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NACA 63(3)-218 (naca633218-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 63(3)-218 (naca633218-il)
Reynolds number: 50,000
Max Cl/Cd: 22.19 at α=11°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca633218-il-50000.txt
Download as CSV file: xf-naca633218-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(3)-218                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.7869   0.07099   0.06357  -0.0571   1.0000   0.1540
 -12.000  -0.8156   0.06611   0.05855  -0.0572   1.0000   0.1536
 -11.750  -0.8438   0.06216   0.05443  -0.0560   1.0000   0.1535
 -11.500  -0.8682   0.05890   0.05097  -0.0536   1.0000   0.1537
 -11.250  -0.8865   0.05583   0.04763  -0.0511   1.0000   0.1542
 -11.000  -0.8560   0.05280   0.04478  -0.0517   1.0000   0.1598
 -10.750  -0.8566   0.05041   0.04227  -0.0498   1.0000   0.1636
 -10.500  -0.8653   0.04816   0.03981  -0.0468   1.0000   0.1666
 -10.250  -0.8786   0.04634   0.03774  -0.0428   1.0000   0.1691
 -10.000  -0.8697   0.04434   0.03576  -0.0406   1.0000   0.1740
  -9.750  -0.8652   0.04292   0.03434  -0.0377   1.0000   0.1798
  -9.500  -0.8733   0.04164   0.03287  -0.0335   1.0000   0.1846
  -9.250  -0.8616   0.04020   0.03158  -0.0314   1.0000   0.1936
  -9.000  -0.8635   0.03894   0.03016  -0.0278   1.0000   0.2018
  -8.750  -0.8503   0.03764   0.02908  -0.0257   1.0000   0.2151
  -8.500  -0.8440   0.03646   0.02804  -0.0229   1.0000   0.2306
  -8.250  -0.8417   0.03527   0.02701  -0.0197   1.0000   0.2502
  -8.000  -0.8407   0.03407   0.02610  -0.0163   1.0000   0.2757
  -7.750  -0.8418   0.03302   0.02548  -0.0125   1.0000   0.3103
  -7.500  -0.8422   0.03259   0.02557  -0.0082   1.0000   0.3567
  -7.250  -0.8370   0.03350   0.02687  -0.0036   1.0000   0.4095
  -7.000  -0.8175   0.03652   0.03010   0.0014   1.0000   0.4526
  -6.750  -0.7993   0.03933   0.03291   0.0062   1.0000   0.4852
  -6.500  -0.7524   0.04546   0.03902   0.0115   1.0000   0.5095
  -6.250  -0.7240   0.04840   0.04181   0.0149   0.9980   0.5354
  -6.000  -0.5753   0.05853   0.05150   0.0124   0.9912   0.5661
  -5.750  -0.5517   0.05811   0.05090   0.0112   0.9819   0.5928
  -5.500  -0.4202   0.06103   0.05340   0.0026   0.9773   0.6229
  -5.250  -0.3779   0.06058   0.05276  -0.0006   0.9694   0.6463
  -5.000  -0.3431   0.06004   0.05207  -0.0028   0.9609   0.6672
  -4.750  -0.2751   0.05936   0.05118  -0.0091   0.9539   0.6912
  -4.500  -0.2588   0.05864   0.05036  -0.0096   0.9435   0.7074
  -4.250  -0.1615   0.05729   0.04878  -0.0201   0.9377   0.7324
  -4.000  -0.1488   0.05654   0.04796  -0.0202   0.9258   0.7446
  -3.750  -0.0853   0.05515   0.04641  -0.0273   0.9188   0.7627
  -3.500  -0.0340   0.05381   0.04497  -0.0324   0.9086   0.7777
  -3.250   0.0253   0.05223   0.04327  -0.0391   0.8999   0.7937
  -3.000   0.0461   0.05139   0.04236  -0.0402   0.8879   0.8009
  -2.750   0.0925   0.05007   0.04097  -0.0443   0.8759   0.8134
  -2.500   0.1178   0.04922   0.04004  -0.0459   0.8667   0.8197
  -2.250   0.1485   0.04829   0.03909  -0.0474   0.8537   0.8282
  -2.000   0.1641   0.04780   0.03857  -0.0470   0.8414   0.8332
  -1.750   0.1800   0.04724   0.03796  -0.0464   0.8310   0.8384
  -1.500   0.2078   0.04648   0.03720  -0.0474   0.8166   0.8455
  -1.250   0.2228   0.04606   0.03676  -0.0464   0.8030   0.8502
  -1.000   0.2412   0.04541   0.03605  -0.0456   0.7926   0.8557
  -0.750   0.2576   0.04497   0.03562  -0.0447   0.7766   0.8608
  -0.500   0.2753   0.04460   0.03524  -0.0440   0.7609   0.8660
  -0.250   0.2848   0.04436   0.03499  -0.0419   0.7461   0.8709
   0.000   0.3076   0.04359   0.03417  -0.0413   0.7355   0.8767
   0.250   0.3265   0.04338   0.03397  -0.0410   0.7191   0.8818
