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NACA 4424 (naca4424-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 4424 (naca4424-il)
Reynolds number: 50,000
Max Cl/Cd: 1.96 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca4424-il-50000.txt
Download as CSV file: xf-naca4424-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 4424                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2667   0.13833   0.13121  -0.0134   0.9676   0.4413
  -7.750  -0.2210   0.13487   0.12770  -0.0173   0.9571   0.4525
  -7.500  -0.2590   0.13509   0.12796  -0.0164   0.9516   0.4643
  -7.250  -0.1934   0.13018   0.12298  -0.0211   0.9400   0.4739
  -7.000  -0.5795   0.09954   0.09224  -0.0191   0.9611   0.3178
  -6.750  -0.6346   0.09425   0.08693  -0.0142   0.9613   0.3165
  -6.500  -0.6952   0.09625   0.08925   0.0039   1.0000   0.3140
  -6.250  -0.7790   0.08646   0.07929   0.0089   1.0000   0.3110
  -6.000  -0.8421   0.07810   0.07062   0.0140   1.0000   0.3112
  -5.750  -0.8813   0.07203   0.06419   0.0186   1.0000   0.3137
  -5.500  -0.9115   0.06695   0.05861   0.0233   1.0000   0.3174
  -5.250  -0.9085   0.06529   0.05692   0.0256   1.0000   0.3218
  -5.000  -0.8907   0.06538   0.05714   0.0265   0.9989   0.3274
  -4.750  -0.8820   0.06404   0.05557   0.0273   0.9940   0.3344
  -4.500  -0.8890   0.06148   0.05243   0.0303   0.9907   0.3410
  -4.250  -0.8653   0.06156   0.05273   0.0300   0.9849   0.3475
  -4.000  -0.8418   0.06220   0.05329   0.0294   0.9788   0.3557
  -3.750  -0.8442   0.06019   0.05090   0.0326   0.9744   0.3630
  -3.500  -0.8203   0.06047   0.05123   0.0321   0.9667   0.3711
  -3.250  -0.8075   0.06022   0.05096   0.0335   0.9625   0.3788
  -3.000  -0.7994   0.05942   0.04976   0.0354   0.9546   0.3884
  -2.750  -0.7769   0.05999   0.05048   0.0353   0.9495   0.3967
  -2.500  -0.7639   0.05954   0.04998   0.0367   0.9409   0.4059
  -2.250  -0.7418   0.06048   0.05073   0.0365   0.9350   0.4171
  -2.000  -0.7353   0.05955   0.04987   0.0391   0.9298   0.4250
  -1.750  -0.7177   0.05987   0.04994   0.0398   0.9207   0.4375
  -1.500  -0.6979   0.06058   0.05079   0.0401   0.9163   0.4474
  -1.250  -0.6890   0.05995   0.05008   0.0422   0.9074   0.4583
  -1.000  -0.6616   0.06130   0.05146   0.0414   0.9003   0.4717
  -0.750  -0.6533   0.06124   0.05133   0.0436   0.8959   0.4839
  -0.500  -0.6384   0.06104   0.05120   0.0447   0.8860   0.4960
  -0.250  -0.6095   0.06301   0.05304   0.0437   0.8792   0.5142
   0.000  -0.6004   0.06269   0.05290   0.0455   0.8749   0.5260
   0.250  -0.5867   0.06259   0.05275   0.0468   0.8644   0.5423
   0.500  -0.5541   0.06492   0.05510   0.0453   0.8578   0.5645
   0.750  -0.5470   0.06441   0.05476   0.0473   0.8525   0.5793
   1.000  -0.5274   0.06470   0.05513   0.0474   0.8425   0.6011
   1.250  -0.4849   0.06755   0.05811   0.0439   0.8360   0.6326
   1.500  -0.4782   0.06681   0.05748   0.0455   0.8294   0.6556
   1.750  -0.4504   0.06768   0.05855   0.0441   0.8200   0.6912
   2.000  -0.3979   0.07117   0.06241   0.0389   0.8141   0.7485
   2.250  -0.3746   0.07067   0.06233   0.0367   0.8059   0.8018
   2.500  -0.2106   0.07932   0.07150   0.0077   0.7943   0.8968
   2.750  -0.1449   0.08333   0.07551  -0.0030   0.7841   0.9349
   3.000  -0.0328   0.09061   0.08266  -0.0217   0.7735   0.9834
   3.250  -0.0151   0.09179   0.08360  -0.0261   0.7693   1.0000
   3.500  -0.0340   0.09000   0.08158  -0.0213   0.7577   1.0000
   3.750  -0.0075   0.09247   0.08379  -0.0226   0.7508   1.0000
   4.000  -0.0207   0.09201   0.08320  -0.0188   0.7432   1.0000
   4.250  -0.0044   0.09333   0.08437  -0.0185   0.7327   1.0000
   4.500   0.0293   0.09734   0.08819  -0.0207   0.7277   1.0000
   4.750   0.0098   0.09570   0.08649  -0.0161   0.7161   1.0000
   5.000   0.0371   0.09829   0.08895  -0.0172   0.7085   1.0000
   5.250   0.0394   0.09961   0.09018  -0.0156   0.7023   1.0000
   5.500   0.0482   0.10045   0.09093  -0.0145   0.6904   1.0000
   5.750   0.0849   0.10452   0.09489  -0.0167   0.6846   1.0000
   6.000   0.0671   0.10367   0.09400  -0.0130   0.6745   1.0000
   6.250   0.0908   0.10598   0.09622  -0.0136   0.6654   1.0000
   6.500   0.1158   0.10975   0.09990  -0.0147   0.6609   1.0000
   6.750   0.1036   0.10883   0.09896  -0.0116   0.6483   1.0000
   7.000   0.1359   0.11232   0.10236  -0.0131   0.6414   1.0000
   7.250   0.1274   0.11287   0.10289  -0.0109   0.6336   1.0000
   7.500   0.1424   0.11458   0.10454  -0.0108   0.6235   1.0000
   7.750   0.1833   0.11972   0.10962  -0.0132   0.6181   1.0000
   8.000   0.1590   0.11818   0.10806  -0.0096   0.6071   1.0000
   8.250   0.1835   0.12093   0.11076  -0.0104   0.5993   1.0000
   8.500   0.2018   0.12448   0.11426  -0.0109   0.5947   1.0000
   8.750   0.1940   0.12411   0.11388  -0.0090   0.5823   1.0000
   9.000   0.2255   0.12793   0.11766  -0.0103   0.5760   1.0000
   9.250   0.2177   0.12885   0.11857  -0.0089   0.5697   1.0000
   9.500   0.2289   0.13038   0.12008  -0.0086   0.5587   1.0000
   9.750   0.2660   0.13538   0.12504  -0.0104   0.5534   1.0000
  10.000   0.2453   0.13464   0.12429  -0.0082   0.5452   1.0000
  10.250   0.2627   0.13689   0.12652  -0.0085   0.5360   1.0000
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