000   0.1629
  -9.750  -0.3821   0.10038   0.09580  -0.0463   1.0000   0.1651
  -9.500  -0.3717   0.09900   0.09442  -0.0421   1.0000   0.1684
  -9.250  -0.3850   0.09812   0.09364  -0.0386   1.0000   0.1720
  -9.000  -0.4161   0.09717   0.09283  -0.0359   1.0000   0.1762
  -8.750  -0.5005   0.09677   0.09270  -0.0353   1.0000   0.1789
  -8.500  -0.4564   0.09381   0.08968  -0.0308   1.0000   0.1829
  -8.250  -0.6037   0.05726   0.05213  -0.0684   0.9769   0.0916
  -8.000  -0.5860   0.05026   0.04451  -0.0733   0.9706   0.0839
  -7.750  -0.5717   0.04495   0.03859  -0.0755   0.9622   0.0811
  -7.500  -0.5397   0.04131   0.03444  -0.0791   0.9570   0.0829
  -7.250  -0.5164   0.03856   0.03122  -0.0802   0.9495   0.0843
  -7.000  -0.4819   0.03574   0.02785  -0.0827   0.9440   0.0858
  -6.750  -0.4473   0.03386   0.02541  -0.0849   0.9384   0.0893
  -6.500  -0.4200   0.03184   0.02339  -0.0857   0.9316   0.0930
  -6.250  -0.3805   0.03042   0.02178  -0.0881   0.9270   0.0982
  -6.000  -0.3507   0.02928   0.02040  -0.0887   0.9205   0.1034
  -5.750  -0.3200   0.02805   0.01929  -0.0896   0.9141   0.1096
  -5.500  -0.2790   0.02692   0.01808  -0.0921   0.9101   0.1191
  -5.250  -0.2558   0.02624   0.01750  -0.0916   0.9023   0.1280
  -5.000  -0.2225   0.02531   0.01669  -0.0929   0.8964   0.1438
  -4.750  -0.1803   0.02396   0.01562  -0.0961   0.8929   0.1804
  -4.500  -0.1592   0.02185   0.01507  -0.0972   0.8850   0.4005
  -4.250  -0.1251   0.02226   0.01569  -0.0976   0.8790   0.5250
  -4.000  -0.0826   0.02283   0.01618  -0.0989   0.8757   0.5709
  -3.750  -0.0722   0.02351   0.01684  -0.0955   0.8651   0.5931
  -3.500  -0.0383   0.02415   0.01747  -0.0949   0.8607   0.6199
  -3.250  -0.0188   0.02480   0.01806  -0.0927   0.8528   0.6427
  -3.000   0.0024   0.02545   0.01872  -0.0900   0.8460   0.6618
  -2.750   0.0346   0.02587   0.01911  -0.0888   0.8425   0.6807
  -2.500   0.0429   0.02644   0.01963  -0.0855   0.8322   0.6953
  -2.250   0.0739   0.02659   0.01971  -0.0850   0.8276   0.7115
  -2.000   0.1074   0.02663   0.01969  -0.0843   0.8248   0.7238
  -1.750   0.1099   0.02716   0.02020  -0.0806   0.8132   0.7333
  -1.500   0.1496   0.02691   0.01982  -0.0826   0.8098   0.7456
  -1.250   0.1569   0.02737   0.02030  -0.0791   0.8003   0.7537
  -1.000   0.1883   0.02728   0.02011  -0.0799   0.7952   0.7643
  -0.750   0.2246   0.02702   0.01978  -0.0807   0.7922   0.7736
  -0.500   0.2301   0.02763   0.02039  -0.0780   0.7815   0.7827
  -0.250   0.2651   0.02743   0.02012  -0.0791   0.7774   0.7927
   0.000   0.3010   0.02710   0.01974  -0.0797   0.7748   0.8010
   0.250   0.3053   0.02796   0.02060  -0.0776   0.7634   0.8115
   0.500   0.3365   0.02767   0.02029  -0.0773   0.7599   0.8198
   0.750   0.3755   0.02734   0.01991  -0.0789   0.7573   0.8295
   1.000   0.3715   0.02840   0.02102  -0.0751   0.7453   0.8398
   1.250   0.4069   0.02801   0.02060  -0.0757   0.7425   0.8492
   1.500   0.4064   0.02913   0.02176  -0.0728   0.7315   0.8610
   1.750   0.4356   0.02891   0.02153  -0.0725   0.7276   0.8716
   2.000   0.4716   0.02838   0.02100  -0.0729   0.7252   0.8822
   2.250   0.4608   0.02983   0.02251  -0.0686   0.7128   0.8967
   2.500   0.4961   0.02935   0.02203  -0.0691   0.7099   0.9095
   2.750   0.5344   0.02874   0.02142  -0.0698   0.7079   0.9230
   3.000   0.5211   0.03033   0.02310  -0.0656   0.6948   0.9449
   3.250   0.5702   0.02964   0.02244  -0.0683   0.6927   0.9608
