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FX 83-W-108 (fx83w108-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 83-W-108 (fx83w108-il)
Reynolds number: 50,000
Max Cl/Cd: 34.54 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx83w108-il-50000-n5.txt
Download as CSV file: xf-fx83w108-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 83-W-108                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3685   0.10491   0.09771  -0.0460   1.0000   0.0658
  -9.000  -0.3757   0.10218   0.09508  -0.0452   1.0000   0.0647
  -8.750  -0.3858   0.09956   0.09257  -0.0441   1.0000   0.0638
  -8.500  -0.3985   0.09707   0.09019  -0.0427   1.0000   0.0632
  -8.250  -0.4142   0.09465   0.08789  -0.0411   1.0000   0.0624
  -8.000  -0.4341   0.09217   0.08554  -0.0393   1.0000   0.0616
  -7.500  -0.4963   0.08029   0.07387  -0.0450   1.0000   0.0579
  -7.250  -0.4939   0.07434   0.06785  -0.0505   0.9966   0.0576
  -7.000  -0.4838   0.06531   0.05847  -0.0620   0.9888   0.0579
  -6.750  -0.4652   0.06288   0.05608  -0.0635   0.9836   0.0598
  -6.500  -0.4465   0.05744   0.05034  -0.0697   0.9779   0.0609
  -6.250  -0.4264   0.05209   0.04454  -0.0751   0.9719   0.0620
  -6.000  -0.4001   0.04699   0.03884  -0.0802   0.9673   0.0630
  -5.750  -0.3756   0.04328   0.03459  -0.0830   0.9621   0.0647
  -5.500  -0.3452   0.04002   0.03062  -0.0861   0.9579   0.0686
  -5.250  -0.3150   0.03747   0.02756  -0.0882   0.9542   0.0716
  -5.000  -0.2895   0.03577   0.02564  -0.0888   0.9492   0.0744
  -4.750  -0.2592   0.03428   0.02384  -0.0901   0.9451   0.0796
  -4.500  -0.2262   0.03282   0.02203  -0.0916   0.9419   0.0856
  -4.250  -0.2026   0.03180   0.02094  -0.0914   0.9367   0.0905
  -4.000  -0.1735   0.03085   0.01973  -0.0920   0.9322   0.0994
  -3.750  -0.1419   0.02997   0.01878  -0.0931   0.9286   0.1099
  -3.500  -0.1145   0.02922   0.01799  -0.0935   0.9241   0.1234
  -3.250  -0.0880   0.02853   0.01727  -0.0938   0.9190   0.1436
  -3.000  -0.0556   0.02776   0.01670  -0.0954   0.9150   0.1843
  -2.750  -0.0209   0.02718   0.01656  -0.0973   0.9119   0.2725
  -2.500  -0.0005   0.02725   0.01674  -0.0963   0.9054   0.3448
  -2.250   0.0277   0.02740   0.01689  -0.0965   0.9006   0.4036
  -2.000   0.0591   0.02756   0.01707  -0.0972   0.8969   0.4585
  -1.750   0.0777   0.02773   0.01727  -0.0956   0.8904   0.4966
  -1.500   0.1052   0.02781   0.01730  -0.0956   0.8854   0.5330
  -1.250   0.1374   0.02783   0.01728  -0.0964   0.8819   0.5648
  -1.000   0.1578   0.02794   0.01740  -0.0952   0.8755   0.5900
  -0.750   0.1851   0.02799   0.01745  -0.0953   0.8704   0.6188
  -0.500   0.2173   0.02796   0.01745  -0.0961   0.8667   0.6520
  -0.250   0.2371   0.02807   0.01764  -0.0948   0.8603   0.6868
   0.000   0.2623   0.02804   0.01775  -0.0943   0.8550   0.7353
   0.250   0.2954   0.02776   0.01773  -0.0949   0.8514   0.8311
   0.500   0.3215   0.02796   0.01785  -0.0955   0.8439   1.0000
   0.750   0.3530   0.02836   0.01804  -0.0968   0.8386   1.0000
   1.000   0.3903   0.02867   0.01816  -0.0988   0.8348   1.0000
   1.250   0.4067   0.02929   0.01866  -0.0975   0.8263   1.0000
   1.500   0.4396   0.02965   0.01890  -0.0987   0.8214   1.0000
   1.750   0.4623   0.03021   0.01938  -0.0984   0.8146   1.0000
   2.000   0.4885   0.03069   0.01979  -0.0985   0.8081   1.0000
