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FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 84-W-097 (fx84w097-il)
Reynolds number: 200,000
Max Cl/Cd: 76.9 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx84w097-il-200000.txt
Download as CSV file: xf-fx84w097-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 84-W-097                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3487   0.08832   0.08522  -0.0253   1.0000   0.0515
  -9.000  -0.3413   0.08489   0.08181  -0.0257   1.0000   0.0528
  -8.750  -0.4383   0.08809   0.08484  -0.0300   1.0000   0.0505
  -8.500  -0.4276   0.08527   0.08203  -0.0291   1.0000   0.0515
  -8.250  -0.4203   0.08237   0.07916  -0.0295   1.0000   0.0528
  -8.000  -0.4179   0.07901   0.07585  -0.0313   1.0000   0.0540
  -7.750  -0.4195   0.07544   0.07235  -0.0339   1.0000   0.0552
  -7.500  -0.4208   0.07116   0.06811  -0.0385   1.0000   0.0567
  -7.250  -0.4259   0.06719   0.06418  -0.0417   1.0000   0.0581
  -7.000  -0.4305   0.06137   0.05786  -0.0524   0.9897   0.0617
  -6.750  -0.4106   0.05357   0.05010  -0.0570   0.9842   0.0635
  -6.500  -0.3822   0.05033   0.04685  -0.0599   0.9776   0.0655
  -6.250  -0.3510   0.04614   0.04245  -0.0647   0.9710   0.0699
  -6.000  -0.3318   0.03343   0.02853  -0.0694   0.9585   0.0516
  -5.750  -0.3074   0.02844   0.02301  -0.0699   0.9484   0.0449
  -5.500  -0.2832   0.02427   0.01816  -0.0697   0.9392   0.0432
  -5.250  -0.2579   0.02194   0.01537  -0.0691   0.9301   0.0441
  -5.000  -0.2337   0.02070   0.01381  -0.0682   0.9198   0.0470
  -4.750  -0.2087   0.01983   0.01259  -0.0671   0.9108   0.0492
  -4.500  -0.1859   0.01770   0.01027  -0.0661   0.9020   0.0519
  -4.250  -0.1619   0.01696   0.00946  -0.0652   0.8925   0.0561
  -4.000  -0.1373   0.01648   0.00880  -0.0640   0.8846   0.0613
  -3.750  -0.1139   0.01532   0.00766  -0.0631   0.8752   0.0671
  -3.500  -0.0889   0.01494   0.00715  -0.0622   0.8670   0.0751
  -3.250  -0.0653   0.01419   0.00645  -0.0612   0.8589   0.0869
  -3.000  -0.0405   0.01366   0.00592  -0.0605   0.8503   0.1032
  -2.750  -0.0165   0.01307   0.00543  -0.0596   0.8431   0.1306
  -2.500   0.0080   0.01245   0.00508  -0.0592   0.8342   0.1834
  -2.250   0.0308   0.01168   0.00478  -0.0583   0.8277   0.3013
  -2.000   0.0499   0.01057   0.00470  -0.0570   0.8186   0.5570
  -1.750   0.0653   0.00994   0.00483  -0.0533   0.8120   0.7829
  -1.500   0.0869   0.00987   0.00491  -0.0506   0.8035   0.8828
  -1.250   0.1208   0.00987   0.00480  -0.0506   0.7975   0.9397
  -1.000   0.1750   0.00986   0.00465  -0.0554   0.7897   0.9742
  -0.750   0.2391   0.00975   0.00432  -0.0625   0.7841   0.9963
  -0.500   0.2692   0.00974   0.00422  -0.0633   0.7748   1.0000
  -0.250   0.2912   0.00976   0.00412  -0.0622   0.7673   1.0000
   0.000   0.3137   0.00979   0.00407  -0.0613   0.7585   1.0000
   0.250   0.3366   0.00985   0.00404  -0.0604   0.7506   1.0000
   0.500   0.3598   0.00990   0.00400  -0.0595   0.7427   1.0000
   0.750   0.3834   0.00998   0.00402  -0.0587   0.7344   1.0000
   1.000   0.4073   0.01004   0.00399  -0.0579   0.7271   1.0000
   1.250   0.4315   0.01015   0.00406  -0.0572   0.7184   1.0000
   1.500   0.4561   0.01022   0.00403  -0.0564   0.7115   1.0000
   1.750   0.4808   0.01033   0.00414  -0.0559   0.7020   1.0000
