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FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 84-W-097 (fx84w097-il)
Reynolds number: 100,000
Max Cl/Cd: 56.48 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx84w097-il-100000.txt
Download as CSV file: xf-fx84w097-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4339   0.11468   0.10978  -0.0147   1.0000   0.0868
  -9.750  -0.4477   0.11282   0.10803  -0.0207   1.0000   0.0884
  -9.500  -0.4618   0.11038   0.10571  -0.0267   1.0000   0.0888
  -9.250  -0.4215   0.10332   0.09855  -0.0193   1.0000   0.0925
  -9.000  -0.4136   0.10014   0.09540  -0.0200   1.0000   0.0967
  -8.750  -0.3252   0.08790   0.08355  -0.0254   1.0000   0.1095
  -8.500  -0.3271   0.08431   0.08001  -0.0274   1.0000   0.1139
  -8.250  -0.3519   0.08126   0.07709  -0.0334   1.0000   0.1166
  -8.000  -0.3434   0.07612   0.07199  -0.0330   1.0000   0.1188
  -7.750  -0.3255   0.07262   0.06849  -0.0311   1.0000   0.1235
  -7.500  -0.3331   0.06926   0.06522  -0.0330   1.0000   0.1282
  -7.250  -0.4131   0.07605   0.07179  -0.0345   1.0000   0.1216
  -7.000  -0.4129   0.07316   0.06896  -0.0354   1.0000   0.1263
  -6.750  -0.4438   0.07160   0.06740  -0.0373   1.0000   0.1306
  -6.500  -0.4677   0.06959   0.06533  -0.0362   1.0000   0.1321
  -6.250  -0.4630   0.06678   0.06269  -0.0316   1.0000   0.1341
  -6.000  -0.4652   0.06495   0.06090  -0.0285   1.0000   0.1370
  -5.750  -0.4774   0.06238   0.05804  -0.0313   0.9998   0.1467
  -5.500  -0.4484   0.05840   0.05420  -0.0318   0.9948   0.1522
  -5.250  -0.4175   0.05399   0.04962  -0.0373   0.9869   0.1667
  -5.000  -0.3747   0.03916   0.03312  -0.0482   0.9788   0.0912
  -4.750  -0.3378   0.03430   0.02768  -0.0511   0.9727   0.0832
  -4.500  -0.3029   0.02962   0.02204  -0.0529   0.9659   0.0780
  -4.250  -0.2641   0.02745   0.01953  -0.0554   0.9596   0.0821
  -4.000  -0.2268   0.02558   0.01708  -0.0570   0.9526   0.0871
  -3.750  -0.1876   0.02353   0.01477  -0.0592   0.9463   0.0927
  -3.500  -0.1480   0.02234   0.01337  -0.0614   0.9400   0.1044
  -3.250  -0.1100   0.02116   0.01210  -0.0632   0.9329   0.1182
  -3.000  -0.0675   0.01999   0.01109  -0.0661   0.9278   0.1422
  -2.750  -0.0379   0.01918   0.01042  -0.0665   0.9188   0.1758
  -2.500  -0.0051   0.01804   0.00978  -0.0676   0.9119   0.2511
  -2.250   0.0127   0.01604   0.00961  -0.0656   0.9036   0.6055
  -2.000   0.0816   0.01563   0.00977  -0.0688   0.9033   0.9560
  -1.750   0.1914   0.01516   0.00882  -0.0842   0.9046   1.0000
  -1.500   0.2145   0.01525   0.00873  -0.0837   0.8934   1.0000
  -1.250   0.2391   0.01532   0.00864  -0.0833   0.8836   1.0000
  -1.000   0.2600   0.01546   0.00862  -0.0821   0.8729   1.0000
  -0.750   0.2780   0.01568   0.00873  -0.0806   0.8615   1.0000
  -0.500   0.2979   0.01588   0.00881  -0.0792   0.8513   1.0000
  -0.250   0.3208   0.01598   0.00879  -0.0780   0.8429   1.0000
   0.000   0.3390   0.01627   0.00898  -0.0764   0.8317   1.0000
   0.250   0.3592   0.01652   0.00914  -0.0750   0.8220   1.0000
   0.500   0.3824   0.01662   0.00914  -0.0737   0.8140   1.0000
   0.750   0.4019   0.01694   0.00942  -0.0724   0.8034   1.0000
   1.000   0.4239   0.01717   0.00958  -0.0711   0.7946   1.0000
   1.250   0.4470   0.01733   0.00968  -0.0700   0.7860   1.0000
