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NACA 63(2)-215 MOD B (n63215b-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 63(2)-215 MOD B (n63215b-il)
Reynolds number: 100,000
Max Cl/Cd: 32.85 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63215b-il-100000.txt
Download as CSV file: xf-n63215b-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(2)-215 MOD B                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6313   0.08733   0.08191  -0.0404   1.0000   0.0804
 -12.000  -0.6441   0.08080   0.07536  -0.0432   1.0000   0.0787
 -11.750  -0.6834   0.07249   0.06692  -0.0481   1.0000   0.0765
 -11.500  -0.7315   0.06517   0.05936  -0.0514   1.0000   0.0741
 -11.250  -0.8231   0.05955   0.05310  -0.0493   1.0000   0.0707
 -11.000  -0.8392   0.05716   0.05036  -0.0469   1.0000   0.0700
 -10.750  -0.8419   0.05390   0.04683  -0.0453   1.0000   0.0698
 -10.500  -0.8426   0.05057   0.04324  -0.0436   1.0000   0.0697
 -10.250  -0.8416   0.04732   0.03970  -0.0418   1.0000   0.0700
 -10.000  -0.8328   0.04374   0.03601  -0.0407   1.0000   0.0711
  -9.750  -0.8166   0.04182   0.03417  -0.0398   1.0000   0.0735
  -9.500  -0.8067   0.04004   0.03228  -0.0379   1.0000   0.0753
  -9.250  -0.8009   0.03832   0.03038  -0.0353   1.0000   0.0771
  -9.000  -0.7979   0.03689   0.02870  -0.0321   1.0000   0.0789
  -8.750  -0.7972   0.03575   0.02730  -0.0284   1.0000   0.0806
  -8.500  -0.7933   0.03428   0.02562  -0.0252   1.0000   0.0822
  -8.250  -0.7821   0.03257   0.02397  -0.0231   1.0000   0.0843
  -8.000  -0.7723   0.03149   0.02287  -0.0207   1.0000   0.0868
  -7.750  -0.7618   0.03053   0.02184  -0.0184   1.0000   0.0898
  -7.500  -0.7498   0.02959   0.02074  -0.0162   1.0000   0.0927
  -7.250  -0.7356   0.02846   0.01949  -0.0142   1.0000   0.0952
  -7.000  -0.7203   0.02729   0.01847  -0.0126   1.0000   0.0987
  -6.750  -0.7064   0.02655   0.01775  -0.0108   1.0000   0.1033
  -6.500  -0.6787   0.02559   0.01674  -0.0112   0.9968   0.1098
  -6.250  -0.6427   0.02452   0.01585  -0.0133   0.9911   0.1194
  -6.000  -0.6109   0.02344   0.01493  -0.0148   0.9844   0.1339
  -5.750  -0.5791   0.02208   0.01390  -0.0167   0.9786   0.1649
  -5.500  -0.5632   0.01950   0.01250  -0.0171   0.9710   0.2958
  -5.250  -0.5346   0.01906   0.01289  -0.0177   0.9645   0.4750
  -5.000  -0.5050   0.01952   0.01335  -0.0178   0.9569   0.5248
  -4.750  -0.4676   0.02020   0.01400  -0.0190   0.9515   0.5596
  -4.500  -0.4441   0.02087   0.01470  -0.0174   0.9440   0.5821
  -4.250  -0.4095   0.02168   0.01547  -0.0178   0.9386   0.6087
  -4.000  -0.3853   0.02255   0.01639  -0.0160   0.9317   0.6273
  -3.750  -0.3558   0.02336   0.01721  -0.0151   0.9257   0.6448
  -3.500  -0.3186   0.02405   0.01785  -0.0158   0.9218   0.6607
  -3.250  -0.3041   0.02439   0.01815  -0.0133   0.9136   0.6746
  -3.000  -0.2710   0.02504   0.01878  -0.0131   0.9083   0.6900
  -2.750  -0.2466   0.02571   0.01947  -0.0110   0.9013   0.7003
  -2.500  -0.2091   0.02573   0.01942  -0.0124   0.8932   0.7109
  -2.250  -0.1740   0.02572   0.01934  -0.0133   0.8838   0.7207
  -2.000  -0.1224   0.02566   0.01922  -0.0161   0.8757   0.7290
  -1.750  -0.0969   0.02542   0.01890  -0.0160   0.8648   0.7402
  -1.500  -0.0481   0.02528   0.01873  -0.0179   0.8582   0.7456
  -1.250  -0.0304   0.02513   0.01853  -0.0166   0.8472   0.7553
  -1.000   0.0121   0.02487   0.01825  -0.0178   0.8413   0.7614
