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NACA 23018 (naca23018-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 23018 (naca23018-il)
Reynolds number: 50,000
Max Cl/Cd: 21.08 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca23018-il-50000.txt
Download as CSV file: xf-naca23018-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 23018                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.7369   0.07551   0.06719  -0.0469   1.0000   0.1785
 -11.500  -0.7734   0.06990   0.06147  -0.0457   1.0000   0.1774
 -11.250  -0.8107   0.06557   0.05703  -0.0422   1.0000   0.1764
 -11.000  -0.8415   0.06179   0.05306  -0.0379   1.0000   0.1760
 -10.750  -0.8654   0.05835   0.04940  -0.0335   1.0000   0.1761
 -10.500  -0.8836   0.05525   0.04603  -0.0291   1.0000   0.1766
 -10.250  -0.8971   0.05242   0.04288  -0.0246   1.0000   0.1776
 -10.000  -0.9078   0.04985   0.03993  -0.0200   1.0000   0.1789
  -9.750  -0.8911   0.04761   0.03780  -0.0187   1.0000   0.1829
  -9.500  -0.8803   0.04573   0.03586  -0.0164   1.0000   0.1869
  -9.250  -0.8761   0.04370   0.03360  -0.0132   1.0000   0.1906
  -9.000  -0.8748   0.04176   0.03127  -0.0094   1.0000   0.1944
  -8.750  -0.8538   0.04010   0.02981  -0.0084   1.0000   0.2007
  -8.500  -0.8426   0.03855   0.02812  -0.0058   1.0000   0.2074
  -8.250  -0.8267   0.03699   0.02657  -0.0039   1.0000   0.2148
  -8.000  -0.8129   0.03571   0.02525  -0.0016   1.0000   0.2246
  -7.750  -0.7954   0.03444   0.02414   0.0001   1.0000   0.2361
  -7.500  -0.7807   0.03323   0.02302   0.0023   1.0000   0.2505
  -7.250  -0.7672   0.03213   0.02209   0.0048   1.0000   0.2694
  -7.000  -0.7564   0.03108   0.02124   0.0077   1.0000   0.2949
  -6.750  -0.7478   0.03017   0.02071   0.0111   1.0000   0.3300
  -6.500  -0.7426   0.02942   0.02038   0.0152   1.0000   0.3791
  -6.250  -0.7386   0.02909   0.02038   0.0199   1.0000   0.4353
  -6.000  -0.7274   0.02937   0.02100   0.0240   1.0000   0.4824
  -5.750  -0.7163   0.02966   0.02139   0.0279   1.0000   0.5210
  -5.500  -0.7009   0.03023   0.02210   0.0313   1.0000   0.5531
  -5.250  -0.6886   0.03055   0.02246   0.0348   1.0000   0.5828
  -5.000  -0.6707   0.03142   0.02345   0.0382   1.0000   0.6095
  -4.750  -0.6550   0.03212   0.02421   0.0416   1.0000   0.6352
  -4.500  -0.6404   0.03265   0.02478   0.0449   1.0000   0.6592
  -4.250  -0.6259   0.03312   0.02525   0.0479   1.0000   0.6814
  -4.000  -0.6115   0.03364   0.02578   0.0510   1.0000   0.7037
  -3.750  -0.5982   0.03421   0.02636   0.0542   1.0000   0.7271
  -3.500  -0.5856   0.03472   0.02686   0.0573   1.0000   0.7505
  -3.250  -0.5687   0.03540   0.02755   0.0598   1.0000   0.7719
  -3.000  -0.5476   0.03603   0.02815   0.0611   1.0000   0.7902
  -2.750  -0.4894   0.03727   0.02927   0.0556   0.9904   0.8088
  -2.500  -0.4061   0.03879   0.03064   0.0456   0.9736   0.8269
  -2.250  -0.3179   0.04004   0.03173   0.0346   0.9564   0.8442