   3.500   0.5885   0.03127   0.02418  -0.0703   0.6806   1.0000
   3.750   0.6393   0.03076   0.02368  -0.0739   0.6778   1.0000
   4.000   0.6929   0.03001   0.02294  -0.0776   0.6759   1.0000
   4.750   0.8032   0.03049   0.02356  -0.0842   0.6584   1.0000
   5.000   0.8109   0.03242   0.02555  -0.0839   0.6455   1.0000
   5.250   0.8287   0.03371   0.02692  -0.0843   0.6354   1.0000
   5.500   0.8752   0.03292   0.02619  -0.0864   0.6305   1.0000
   5.750   0.9353   0.03113   0.02447  -0.0893   0.6280   1.0000
   6.000   0.9475   0.03242   0.02585  -0.0885   0.6158   1.0000
   6.250   1.0090   0.03031   0.02382  -0.0914   0.6122   1.0000
   6.500   1.0290   0.03087   0.02447  -0.0907   0.6007   1.0000
   6.750   1.0925   0.02842   0.02207  -0.0936   0.5951   1.0000
   7.000   1.1174   0.02834   0.02210  -0.0930   0.5824   1.0000
   7.250   1.1536   0.02745   0.02127  -0.0933   0.5705   1.0000
   7.500   1.1932   0.02610   0.01997  -0.0937   0.5562   1.0000
   7.750   1.2250   0.02503   0.01892  -0.0931   0.5378   1.0000
   8.000   1.2528   0.02424   0.01815  -0.0921   0.5182   1.0000
   8.250   1.2792   0.02367   0.01759  -0.0911   0.4980   1.0000
   8.500   1.2933   0.02374   0.01776  -0.0887   0.4760   1.0000
   8.750   1.3075   0.02377   0.01782  -0.0863   0.4509   1.0000
   9.000   1.3138   0.02415   0.01823  -0.0829   0.4214   1.0000
   9.250   1.3140   0.02476   0.01876  -0.0787   0.3877   1.0000
   9.500   1.3084   0.02591   0.01976  -0.0743   0.3448   1.0000
   9.750   1.2965   0.02776   0.02126  -0.0698   0.2958   1.0000
  10.000   1.2798   0.03038   0.02350  -0.0658   0.2479   1.0000
  10.250   1.2625   0.03352   0.02627  -0.0624   0.2061   1.0000
  10.500   1.2475   0.03687   0.02927  -0.0596   0.1737   1.0000
  10.750   1.2385   0.04001   0.03217  -0.0575   0.1484   1.0000
  11.000   1.2352   0.04282   0.03477  -0.0558   0.1307   1.0000
  11.250   1.2384   0.04520   0.03701  -0.0544   0.1171   1.0000
  11.500   1.2471   0.04724   0.03898  -0.0532   0.1061   1.0000
  11.750   1.2599   0.04909   0.04075  -0.0521   0.0972   1.0000
  12.000   1.2810   0.05057   0.04198  -0.0513   0.0888   1.0000
  12.250   1.2918   0.05258   0.04423  -0.0505   0.0833   1.0000
  12.500   1.3221   0.05397   0.04539  -0.0501   0.0766   1.0000
  12.750   1.3323   0.05615   0.04786  -0.0493   0.0727   1.0000
  13.000   1.3518   0.05804   0.04979  -0.0488   0.0688   1.0000
  13.250   1.3840   0.06031   0.05209  -0.0486   0.0650   1.0000
  13.500   1.3887   0.06312   0.05521  -0.0477   0.0628   1.0000
  13.750   1.3970   0.06584   0.05813  -0.0471   0.0606   1.0000
  14.000   1.4068   0.06862   0.06105  -0.0467   0.0587   1.0000
  14.250   1.4322   0.07201   0.06450  -0.0467   0.0569   1.0000
  14.500   1.4301   0.07642   0.06920  -0.0461   0.0563   1.0000
  14.750   1.4168   0.08071   0.07384  -0.0456   0.0561   1.0000
  15.000   1.4010   0.08540   0.07885  -0.0454   0.0559   1.0000
  15.250   1.3830   0.09050   0.08426  -0.0458   0.0558   1.0000
  15.500   1.3632   0.09600   0.09006  -0.0467   0.0558   1.0000
  15.750   1.3420   0.10194   0.09628  -0.0482   0.0559   1.0000
  16.000   1.3196   0.10836   0.10296  -0.0504   0.0560   1.0000
  16.250   1.2975   0.11523   0.11007  -0.0533   0.0561   1.0000
  16.500   1.2751   0.12262   0.11767  -0.0568   0.0563   1.0000
  16.750   1.1006   0.16359   0.15938  -0.0867   0.0646   1.0000
  17.000   1.0895   0.17333   0.16911  -0.0920   0.0658   1.0000
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