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FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 84-W-097 (fx84w097-il)
Reynolds number: 500,000
Max Cl/Cd: 104.34 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx84w097-il-500000.txt
Download as CSV file: xf-fx84w097-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4479   0.10225   0.10004  -0.0182   1.0000   0.0216
  -9.750  -0.4459   0.09780   0.09560  -0.0206   1.0000   0.0217
  -9.500  -0.4560   0.09109   0.08894  -0.0230   1.0000   0.0223
  -9.250  -0.4518   0.08787   0.08574  -0.0243   1.0000   0.0226
  -9.000  -0.4446   0.08551   0.08339  -0.0250   1.0000   0.0231
  -8.750  -0.4413   0.08216   0.08007  -0.0267   1.0000   0.0235
  -8.500  -0.4404   0.07842   0.07636  -0.0290   1.0000   0.0238
  -8.250  -0.4413   0.07452   0.07251  -0.0317   1.0000   0.0243
  -8.000  -0.4477   0.06999   0.06804  -0.0359   1.0000   0.0245
  -7.750  -0.4373   0.06293   0.06094  -0.0464   0.9727   0.0251
  -7.500  -0.4262   0.05563   0.05346  -0.0545   0.9421   0.0260
  -7.250  -0.4582   0.03790   0.03493  -0.0589   0.9124   0.0230
  -7.000  -0.4592   0.02970   0.02610  -0.0579   0.8987   0.0191
  -6.750  -0.4540   0.02190   0.01725  -0.0561   0.8873   0.0183
  -6.500  -0.4327   0.01980   0.01478  -0.0554   0.8780   0.0188
  -6.250  -0.4099   0.01825   0.01292  -0.0546   0.8698   0.0195
  -6.000  -0.3854   0.01698   0.01139  -0.0540   0.8611   0.0204
  -5.750  -0.3602   0.01603   0.01022  -0.0534   0.8534   0.0212
  -5.500  -0.3358   0.01459   0.00853  -0.0529   0.8453   0.0224
  -5.250  -0.3103   0.01382   0.00769  -0.0526   0.8374   0.0243
  -5.000  -0.2841   0.01335   0.00713  -0.0522   0.8297   0.0260
  -4.750  -0.2574   0.01279   0.00647  -0.0519   0.8219   0.0277
  -4.500  -0.2305   0.01246   0.00602  -0.0516   0.8146   0.0289
  -4.250  -0.2052   0.01145   0.00494  -0.0512   0.8069   0.0326
  -4.000  -0.1783   0.01114   0.00457  -0.0510   0.7999   0.0358
  -3.750  -0.1507   0.01088   0.00424  -0.0508   0.7923   0.0382
  -3.500  -0.1245   0.01028   0.00359  -0.0505   0.7854   0.0445
  -3.250  -0.0968   0.01005   0.00331  -0.0504   0.7779   0.0501
  -3.000  -0.0697   0.00970   0.00294  -0.0502   0.7709   0.0603
  -2.750  -0.0421   0.00942   0.00267  -0.0502   0.7636   0.0747
  -2.500  -0.0149   0.00912   0.00244  -0.0501   0.7565   0.0994
  -2.250   0.0126   0.00884   0.00226  -0.0501   0.7491   0.1353
  -2.000   0.0397   0.00854   0.00212  -0.0500   0.7419   0.1900
  -1.750   0.0667   0.00816   0.00200  -0.0501   0.7345   0.2677
  -1.500   0.0928   0.00764   0.00188  -0.0500   0.7273   0.3991
  -1.250   0.1172   0.00692   0.00182  -0.0496   0.7199   0.5962
  -1.000   0.1401   0.00644   0.00184  -0.0484   0.7129   0.7571
  -0.750   0.1636   0.00626   0.00189  -0.0470   0.7056   0.8408
  -0.500   0.1873   0.00621   0.00189  -0.0456   0.6987   0.8890
  -0.250   0.2118   0.00620   0.00189  -0.0445   0.6915   0.9246
   0.000   0.2402   0.00621   0.00187  -0.0442   0.6844   0.9516
   0.250   0.2757   0.00623   0.00184  -0.0455   0.6770   0.9722
   0.500   0.3158   0.00626   0.00179  -0.0480   0.6696   0.9847
   0.750   0.3598   0.00628   0.00176  -0.0515   0.6615   0.9934
   1.000   0.4009   0.00631   0.00171  -0.0544   0.6538   1.0000
   1.250   0.4251   0.00634   0.00171  -0.0537   0.6452   1.0000
   1.500   0.4495   0.00641   0.00171  -0.0531   0.6378   1.0000
   1.750   0.4745   0.00646   0.00174  -0.0525   0.6293   1.0000
   2.000   0.4996   0.00654   0.00178  -0.0520   0.6217   1.0000
   2.250   0.5252   0.00661   0.00182  -0.0516   0.6134   1.0000
   2.500   0.5512   0.00669   0.00188  -0.0512   0.6051   1.0000