  -2.000  -0.2261   0.04092   0.03246   0.0227   0.9389   0.8612
  -1.750  -0.1298   0.04139   0.03280   0.0099   0.9208   0.8784
  -1.500  -0.0381   0.04141   0.03271  -0.0021   0.9022   0.8957
  -1.250   0.0845   0.04084   0.03205  -0.0189   0.8832   0.9099
  -1.000   0.1917   0.03956   0.03072  -0.0330   0.8642   0.9256
  -0.750   0.2788   0.03804   0.02915  -0.0433   0.8436   0.9414
  -0.500   0.3525   0.03645   0.02753  -0.0510   0.8215   0.9573
  -0.250   0.4169   0.03488   0.02590  -0.0570   0.7983   0.9731
   0.000   0.4768   0.03329   0.02423  -0.0623   0.7743   0.9888
   0.250   0.5224   0.03220   0.02308  -0.0656   0.7483   1.0000
   0.500   0.5367   0.03188   0.02267  -0.0637   0.7264   1.0000
   0.750   0.5512   0.03162   0.02233  -0.0617   0.7054   1.0000
   1.000   0.5659   0.03141   0.02202  -0.0597   0.6848   1.0000
   1.250   0.5812   0.03124   0.02174  -0.0578   0.6651   1.0000
   1.500   0.5971   0.03113   0.02151  -0.0559   0.6462   1.0000
   1.750   0.6114   0.03126   0.02157  -0.0541   0.6266   1.0000
   2.000   0.6256   0.03148   0.02173  -0.0523   0.6076   1.0000
   2.250   0.6397   0.03181   0.02202  -0.0505   0.5897   1.0000
   2.500   0.6545   0.03218   0.02233  -0.0488   0.5732   1.0000
   2.750   0.6721   0.03237   0.02240  -0.0471   0.5588   1.0000
   3.000   0.6877   0.03276   0.02273  -0.0453   0.5440   1.0000
   3.250   0.6984   0.03363   0.02364  -0.0434   0.5295   1.0000
   3.500   0.7166   0.03399   0.02388  -0.0417   0.5180   1.0000
   3.750   0.7262   0.03492   0.02487  -0.0395   0.5050   1.0000
   4.000   0.7381   0.03583   0.02577  -0.0374   0.4943   1.0000
   4.250   0.7499   0.03669   0.02663  -0.0353   0.4836   1.0000
   4.500   0.7589   0.03782   0.02778  -0.0329   0.4741   1.0000
   4.750   0.7653   0.03905   0.02906  -0.0302   0.4643   1.0000
   5.000   0.7828   0.03976   0.02969  -0.0285   0.4564   1.0000
   5.250   0.7672   0.04233   0.03246  -0.0239   0.4478   1.0000
   5.500   0.7933   0.04252   0.03255  -0.0229   0.4399   1.0000
   5.750   0.7741   0.04539   0.03556  -0.0179   0.4330   1.0000
   6.000   0.7413   0.04897   0.03928  -0.0121   0.4267   1.0000
   6.250   0.7983   0.04764   0.03777  -0.0136   0.4187   1.0000
   6.500   0.7326   0.05335   0.04365  -0.0054   0.4144   1.0000
   6.750   0.5659   0.06730   0.05753   0.0041   0.4146   1.0000
   7.000   0.5039   0.07622   0.06638   0.0040   0.4135   1.0000
   7.250   0.4796   0.08189   0.07203   0.0036   0.4131   1.0000
   7.500   0.4653   0.08676   0.07689   0.0030   0.4130   1.0000
   7.750   0.4602   0.09119   0.08132   0.0024   0.4144   1.0000
   8.000   0.4637   0.09531   0.08546   0.0016   0.4161   1.0000
   8.250   0.4776   0.09925   0.08945   0.0007   0.4177   1.0000
   8.500   0.3584   0.11120   0.10144  -0.0059   0.5124   1.0000
   8.750   0.3939   0.11523   0.10550  -0.0071   0.5010   1.0000
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