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NACA 4418 (naca4418-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 4418 (naca4418-il)
Reynolds number: 50,000
Max Cl/Cd: 5.31 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca4418-il-50000.txt
Download as CSV file: xf-naca4418-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 4418                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2779   0.12876   0.12121  -0.0274   1.0000   0.3077
 -10.000  -0.2957   0.12849   0.12103  -0.0254   1.0000   0.3169
  -9.750  -0.3348   0.12912   0.12184  -0.0231   1.0000   0.3205
  -9.500  -0.2931   0.12335   0.11601  -0.0218   1.0000   0.3285
  -9.250  -0.3108   0.12299   0.11575  -0.0193   1.0000   0.3386
  -9.000  -0.3536   0.12356   0.11650  -0.0164   1.0000   0.3426
  -8.750  -0.3111   0.11827   0.11115  -0.0152   1.0000   0.3518
  -8.500  -0.3414   0.11860   0.11161  -0.0121   1.0000   0.3619
  -8.250  -0.3456   0.11589   0.10898  -0.0102   1.0000   0.3674
  -8.000  -0.3344   0.11363   0.10673  -0.0081   1.0000   0.3780
  -7.750  -0.3947   0.11540   0.10870  -0.0036   1.0000   0.3855
  -7.500  -0.3529   0.11030   0.10355  -0.0032   1.0000   0.3943
  -7.250  -0.3865   0.11047   0.10385   0.0006   1.0000   0.4058
  -7.000  -0.6052   0.08452   0.07783  -0.0184   1.0000   0.2391
  -6.750  -0.6119   0.08025   0.07352  -0.0181   1.0000   0.2377
  -6.500  -0.6218   0.07499   0.06813  -0.0190   1.0000   0.2362
  -6.250  -0.6300   0.06908   0.06198  -0.0208   1.0000   0.2360
  -6.000  -0.6319   0.06322   0.05573  -0.0231   1.0000   0.2373
  -5.750  -0.6274   0.05774   0.04968  -0.0255   1.0000   0.2406
  -5.500  -0.6136   0.05766   0.04984  -0.0233   1.0000   0.2457
  -5.250  -0.6011   0.05545   0.04742  -0.0234   1.0000   0.2509
  -5.000  -0.5865   0.05205   0.04345  -0.0253   1.0000   0.2571
  -4.750  -0.5713   0.05074   0.04210  -0.0248   1.0000   0.2625
  -4.500  -0.5276   0.04974   0.04086  -0.0296   0.9910   0.2732
  -4.250  -0.4802   0.04867   0.03954  -0.0350   0.9793   0.2842
  -4.000  -0.4378   0.04762   0.03804  -0.0395   0.9685   0.2973
  -3.750  -0.4043   0.04714   0.03765  -0.0416   0.9574   0.3083
  -3.500  -0.3666   0.04640   0.03661  -0.0448   0.9467   0.3230
  -3.250  -0.3208   0.04617   0.03617  -0.0490   0.9367   0.3424
  -3.000  -0.2981   0.04582   0.03595  -0.0490   0.9260   0.3565
  -2.750  -0.2628   0.04566   0.03576  -0.0511   0.9159   0.3771
  -2.500  -0.2294   0.04554   0.03564  -0.0529   0.9058   0.3996
  -2.250  -0.2029   0.04555   0.03566  -0.0535   0.8960   0.4221
  -2.000  -0.1643   0.04567   0.03575  -0.0559   0.8864   0.4517
  -1.750  -0.1449   0.04582   0.03601  -0.0553   0.8764   0.4748
  -1.500  -0.1075   0.04611   0.03645  -0.0570   0.8675   0.5076
  -1.250  -0.0914   0.04640   0.03680  -0.0559   0.8577   0.5360
  -1.000  -0.0558   0.04671   0.03729  -0.0571   0.8489   0.5770
  -0.750  -0.0412   0.04708   0.03782  -0.0555   0.8396   0.6125
  -0.500  -0.0136   0.04733   0.03832  -0.0552   0.8310   0.6649
  -0.250   0.0023   0.04763   0.03891  -0.0529   0.8226   0.7233
   0.000   0.0114   0.04775   0.03944  -0.0487   0.8144   0.8044
   0.250   0.0798   0.04843   0.04025  -0.0567   0.8038   1.0000
   0.500   0.0996   0.04921   0.04063  -0.0584   0.7945   1.0000
   0.750   0.1348   0.05022   0.04131  -0.0609   0.7860   1.0000
   1.000   0.1412   0.05141   0.04233  -0.0597   0.7774   1.0000
   1.250   0.1898   0.05235   0.04301  -0.0632   0.7691   1.0000
   1.500   0.1832   0.05382   0.04439  -0.0604   0.7607   1.0000
   1.750   0.2108   0.05499   0.04540  -0.0614   0.7527   1.0000
   2.000   0.2290   0.05638   0.04667  -0.0614   0.7446   1.0000
   2.250   0.2387   0.05786   0.04806  -0.0605   0.7369   1.0000
   2.500   0.2864   0.05890   0.04894  -0.0634   0.7286   1.0000
   2.750   0.2740   0.06087   0.05089  -0.0605   0.7219   1.0000
   3.000   0.2943   0.06234   0.05228  -0.0607   0.7143   1.0000
   3.250   0.3201   0.06386   0.05371  -0.0614   0.7065   1.0000
   3.500   0.3182   0.06589   0.05571  -0.0598   0.7008   1.0000
   3.750   0.3465   0.06733   0.05709  -0.0607   0.6926   1.0000
   4.000   0.3594   0.06928   0.05898  -0.0604   0.6859   1.0000
   4.250   0.3585   0.07154   0.06123  -0.0592   0.6817   1.0000
   4.500   0.3701   0.07359   0.06326  -0.0591   0.6765   1.0000
   4.750   0.3997   0.07523   0.06485  -0.0599   0.6667   1.0000
   5.000   0.3979   0.07783   0.06746  -0.0590   0.6647   1.0000
   5.250   0.4013   0.08055   0.07018  -0.0588   0.6646   1.0000
   5.500   0.4114   0.08356   0.07319  -0.0593   0.6669   1.0000
   5.750   0.4328   0.08688   0.07652  -0.0610   0.6694   1.0000
   6.000   0.3764   0.09290   0.08268  -0.0600   0.7303   1.0000
   6.250   0.3692   0.09389   0.08368  -0.0576   0.7200   1.0000
   6.500   0.4198   0.09845   0.08821  -0.0618   0.7092   1.0000
   6.750   0.4003   0.09836   0.08814  -0.0581   0.6973   1.0000
   7.000   0.4377   0.10242   0.09219  -0.0609   0.6886   1.0000
   7.250   0.4340   0.10317   0.09296  -0.0589   0.6746   1.0000
   7.500   0.4508   0.10622   0.09602  -0.0596   0.6666   1.0000
   7.750   0.4703   0.10843   0.09824  -0.0600   0.6524   1.0000
   8.000   0.4685   0.11041   0.10024  -0.0589   0.6429   1.0000
   8.250   0.5086   0.11430   0.10415  -0.0613   0.6309   1.0000
   8.500   0.4926   0.11520   0.10507  -0.0590   0.6200   1.0000
   8.750   0.5426   0.12040   0.11029  -0.0623   0.6102   1.0000
   9.000   0.5179   0.12030   0.11021  -0.0593   0.5980   1.0000
   9.250   0.5585   0.12528   0.11523  -0.0619   0.5901   1.0000
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