   2.750   0.5773   0.00679   0.00193  -0.0509   0.5960   1.0000
   3.000   0.6039   0.00686   0.00200  -0.0507   0.5857   1.0000
   3.250   0.6307   0.00696   0.00208  -0.0504   0.5767   1.0000
   3.500   0.6574   0.00708   0.00217  -0.0503   0.5675   1.0000
   3.750   0.6845   0.00717   0.00228  -0.0501   0.5570   1.0000
   4.000   0.7116   0.00728   0.00239  -0.0500   0.5468   1.0000
   4.250   0.7384   0.00741   0.00250  -0.0498   0.5356   1.0000
   4.500   0.7651   0.00754   0.00261  -0.0496   0.5170   1.0000
   4.750   0.7912   0.00772   0.00272  -0.0494   0.4950   1.0000
   5.000   0.8178   0.00788   0.00287  -0.0492   0.4751   1.0000
   5.250   0.8441   0.00809   0.00303  -0.0490   0.4547   1.0000
   5.500   0.8700   0.00834   0.00324  -0.0488   0.4297   1.0000
   5.750   0.8953   0.00866   0.00347  -0.0485   0.3988   1.0000
   6.000   0.9196   0.00909   0.00375  -0.0481   0.3590   1.0000
   6.250   0.9424   0.00970   0.00413  -0.0476   0.3052   1.0000
   6.500   0.9628   0.01059   0.00467  -0.0468   0.2349   1.0000
   6.750   0.9811   0.01172   0.00537  -0.0459   0.1561   1.0000
   7.000   0.9983   0.01293   0.00618  -0.0448   0.0870   1.0000
   7.250   1.0175   0.01388   0.00691  -0.0439   0.0532   1.0000
   7.500   1.0382   0.01464   0.00761  -0.0430   0.0390   1.0000
   7.750   1.0575   0.01551   0.00848  -0.0419   0.0307   1.0000
   8.000   1.0792   0.01607   0.00911  -0.0412   0.0272   1.0000
   8.250   1.0959   0.01708   0.01014  -0.0398   0.0236   1.0000
   8.500   1.1140   0.01788   0.01103  -0.0385   0.0217   1.0000
   8.750   1.1329   0.01854   0.01175  -0.0375   0.0200   1.0000
   9.000   1.1497   0.01933   0.01259  -0.0361   0.0186   1.0000
   9.250   1.1585   0.02068   0.01399  -0.0338   0.0173   1.0000
   9.500   1.1629   0.02209   0.01552  -0.0308   0.0166   1.0000
   9.750   1.1737   0.02301   0.01652  -0.0287   0.0162   1.0000
  10.000   1.1836   0.02407   0.01766  -0.0267   0.0157   1.0000
  10.250   1.1933   0.02525   0.01893  -0.0248   0.0152   1.0000
  10.500   1.2034   0.02646   0.02023  -0.0231   0.0146   1.0000
  10.750   1.2145   0.02755   0.02137  -0.0218   0.0139   1.0000
  11.000   1.2240   0.02886   0.02275  -0.0205   0.0134   1.0000
  11.250   1.2311   0.03049   0.02443  -0.0191   0.0127   1.0000
  11.500   1.2373   0.03278   0.02683  -0.0174   0.0124   1.0000
  11.750   1.2447   0.03532   0.02955  -0.0160   0.0120   1.0000
  12.000   1.2526   0.03694   0.03132  -0.0149   0.0118   1.0000
  12.250   1.2594   0.03898   0.03352  -0.0138   0.0116   1.0000
  12.500   1.2646   0.04107   0.03578  -0.0128   0.0114   1.0000
  12.750   1.2671   0.04370   0.03859  -0.0118   0.0112   1.0000
  13.000   1.2674   0.04654   0.04163  -0.0111   0.0110   1.0000
  13.250   1.2654   0.04958   0.04487  -0.0105   0.0108   1.0000
  13.500   1.2599   0.05320   0.04870  -0.0103   0.0107   1.0000
  13.750   1.2529   0.05699   0.05269  -0.0104   0.0106   1.0000
  14.000   1.2436   0.06124   0.05716  -0.0110   0.0105   1.0000
  14.250   1.2282   0.06659   0.06276  -0.0122   0.0105   1.0000
  14.500   1.2203   0.07080   0.06710  -0.0136   0.0103   1.0000
  14.750   1.2026   0.07695   0.07348  -0.0159   0.0104   1.0000
  15.000   1.1815   0.08422   0.08097  -0.0192   0.0104   1.0000
  15.250   1.1630   0.09145   0.08838  -0.0230   0.0104   1.0000
  15.500   1.1335   0.10161   0.09877  -0.0287   0.0106   1.0000
  15.750   1.1127   0.11060   0.10793  -0.0342   0.0106   1.0000
  16.000   1.0891   0.12100   0.11850  -0.0408   0.0107   1.0000
  16.250   1.0537   0.13559   0.13328  -0.0502   0.0113   1.0000
  16.500   1.0178   0.15196   0.14977  -0.0603   0.0117   1.0000
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