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NACA 4418 (naca4418-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 4418 (naca4418-il)
Reynolds number: 50,000
Max Cl/Cd: 23.06 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca4418-il-50000-n5.txt
Download as CSV file: xf-naca4418-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3656   0.11726   0.10903  -0.0518   1.0000   0.1065
 -11.500  -0.3828   0.11251   0.10435  -0.0525   1.0000   0.1079
 -11.250  -0.4127   0.10592   0.09783  -0.0542   1.0000   0.1092
 -11.000  -0.4209   0.10309   0.09508  -0.0534   1.0000   0.1107
 -10.750  -0.4255   0.10102   0.09308  -0.0519   1.0000   0.1121
 -10.500  -0.4405   0.09761   0.08975  -0.0512   1.0000   0.1137
 -10.250  -0.4703   0.09223   0.08446  -0.0515   1.0000   0.1153
 -10.000  -0.5566   0.07924   0.07152  -0.0559   1.0000   0.1160
  -9.750  -0.6723   0.06874   0.06090  -0.0544   1.0000   0.1140
  -9.500  -0.7002   0.06252   0.05437  -0.0558   0.9946   0.1160
  -9.250  -0.7150   0.05513   0.04623  -0.0590   0.9847   0.1197
  -9.000  -0.6873   0.05396   0.04507  -0.0607   0.9787   0.1230
  -8.750  -0.6669   0.05204   0.04298  -0.0620   0.9712   0.1272
  -8.500  -0.6550   0.04836   0.03870  -0.0635   0.9635   0.1321
  -8.250  -0.6250   0.04787   0.03832  -0.0646   0.9566   0.1360
  -8.000  -0.6018   0.04597   0.03610  -0.0659   0.9497   0.1414
  -7.750  -0.5785   0.04445   0.03438  -0.0667   0.9418   0.1462
  -7.500  -0.5465   0.04349   0.03333  -0.0684   0.9360   0.1517
  -7.250  -0.5276   0.04179   0.03122  -0.0683   0.9268   0.1576
  -7.000  -0.4927   0.04118   0.03068  -0.0702   0.9212   0.1629
  -6.750  -0.4719   0.04009   0.02935  -0.0698   0.9119   0.1690
  -6.500  -0.4400   0.03917   0.02833  -0.0712   0.9055   0.1751
  -6.250  -0.4138   0.03842   0.02748  -0.0715   0.8975   0.1816
  -6.000  -0.3856   0.03748   0.02634  -0.0721   0.8896   0.1890
  -5.750  -0.3482   0.03677   0.02562  -0.0741   0.8847   0.1971
  -5.500  -0.3295   0.03611   0.02476  -0.0730   0.8740   0.2049
  -5.250  -0.2943   0.03551   0.02422  -0.0745   0.8681   0.2138
  -5.000  -0.2707   0.03497   0.02354  -0.0741   0.8590   0.2233
  -4.750  -0.2401   0.03450   0.02312  -0.0747   0.8515   0.2337
  -4.500  -0.2008   0.03387   0.02247  -0.0767   0.8470   0.2468
  -4.250  -0.1844   0.03367   0.02215  -0.0750   0.8353   0.2585
  -4.000  -0.1479   0.03318   0.02171  -0.0765   0.8297   0.2731
  -3.750  -0.1264   0.03298   0.02153  -0.0755   0.8197   0.2861
  -3.500  -0.0944   0.03258   0.02108  -0.0762   0.8127   0.3031
  -3.250  -0.0543   0.03202   0.02050  -0.0782   0.8085   0.3231
  -3.000  -0.0392   0.03204   0.02053  -0.0762   0.7962   0.3383
  -2.750  -0.0023   0.03154   0.02006  -0.0775   0.7910   0.3602
  -2.500   0.0187   0.03146   0.02006  -0.0764   0.7812   0.3791
  -2.250   0.0489   0.03114   0.01979  -0.0767   0.7738   0.4034
  -2.000   0.0874   0.03057   0.01932  -0.0781   0.7694   0.4322
  -1.750   0.1010   0.03075   0.01961  -0.0758   0.7574   0.4547
  -1.500   0.1352   0.03030   0.01928  -0.0764   0.7518   0.4873
  -1.250   0.1565   0.03028   0.01939  -0.0752   0.7425   0.5193
  -1.000   0.1826   0.03007   0.01934  -0.0745   0.7347   0.5581
  -0.750   0.2172   0.02955   0.01900  -0.0747   0.7302   0.6083
  -0.500   0.2284   0.02988   0.01952  -0.0717   0.7185   0.6529
  -0.250   0.2581   0.02952   0.01935  -0.0707   0.7127   0.7141
   0.000   0.2838   0.02948   0.01948  -0.0693   0.7055   0.7796
   0.250   0.3130   0.02971   0.01983  -0.0688   0.6964   0.8496
   0.500   0.3783   0.02943   0.01950  -0.0745   0.6919   0.9273
   0.750   0.4406   0.02968   0.01964  -0.0812   0.6838   0.9888