  -0.750   0.0301   0.02477   0.01814  -0.0162   0.8298   0.7702
  -0.500   0.0626   0.02444   0.01778  -0.0159   0.8204   0.7774
  -0.250   0.0945   0.02403   0.01735  -0.0154   0.8100   0.7853
   0.000   0.1181   0.02368   0.01699  -0.0141   0.7975   0.7931
   0.250   0.1468   0.02327   0.01656  -0.0130   0.7865   0.8001
   0.500   0.1775   0.02265   0.01590  -0.0123   0.7758   0.8085
   0.750   0.2010   0.02228   0.01555  -0.0104   0.7620   0.8158
   1.000   0.2256   0.02174   0.01500  -0.0090   0.7477   0.8246
   1.250   0.2513   0.02123   0.01448  -0.0072   0.7328   0.8320
   1.500   0.2762   0.02061   0.01385  -0.0055   0.7164   0.8413
   1.750   0.3020   0.01999   0.01321  -0.0035   0.6974   0.8497
   2.000   0.3276   0.01928   0.01245  -0.0018   0.6753   0.8586
   2.250   0.3504   0.01864   0.01178   0.0004   0.6437   0.8676
   2.500   0.3711   0.01808   0.01113   0.0028   0.5961   0.8768
   2.750   0.3885   0.01774   0.01050   0.0055   0.5236   0.8880
   3.000   0.4073   0.01791   0.01012   0.0078   0.4455   0.8970
   3.250   0.4260   0.01832   0.01007   0.0094   0.4016   0.9076
   3.500   0.4470   0.01878   0.01022   0.0105   0.3736   0.9194
   3.750   0.4804   0.01949   0.01057   0.0095   0.3511   0.9279
   4.000   0.5133   0.02012   0.01103   0.0083   0.3329   0.9381
   4.250   0.5495   0.02074   0.01152   0.0064   0.3161   0.9481
   4.500   0.5915   0.02137   0.01203   0.0034   0.3001   0.9561
   4.750   0.6315   0.02199   0.01250   0.0006   0.2866   0.9655
   5.000   0.6797   0.02258   0.01311  -0.0038   0.2731   0.9724
   5.250   0.7228   0.02327   0.01382  -0.0074   0.2625   0.9811
   5.500   0.7688   0.02409   0.01444  -0.0114   0.2532   0.9888
   5.750   0.8116   0.02471   0.01525  -0.0151   0.2432   0.9986
   6.000   0.8295   0.02535   0.01573  -0.0143   0.2376   1.0000
   6.250   0.8345   0.02585   0.01640  -0.0113   0.2324   1.0000
   6.500   0.8399   0.02632   0.01693  -0.0083   0.2273   1.0000
   6.750   0.8519   0.02693   0.01743  -0.0063   0.2228   1.0000
   7.000   0.8698   0.02792   0.01850  -0.0054   0.2179   1.0000
   7.250   0.8910   0.02885   0.01957  -0.0051   0.2122   1.0000
   7.500   0.9168   0.02972   0.02036  -0.0053   0.2069   1.0000
   7.750   0.9394   0.03099   0.02173  -0.0053   0.2018   1.0000
   8.000   0.9610   0.03207   0.02298  -0.0050   0.1962   1.0000
   8.250   0.9858   0.03305   0.02393  -0.0052   0.1916   1.0000
   8.500   1.0097   0.03456   0.02543  -0.0053   0.1876   1.0000
   8.750   1.0242   0.03604   0.02726  -0.0043   0.1830   1.0000
   9.000   1.0450   0.03720   0.02852  -0.0039   0.1786   1.0000
   9.250   1.0693   0.03826   0.02952  -0.0040   0.1750   1.0000
   9.500   1.0876   0.04030   0.03164  -0.0036   0.1720   1.0000
   9.750   1.0918   0.04265   0.03444  -0.0018   0.1692   1.0000
  10.000   1.0966   0.04509   0.03720  -0.0003   0.1664   1.0000
  10.250   1.1048   0.04720   0.03950   0.0009   0.1636   1.0000
  10.500   1.1254   0.04846   0.04074   0.0011   0.1608   1.0000
  10.750   1.1527   0.04999   0.04213   0.0006   0.1579   1.0000
  11.000   1.1362   0.05350   0.04604   0.0033   0.1563   1.0000
  11.250   1.1029   0.05748   0.05040   0.0070   0.1553   1.0000
  11.500   1.0580   0.06245   0.05565   0.0098   0.1549   1.0000
  11.750   0.9928   0.07053   0.06403   0.0096   0.1554   1.0000
  12.000   0.8941   0.08657   0.08030   0.0026   0.1569   1.0000
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