   2.250   0.5243   0.03098   0.02004  -0.1000   0.8041   1.0000
   2.500   0.5383   0.03175   0.02078  -0.0983   0.7946   1.0000
   2.750   0.5718   0.03206   0.02108  -0.0994   0.7897   1.0000
   3.000   0.5893   0.03276   0.02178  -0.0982   0.7807   1.0000
   3.250   0.6212   0.03307   0.02213  -0.0989   0.7749   1.0000
   3.500   0.6402   0.03374   0.02282  -0.0978   0.7657   1.0000
   3.750   0.6722   0.03400   0.02313  -0.0984   0.7595   1.0000
   4.000   0.6904   0.03467   0.02387  -0.0973   0.7495   1.0000
   4.250   0.7257   0.03473   0.02402  -0.0981   0.7434   1.0000
   4.500   0.7428   0.03537   0.02474  -0.0966   0.7319   1.0000
   4.750   0.7843   0.03500   0.02452  -0.0979   0.7264   1.0000
   5.000   0.8014   0.03553   0.02515  -0.0962   0.7135   1.0000
   5.250   0.8227   0.03582   0.02556  -0.0950   0.7010   1.0000
   5.500   0.8492   0.03574   0.02562  -0.0940   0.6889   1.0000
   5.750   0.8854   0.03494   0.02503  -0.0938   0.6779   1.0000
   6.000   0.9144   0.03431   0.02457  -0.0925   0.6629   1.0000
   6.250   0.9348   0.03398   0.02439  -0.0903   0.6439   1.0000
   6.500   0.9621   0.03304   0.02365  -0.0883   0.6237   1.0000
   6.750   0.9861   0.03229   0.02306  -0.0861   0.6011   1.0000
   7.000   1.0068   0.03175   0.02267  -0.0836   0.5745   1.0000
   7.250   1.0224   0.03158   0.02262  -0.0807   0.5407   1.0000
   7.500   1.0417   0.03120   0.02228  -0.0779   0.4950   1.0000
   7.750   1.0642   0.03081   0.02163  -0.0753   0.4266   1.0000
   8.000   1.0754   0.03154   0.02181  -0.0720   0.3475   1.0000
   8.250   1.0756   0.03331   0.02307  -0.0686   0.2862   1.0000
   8.500   1.0746   0.03538   0.02477  -0.0656   0.2398   1.0000
   8.750   1.0752   0.03751   0.02660  -0.0630   0.2036   1.0000
   9.000   1.0778   0.03962   0.02849  -0.0609   0.1770   1.0000
   9.250   1.0844   0.04153   0.03032  -0.0590   0.1560   1.0000
   9.500   1.0927   0.04340   0.03212  -0.0573   0.1400   1.0000
   9.750   1.1028   0.04519   0.03388  -0.0558   0.1265   1.0000
  10.000   1.1154   0.04689   0.03555  -0.0544   0.1155   1.0000
  10.250   1.1320   0.04844   0.03711  -0.0531   0.1064   1.0000
  10.500   1.1532   0.04984   0.03868  -0.0521   0.0974   1.0000
  10.750   1.1763   0.05129   0.04008  -0.0514   0.0904   1.0000
  11.000   1.2014   0.05289   0.04195  -0.0507   0.0838   1.0000
  11.250   1.2244   0.05461   0.04354  -0.0502   0.0783   1.0000
  11.500   1.2434   0.05684   0.04626  -0.0493   0.0740   1.0000
  11.750   1.2595   0.05916   0.04882  -0.0484   0.0704   1.0000
  12.000   1.2732   0.06135   0.05106  -0.0476   0.0673   1.0000
  12.250   1.2824   0.06423   0.05419  -0.0465   0.0649   1.0000
  12.500   1.2818   0.06762   0.05801  -0.0450   0.0630   1.0000
  12.750   1.2796   0.07126   0.06202  -0.0436   0.0618   1.0000
  13.000   1.2731   0.07521   0.06630  -0.0425   0.0608   1.0000
  13.250   1.2628   0.07941   0.07081  -0.0416   0.0600   1.0000
  13.500   1.2491   0.08399   0.07568  -0.0412   0.0594   1.0000
  13.750   1.2323   0.08896   0.08092  -0.0413   0.0588   1.0000
  14.000   1.2107   0.09477   0.08700  -0.0422   0.0586   1.0000
  14.250   1.1822   0.10192   0.09442  -0.0445   0.0588   1.0000
  14.500   1.1447   0.11129   0.10407  -0.0489   0.0596   1.0000
  14.750   1.1003   0.12373   0.11671  -0.0564   0.0607   1.0000
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