   1.000   0.4675   0.02982   0.01963  -0.0817   0.6753   1.0000
   1.250   0.5019   0.02950   0.01912  -0.0825   0.6703   1.0000
   1.500   0.4975   0.03041   0.01993  -0.0779   0.6580   1.0000
   1.750   0.5295   0.03028   0.01965  -0.0784   0.6524   1.0000
   2.000   0.5380   0.03097   0.02026  -0.0757   0.6425   1.0000
   2.250   0.5620   0.03117   0.02035  -0.0750   0.6351   1.0000
   2.500   0.6010   0.03089   0.01994  -0.0764   0.6306   1.0000
   2.750   0.5977   0.03216   0.02118  -0.0722   0.6187   1.0000
   3.000   0.6318   0.03205   0.02097  -0.0729   0.6131   1.0000
   3.250   0.6431   0.03288   0.02176  -0.0707   0.6041   1.0000
   3.500   0.6632   0.03336   0.02219  -0.0696   0.5963   1.0000
   3.750   0.7032   0.03305   0.02178  -0.0710   0.5917   1.0000
   4.000   0.6967   0.03463   0.02338  -0.0666   0.5802   1.0000
   4.250   0.7292   0.03465   0.02334  -0.0670   0.5745   1.0000
   4.500   0.7534   0.03503   0.02368  -0.0665   0.5678   1.0000
   4.750   0.7547   0.03634   0.02501  -0.0632   0.5577   1.0000
   5.000   0.7952   0.03601   0.02463  -0.0645   0.5530   1.0000
   5.250   0.7849   0.03799   0.02665  -0.0601   0.5419   1.0000
   5.500   0.8142   0.03810   0.02673  -0.0600   0.5357   1.0000
   5.750   0.8621   0.03739   0.02597  -0.0621   0.5318   1.0000
   6.000   0.8348   0.04035   0.02902  -0.0562   0.5186   1.0000
   6.250   0.8755   0.03979   0.02842  -0.0572   0.5140   1.0000
   6.500   0.8581   0.04262   0.03133  -0.0529   0.5020   1.0000
   6.750   0.8901   0.04243   0.03114  -0.0529   0.4962   1.0000
   7.000   0.9411   0.04120   0.02986  -0.0547   0.4926   1.0000
   7.250   0.9045   0.04532   0.03410  -0.0492   0.4783   1.0000
   7.500   0.9513   0.04404   0.03280  -0.0501   0.4744   1.0000
   7.750   0.9183   0.04845   0.03732  -0.0459   0.4603   1.0000
   8.000   0.9614   0.04717   0.03602  -0.0462   0.4560   1.0000
   8.250   0.9308   0.05187   0.04082  -0.0429   0.4421   1.0000
   8.500   0.9704   0.05066   0.03961  -0.0427   0.4377   1.0000
   9.000   0.9782   0.05451   0.04359  -0.0398   0.4192   1.0000
   9.250   1.0301   0.05215   0.04121  -0.0400   0.4163   1.0000
   9.500   0.9847   0.05876   0.04794  -0.0373   0.4008   1.0000
   9.750   1.0345   0.05623   0.04543  -0.0370   0.3980   1.0000
  10.000   0.9903   0.06331   0.05263  -0.0352   0.3824   1.0000
  10.250   1.0385   0.06064   0.04996  -0.0345   0.3797   1.0000
  10.500   0.9957   0.06808   0.05751  -0.0335   0.3641   1.0000
  10.750   1.0424   0.06529   0.05475  -0.0325   0.3616   1.0000
  11.000   1.0000   0.07317   0.06273  -0.0322   0.3460   1.0000
  11.500   1.0035   0.07850   0.06819  -0.0311   0.3281   1.0000
  12.000   1.0064   0.08401   0.07382  -0.0304   0.3106   1.0000
  12.500   1.0087   0.08973   0.07966  -0.0300   0.2933   1.0000
  13.000   1.0102   0.09569   0.08574  -0.0299   0.2763   1.0000
  13.500   1.0108   0.10195   0.09212  -0.0303   0.2597   1.0000
  14.000   1.0104   0.10851   0.09880  -0.0310   0.2435   1.0000
  14.500   1.0099   0.11526   0.10567  -0.0321   0.2276   1.0000
  15.000   1.0098   0.12208   0.11259  -0.0336   0.2122   1.0000
  15.500   1.0102   0.12900   0.11960  -0.0355   0.1972   1.0000
  16.000   1.0103   0.13617   0.12688  -0.0378   0.1826   1.0000
  16.500   1.0091   0.14386   0.13465  -0.0407   0.1686   1.0000
  17.000   1.0061   0.15229   0.14315  -0.0444   0.1552   1.0000
  17.500   1.0010   0.16166   0.15259  -0.0488   0.1426   1.0000
  18.000   0.9934   0.17218   0.16318  -0.0543   0.1309   1.0000
  18.500   0.9837   0.18387   0.17491  -0.0608   0.1206   1.0000
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