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A18 (smoothed) (a18sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: A18 (smoothed) (a18sm-il)
Reynolds number: 100,000
Max Cl/Cd: 65.27 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-a18sm-il-100000.txt
Download as CSV file: xf-a18sm-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: A18 (smoothed)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3957   0.10254   0.09748  -0.0273   1.0000   0.0899
  -8.000  -0.4126   0.10196   0.09705  -0.0287   1.0000   0.0914
  -7.750  -0.4240   0.10071   0.09593  -0.0346   1.0000   0.0920
  -7.500  -0.4117   0.09485   0.09007  -0.0285   1.0000   0.0936
  -7.250  -0.4018   0.09153   0.08675  -0.0258   1.0000   0.0962
  -7.000  -0.3995   0.08890   0.08418  -0.0255   1.0000   0.0992
  -6.750  -0.4005   0.08636   0.08171  -0.0275   1.0000   0.1031
  -6.500  -0.3989   0.08273   0.07812  -0.0408   1.0000   0.1063
  -6.250  -0.3953   0.07935   0.07480  -0.0337   1.0000   0.1078
  -6.000  -0.3891   0.07666   0.07214  -0.0311   1.0000   0.1106
  -5.750  -0.3745   0.07308   0.06852  -0.0393   1.0000   0.1188
  -5.500  -0.3641   0.06858   0.06401  -0.0420   1.0000   0.1215
  -5.250  -0.3333   0.06448   0.05962  -0.0536   1.0000   0.1341
  -5.000  -0.3355   0.06177   0.05714  -0.0455   1.0000   0.1362
  -4.750  -0.3236   0.05943   0.05480  -0.0442   1.0000   0.1438
  -4.500  -0.2302   0.03601   0.02972  -0.0755   1.0000   0.0799
  -4.250  -0.1932   0.03090   0.02379  -0.0793   1.0000   0.0779
  -4.000  -0.1697   0.02924   0.02219  -0.0797   1.0000   0.0847
  -3.750  -0.1334   0.02577   0.01796  -0.0822   1.0000   0.0879
  -3.500  -0.1011   0.02369   0.01538  -0.0835   1.0000   0.0957
  -3.250  -0.0703   0.02246   0.01368  -0.0842   1.0000   0.1055
  -3.000  -0.0413   0.02141   0.01253  -0.0847   1.0000   0.1182
  -2.750  -0.0125   0.02062   0.01155  -0.0851   1.0000   0.1342
  -2.500   0.0148   0.01999   0.01102  -0.0855   1.0000   0.1534
  -2.250   0.0425   0.01955   0.01046  -0.0858   1.0000   0.1771
  -2.000   0.0688   0.01925   0.01023  -0.0860   1.0000   0.2048
  -1.750   0.0953   0.01900   0.01005  -0.0863   1.0000   0.2341
  -1.500   0.1209   0.01884   0.01005  -0.0865   1.0000   0.2668
  -1.250   0.1467   0.01879   0.01013  -0.0868   1.0000   0.3056
  -1.000   0.1727   0.01875   0.01027  -0.0872   1.0000   0.3519
  -0.750   0.1994   0.01870   0.01050  -0.0878   1.0000   0.4142
  -0.500   0.2383   0.01823   0.01063  -0.0904   0.9971   0.5537
  -0.250   0.2743   0.01728   0.01043  -0.0918   0.9874   1.0000
   0.000   0.3203   0.01759   0.01049  -0.0959   0.9783   1.0000
   0.250   0.3689   0.01787   0.01058  -0.1004   0.9708   1.0000
   0.500   0.4100   0.01806   0.01065  -0.1035   0.9595   1.0000
   0.750   0.4505   0.01823   0.01074  -0.1063   0.9485   1.0000
   1.000   0.4923   0.01834   0.01079  -0.1093   0.9382   1.0000
   1.250   0.5385   0.01832   0.01076  -0.1129   0.9299   1.0000
   1.500   0.5760   0.01835   0.01079  -0.1149   0.9180   1.0000
   1.750   0.6145   0.01833   0.01079  -0.1169   0.9067   1.0000
   2.000   0.6564   0.01820   0.01072  -0.1194   0.8972   1.0000
   2.250   0.6987   0.01794   0.01052  -0.1218   0.8883   1.0000
   2.500   0.7330   0.01785   0.01049  -0.1226   0.8758   1.0000
   2.750   0.7671   0.01771   0.01046  -0.1232   0.8633   1.0000
   3.000   0.8027   0.01723   0.01006  -0.1234   0.8486   1.0000
   3.250   0.8386   0.01647   0.00935  -0.1230   0.8312   1.0000
   3.500   0.8655   0.01622   0.00916  -0.1216   0.8097   1.0000
   3.750   0.8949   0.01602   0.00907  -0.1207   0.7914   1.0000
   4.000   0.9227   0.01592   0.00903  -0.1196   0.7717   1.0000
   4.250   0.9488   0.01589   0.00907  -0.1183   0.7492   1.0000
   4.500   0.9742   0.01589   0.00911  -0.1167   0.7241   1.0000
   4.750   0.9988   0.01588   0.00917  -0.1149   0.6943   1.0000
   5.000   1.0219   0.01589   0.00916  -0.1128   0.6575   1.0000
   5.250   1.0430   0.01601   0.00923  -0.1104   0.6109   1.0000
   5.500   1.0626   0.01628   0.00939  -0.1078   0.5531   1.0000
   5.750   1.0790   0.01685   0.00970  -0.1048   0.4666   1.0000
   6.000   1.0856   0.01852   0.01036  -0.1008   0.2956   1.0000
   6.250   1.0886   0.02140   0.01212  -0.0970   0.1674   1.0000
   6.500   1.0985   0.02374   0.01399  -0.0939   0.1158   1.0000
   6.750   1.1131   0.02560   0.01565  -0.0916   0.0933   1.0000
   7.000   1.1314   0.02754   0.01749  -0.0898   0.0809   1.0000
   7.250   1.1520   0.02949   0.01933  -0.0886   0.0708   1.0000
   7.500   1.1765   0.03139   0.02148  -0.0875   0.0645   1.0000
   7.750   1.2021   0.03371   0.02383  -0.0868   0.0603   1.0000
   8.000   1.2295   0.03737   0.02760  -0.0865   0.0574   1.0000
   8.250   1.2493   0.03946   0.03020  -0.0847   0.0543   1.0000
   8.500   1.2683   0.04238   0.03355  -0.0829   0.0523   1.0000
   8.750   1.2838   0.04605   0.03772  -0.0808   0.0520   1.0000
   9.000   1.2943   0.05029   0.04251  -0.0781   0.0524   1.0000
   9.250   1.2994   0.05496   0.04773  -0.0750   0.0536   1.0000
   9.500   1.3009   0.05989   0.05314  -0.0720   0.0550   1.0000
   9.750   1.2997   0.06487   0.05847  -0.0692   0.0562   1.0000
  10.000   1.2959   0.06999   0.06387  -0.0665   0.0569   1.0000
  10.250   1.3003   0.07679   0.07080  -0.0655   0.0581   1.0000
  10.500   1.2344   0.08106   0.07599  -0.0571   0.0670   1.0000
  10.750   1.2292   0.08674   0.08171  -0.0559   0.0691   1.0000
  11.000   1.0770   0.08010   0.07546  -0.0396   0.0629   1.0000
  11.250   1.0405   0.08618   0.08170  -0.0400   0.0631   1.0000
  11.500   1.0018   0.09325   0.08892  -0.0422   0.0634   1.0000
  11.750   0.9584   0.10208   0.09786  -0.0467   0.0641   1.0000
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