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FX 83-W-108 (fx83w108-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 83-W-108 (fx83w108-il)
Reynolds number: 100,000
Max Cl/Cd: 60.98 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx83w108-il-100000.txt
Download as CSV file: xf-fx83w108-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4230   0.10271   0.09824  -0.0286   1.0000   0.1259
  -7.750  -0.4569   0.10258   0.09823  -0.0266   1.0000   0.1269
  -7.500  -0.4965   0.10206   0.09785  -0.0268   1.0000   0.1275
  -7.250  -0.4947   0.09834   0.09418  -0.0238   1.0000   0.1288
  -7.000  -0.4684   0.09581   0.09160  -0.0186   1.0000   0.1333
  -6.750  -0.4805   0.09429   0.09014  -0.0165   1.0000   0.1365
  -6.500  -0.5007   0.08862   0.08452  -0.0313   0.9964   0.1435
  -6.250  -0.4778   0.08735   0.08326  -0.0229   0.9949   0.1473
  -6.000  -0.4619   0.08141   0.07726  -0.0352   0.9882   0.1598
  -5.750  -0.4443   0.07936   0.07522  -0.0326   0.9841   0.1641
  -5.500  -0.4100   0.05347   0.04812  -0.0716   0.9770   0.1122
  -5.250  -0.3760   0.04090   0.03433  -0.0792   0.9747   0.0821
  -5.000  -0.3428   0.03697   0.02985  -0.0823   0.9712   0.0806
  -4.750  -0.3045   0.03464   0.02673  -0.0853   0.9679   0.0834
  -4.500  -0.2781   0.03227   0.02392  -0.0860   0.9636   0.0847
  -4.250  -0.2474   0.03032   0.02178  -0.0872   0.9599   0.0875
  -4.000  -0.2114   0.02933   0.02058  -0.0891   0.9564   0.0944
  -3.750  -0.1836   0.02821   0.01916  -0.0893   0.9519   0.0995
  -3.500  -0.1557   0.02736   0.01834  -0.0897   0.9475   0.1075
  -3.250  -0.1216   0.02655   0.01751  -0.0911   0.9439   0.1184
  -3.000  -0.0904   0.02593   0.01693  -0.0920   0.9399   0.1334
  -2.750  -0.0671   0.02540   0.01649  -0.0915   0.9346   0.1556
  -2.500  -0.0359   0.02457   0.01613  -0.0926   0.9306   0.2230
  -2.250   0.0003   0.02455   0.01671  -0.0944   0.9272   0.3824
  -2.000   0.0153   0.02487   0.01703  -0.0923   0.9204   0.4272
  -1.750   0.0444   0.02521   0.01736  -0.0927   0.9156   0.4696
  -1.500   0.0810   0.02552   0.01771  -0.0943   0.9120   0.5086
  -1.250   0.0933   0.02576   0.01798  -0.0918   0.9050   0.5362
  -1.000   0.1216   0.02596   0.01827  -0.0919   0.9000   0.5722
  -0.750   0.1592   0.02614   0.01851  -0.0936   0.8965   0.6092
  -0.500   0.1692   0.02635   0.01878  -0.0908   0.8887   0.6332
  -0.250   0.2020   0.02645   0.01894  -0.0918   0.8840   0.6666
   0.000   0.2363   0.02658   0.01915  -0.0930   0.8796   0.7060
   0.250   0.2542   0.02672   0.01945  -0.0917   0.8726   0.7492
   0.500   0.3030   0.02619   0.01942  -0.0956   0.8687   1.0000
   0.750   0.3448   0.02666   0.01961  -0.0992   0.8643   1.0000
   1.000   0.3628   0.02726   0.02005  -0.0985   0.8561   1.0000
   1.250   0.4030   0.02761   0.02027  -0.1009   0.8517   1.0000
   1.500   0.4197   0.02829   0.02086  -0.0998   0.8436   1.0000
   1.750   0.4530   0.02870   0.02119  -0.1010   0.8379   1.0000
   2.000   0.4823   0.02919   0.02163  -0.1016   0.8315   1.0000
   2.250   0.5065   0.02971   0.02211  -0.1014   0.8236   1.0000
   2.500   0.5507   0.02986   0.02223  -0.1041   0.8197   1.0000
   2.750   0.5610   0.03068   0.02304  -0.1018   0.8089   1.0000