   1.500   0.4683   0.01766   0.00998  -0.0689   0.7760   1.0000
   1.750   0.4939   0.01768   0.00995  -0.0678   0.7694   1.0000
   2.000   0.5154   0.01805   0.01032  -0.0669   0.7584   1.0000
   2.250   0.5385   0.01832   0.01058  -0.0659   0.7490   1.0000
   2.500   0.5643   0.01835   0.01059  -0.0649   0.7414   1.0000
   2.750   0.5869   0.01869   0.01097  -0.0641   0.7306   1.0000
   3.000   0.6115   0.01887   0.01116  -0.0632   0.7217   1.0000
   3.250   0.6371   0.01895   0.01125  -0.0623   0.7130   1.0000
   3.500   0.6605   0.01927   0.01162  -0.0615   0.7023   1.0000
   3.750   0.6861   0.01939   0.01180  -0.0606   0.6934   1.0000
   4.000   0.7119   0.01945   0.01189  -0.0598   0.6839   1.0000
   4.250   0.7359   0.01967   0.01218  -0.0589   0.6722   1.0000
   4.500   0.7609   0.01978   0.01236  -0.0580   0.6611   1.0000
   4.750   0.7881   0.01970   0.01234  -0.0570   0.6517   1.0000
   5.000   0.8137   0.01975   0.01247  -0.0561   0.6402   1.0000
   5.250   0.8385   0.01987   0.01269  -0.0552   0.6273   1.0000
   5.500   0.8637   0.01989   0.01284  -0.0542   0.6140   1.0000
   5.750   0.8901   0.01955   0.01255  -0.0529   0.5982   1.0000
   6.000   0.9152   0.01905   0.01207  -0.0512   0.5772   1.0000
   6.250   0.9404   0.01849   0.01151  -0.0494   0.5538   1.0000
   6.500   0.9634   0.01823   0.01136  -0.0478   0.5278   1.0000
   6.750   0.9860   0.01806   0.01125  -0.0462   0.4990   1.0000
   7.000   1.0069   0.01798   0.01122  -0.0445   0.4633   1.0000
   7.250   1.0246   0.01814   0.01133  -0.0424   0.4110   1.0000
   7.500   1.0326   0.01910   0.01181  -0.0393   0.3012   1.0000
   7.750   1.0222   0.02227   0.01367  -0.0350   0.1550   1.0000
   8.000   1.0222   0.02473   0.01564  -0.0318   0.1138   1.0000
   8.250   1.0293   0.02656   0.01740  -0.0293   0.0942   1.0000
   8.500   1.0394   0.02841   0.01917  -0.0270   0.0831   1.0000
   8.750   1.0547   0.03038   0.02098  -0.0255   0.0739   1.0000
   9.000   1.0751   0.03209   0.02272  -0.0245   0.0667   1.0000
   9.250   1.1067   0.03489   0.02549  -0.0247   0.0616   1.0000
   9.500   1.1287   0.03682   0.02764  -0.0238   0.0569   1.0000
   9.750   1.1528   0.03930   0.03020  -0.0236   0.0534   1.0000
  10.000   1.1821   0.04422   0.03528  -0.0241   0.0516   1.0000
  10.250   1.1957   0.04730   0.03877  -0.0225   0.0511   1.0000
  10.500   1.2055   0.05071   0.04261  -0.0208   0.0509   1.0000
  10.750   1.2089   0.05387   0.04620  -0.0187   0.0505   1.0000
  11.000   1.2070   0.05695   0.04969  -0.0163   0.0500   1.0000
  11.250   1.1999   0.06009   0.05321  -0.0138   0.0495   1.0000
  11.500   1.1891   0.06348   0.05688  -0.0112   0.0496   1.0000
  11.750   1.1749   0.06702   0.06068  -0.0091   0.0497   1.0000
  12.000   1.1589   0.07101   0.06490  -0.0078   0.0500   1.0000
  12.250   1.1445   0.07566   0.06975  -0.0074   0.0506   1.0000
  12.500   1.1441   0.08203   0.07624  -0.0077   0.0517   1.0000
  12.750   1.1216   0.08508   0.07954  -0.0079   0.0522   1.0000
  13.000   1.0844   0.09021   0.08497  -0.0104   0.0531   1.0000
  13.250   0.9946   0.10631   0.10150  -0.0225   0.0590   1.0000
  13.500   0.9697   0.11616   0.11141  -0.0285   0.0610   1.0000
  13.750   0.9647   0.12298   0.11823  -0.0309   0.0626   1.0000
  14.000   0.7541   0.13892   0.13455  -0.0389   0.0748   1.0000
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