   2.000   0.5061   0.01042   0.00417  -0.0553   0.6944   1.0000
   2.250   0.5315   0.01051   0.00424  -0.0548   0.6854   1.0000
   2.500   0.5572   0.01063   0.00434  -0.0543   0.6768   1.0000
   2.750   0.5833   0.01072   0.00439  -0.0538   0.6688   1.0000
   3.000   0.6093   0.01085   0.00454  -0.0535   0.6593   1.0000
   3.250   0.6356   0.01096   0.00462  -0.0531   0.6511   1.0000
   3.500   0.6618   0.01106   0.00474  -0.0527   0.6412   1.0000
   3.750   0.6880   0.01117   0.00487  -0.0523   0.6305   1.0000
   4.000   0.7144   0.01129   0.00498  -0.0519   0.6207   1.0000
   4.250   0.7409   0.01140   0.00509  -0.0516   0.6109   1.0000
   4.500   0.7671   0.01153   0.00530  -0.0512   0.5994   1.0000
   4.750   0.7933   0.01166   0.00547  -0.0508   0.5879   1.0000
   5.000   0.8194   0.01176   0.00559  -0.0504   0.5747   1.0000
   5.250   0.8446   0.01176   0.00559  -0.0497   0.5556   1.0000
   5.500   0.8695   0.01181   0.00565  -0.0489   0.5341   1.0000
   5.750   0.8945   0.01192   0.00578  -0.0483   0.5128   1.0000
   6.000   0.9192   0.01208   0.00596  -0.0477   0.4901   1.0000
   6.250   0.9434   0.01229   0.00616  -0.0470   0.4639   1.0000
   6.500   0.9666   0.01257   0.00643  -0.0462   0.4298   1.0000
   6.750   0.9881   0.01302   0.00676  -0.0453   0.3838   1.0000
   7.000   1.0061   0.01380   0.00725  -0.0439   0.3139   1.0000
   7.250   1.0151   0.01550   0.00825  -0.0419   0.1956   1.0000
   7.500   1.0186   0.01789   0.00985  -0.0393   0.0914   1.0000
   7.750   1.0297   0.01946   0.01125  -0.0373   0.0663   1.0000
   8.000   1.0425   0.02075   0.01257  -0.0354   0.0552   1.0000
   8.250   1.0522   0.02224   0.01408  -0.0332   0.0491   1.0000
   8.500   1.0653   0.02338   0.01525  -0.0315   0.0436   1.0000
   8.750   1.0720   0.02516   0.01702  -0.0290   0.0400   1.0000
   9.000   1.0857   0.02631   0.01828  -0.0271   0.0376   1.0000
   9.250   1.0996   0.02767   0.01970  -0.0254   0.0352   1.0000
   9.500   1.1151   0.02919   0.02126  -0.0241   0.0333   1.0000
   9.750   1.1474   0.03277   0.02484  -0.0251   0.0309   1.0000
  10.000   1.1608   0.03371   0.02600  -0.0233   0.0298   1.0000
  10.250   1.1782   0.03543   0.02794  -0.0221   0.0285   1.0000
  10.500   1.1970   0.03778   0.03053  -0.0213   0.0277   1.0000
  10.750   1.2119   0.04041   0.03344  -0.0201   0.0272   1.0000
  11.000   1.2214   0.04332   0.03666  -0.0184   0.0269   1.0000
  11.250   1.2242   0.04648   0.04014  -0.0161   0.0268   1.0000
  11.500   1.2210   0.04978   0.04379  -0.0137   0.0270   1.0000
  11.750   1.2150   0.05271   0.04698  -0.0116   0.0267   1.0000
  12.000   1.2062   0.05587   0.05039  -0.0098   0.0264   1.0000
  12.250   1.1930   0.05969   0.05448  -0.0085   0.0266   1.0000
  12.500   1.1833   0.06286   0.05783  -0.0079   0.0260   1.0000
  12.750   1.1590   0.06840   0.06369  -0.0079   0.0267   1.0000
  13.000   1.1369   0.07390   0.06944  -0.0089   0.0271   1.0000
  13.250   1.1156   0.07954   0.07529  -0.0108   0.0272   1.0000
  13.500   1.0901   0.08652   0.08248  -0.0138   0.0279   1.0000
  13.750   1.0658   0.09382   0.08994  -0.0177   0.0282   1.0000
  14.000   1.0410   0.10200   0.09827  -0.0225   0.0289   1.0000
  14.250   1.0167   0.11104   0.10742  -0.0279   0.0297   1.0000
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