   3.000   0.6053   0.03072   0.02308  -0.1043   0.8046   1.0000
   3.250   0.6183   0.03147   0.02385  -0.1024   0.7934   1.0000
   3.500   0.6660   0.03124   0.02366  -0.1050   0.7890   1.0000
   3.750   0.6809   0.03190   0.02434  -0.1032   0.7771   1.0000
   4.000   0.7346   0.03122   0.02376  -0.1064   0.7732   1.0000
   4.250   0.7513   0.03170   0.02428  -0.1046   0.7606   1.0000
   4.500   0.8148   0.03015   0.02287  -0.1084   0.7569   1.0000
   4.750   0.8394   0.03000   0.02280  -0.1072   0.7442   1.0000
   5.000   0.8772   0.02903   0.02194  -0.1072   0.7325   1.0000
   5.250   0.9690   0.02508   0.01820  -0.1135   0.7270   1.0000
   5.500   1.0026   0.02410   0.01735  -0.1128   0.7134   1.0000
   5.750   1.0429   0.02265   0.01603  -0.1128   0.6984   1.0000
   6.000   1.0844   0.02113   0.01463  -0.1130   0.6810   1.0000
   6.250   1.1047   0.02056   0.01417  -0.1103   0.6587   1.0000
   6.500   1.1299   0.01969   0.01338  -0.1081   0.6305   1.0000
   6.750   1.1475   0.01921   0.01291  -0.1048   0.5919   1.0000
   7.000   1.1611   0.01904   0.01262  -0.1009   0.5366   1.0000
   7.250   1.1668   0.01948   0.01252  -0.0959   0.4389   1.0000
   7.500   1.1549   0.02102   0.01325  -0.0888   0.3348   1.0000
   7.750   1.1422   0.02303   0.01458  -0.0825   0.2570   1.0000
   8.000   1.1359   0.02507   0.01608  -0.0777   0.2058   1.0000
   8.250   1.1376   0.02690   0.01761  -0.0741   0.1730   1.0000
   8.500   1.1446   0.02859   0.01906  -0.0713   0.1504   1.0000
   8.750   1.1572   0.03028   0.02049  -0.0693   0.1335   1.0000
   9.000   1.1764   0.03188   0.02197  -0.0682   0.1195   1.0000
   9.250   1.1955   0.03321   0.02336  -0.0670   0.1089   1.0000
   9.500   1.2233   0.03493   0.02510  -0.0669   0.0995   1.0000
   9.750   1.2603   0.03707   0.02707  -0.0685   0.0908   1.0000
  10.000   1.2844   0.03875   0.02903  -0.0678   0.0854   1.0000
  10.250   1.3226   0.04118   0.03143  -0.0698   0.0800   1.0000
  10.500   1.3521   0.04415   0.03472  -0.0704   0.0763   1.0000
  10.750   1.3652   0.04620   0.03711  -0.0683   0.0734   1.0000
  11.000   1.3821   0.04881   0.04000  -0.0671   0.0712   1.0000
  11.250   1.3987   0.05167   0.04310  -0.0660   0.0696   1.0000
  11.500   1.4104   0.05468   0.04636  -0.0643   0.0683   1.0000
  11.750   1.4210   0.05840   0.05028  -0.0630   0.0671   1.0000
  12.000   1.4214   0.06327   0.05546  -0.0609   0.0660   1.0000
  12.250   1.4058   0.06556   0.05809  -0.0559   0.0656   1.0000
  12.500   1.3902   0.06858   0.06143  -0.0518   0.0654   1.0000
  12.750   1.3716   0.07177   0.06493  -0.0480   0.0652   1.0000
  13.000   1.3549   0.07584   0.06927  -0.0453   0.0654   1.0000
  13.250   1.3373   0.08027   0.07394  -0.0432   0.0656   1.0000
  13.500   1.3195   0.08521   0.07910  -0.0417   0.0659   1.0000
  13.750   1.3021   0.09029   0.08441  -0.0407   0.0663   1.0000
  14.000   1.2693   0.09418   0.08859  -0.0400   0.0669   1.0000
  14.250   1.1301   0.11328   0.10837  -0.0495   0.0740   1.0000
  14.500   1.0958   0.12431   0.11948  -0.0556   0.0762   1.0000
  14.750   1.0811   0.13292   0.12812  -0.0595   0.0776   1.0000
  15.000   1.0805   0.13942   0.13463  -0.0612   0.0784   1.0000
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