   0.500   0.3335   0.04352   0.03410  -0.0388   0.7036   0.8868
   0.750   0.3337   0.04365   0.03420  -0.0354   0.6924   0.8923
   1.000   0.3685   0.04326   0.03381  -0.0376   0.6813   0.8984
   1.250   0.3683   0.04407   0.03464  -0.0352   0.6689   0.9039
   1.500   0.3799   0.04408   0.03462  -0.0336   0.6620   0.9103
   1.750   0.3896   0.04518   0.03576  -0.0335   0.6521   0.9168
   2.000   0.3898   0.04596   0.03654  -0.0312   0.6451   0.9235
   2.250   0.4341   0.04529   0.03588  -0.0343   0.6413   0.9304
   2.500   0.3755   0.04930   0.03994  -0.0272   0.6319   0.9381
   2.750   0.3877   0.05043   0.04110  -0.0279   0.6274   0.9461
   3.000   0.4125   0.05080   0.04149  -0.0290   0.6242   0.9545
   3.250   0.4685   0.05054   0.04128  -0.0345   0.6220   0.9621
   3.500   0.4006   0.05532   0.04609  -0.0286   0.6191   0.9726
   3.750   0.3975   0.05762   0.04842  -0.0292   0.6185   0.9825
   4.000   0.4150   0.05962   0.05047  -0.0325   0.6192   0.9921
   4.250   0.4353   0.06142   0.05234  -0.0358   0.6204   1.0000
   4.500   0.3533   0.06439   0.05524  -0.0272   0.6300   1.0000
   4.750   0.3317   0.06558   0.05640  -0.0236   0.6364   1.0000
   5.000   0.3289   0.06640   0.05722  -0.0215   0.6409   1.0000
   5.250   0.1311   0.06956   0.06027  -0.0071   0.7921   1.0000
   5.500   0.1279   0.06911   0.05979  -0.0053   0.7904   1.0000
   5.750   0.1342   0.06909   0.05974  -0.0049   0.7842   1.0000
   6.000   0.1594   0.07060   0.06124  -0.0070   0.7777   1.0000
   6.250   0.1943   0.07340   0.06404  -0.0106   0.7738   1.0000
   6.500   0.2031   0.07404   0.06467  -0.0107   0.7703   1.0000
   6.750   0.2172   0.07480   0.06545  -0.0112   0.7621   1.0000
   7.000   0.2500   0.07743   0.06812  -0.0142   0.7560   1.0000
   7.250   0.2661   0.07913   0.06984  -0.0151   0.7514   1.0000
   7.500   0.2865   0.08046   0.07122  -0.0161   0.7384   1.0000
   7.750   0.3009   0.08196   0.07277  -0.0166   0.7273   1.0000
   8.000   0.3398   0.08568   0.07658  -0.0199   0.7148   1.0000
   8.250   0.3673   0.08827   0.07928  -0.0215   0.6964   1.0000
   8.500   0.3738   0.08938   0.08046  -0.0211   0.6755   1.0000
   8.750   0.3958   0.09138   0.08258  -0.0218   0.6439   1.0000
   9.000   0.4349   0.09376   0.08506  -0.0227   0.6019   1.0000
   9.250   0.5216   0.08730   0.07872  -0.0182   0.5027   1.0000
   9.500   0.5729   0.08645   0.07802  -0.0175   0.4752   1.0000
   9.750   0.5790   0.08822   0.07987  -0.0170   0.4517   1.0000
  10.000   0.6140   0.08782   0.07960  -0.0160   0.4287   1.0000
  10.250   0.6735   0.08439   0.07639  -0.0137   0.4067   1.0000
  10.500   0.6641   0.08780   0.07983  -0.0136   0.3850   1.0000
  10.750   0.7351   0.08088   0.07317  -0.0095   0.3607   1.0000
  11.000   1.0009   0.04511   0.03739   0.0048   0.2907   1.0000
  11.250   0.9711   0.04950   0.04194   0.0061   0.2729   1.0000
  11.500   0.9327   0.05596   0.04858   0.0058   0.2599   1.0000
  11.750   0.9822   0.05050   0.04224   0.0088   0.2270   1.0000
  12.250   1.1252   0.05417   0.04491   0.0084   0.1681   1.0000
  12.500   1.1576   0.05738   0.04815   0.0076   0.1583   1.0000
  12.750   1.1404   0.06037   0.05151   0.0097   0.1562   1.0000
  13.000   1.1247   0.06380   0.05525   0.0111   0.1539   1.0000
  13.250   1.1128   0.06749   0.05918   0.0119   0.1512   1.0000
  13.500   1.1356   0.07064   0.06232   0.0117   0.1452   1.0000
  13.750   1.1074   0.07529   0.06727   0.0122   0.1449   1.0000
  14.000   1.0774   0.08075   0.07298   0.0117   0.1449   1.0000
  14.250   1.0430   0.08729   0.07976   0.0101   0.1453   1.0000
  14.500   1.0066   0.09506   0.08772   0.0074   0.1460   1.0000
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