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FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 84-W-097 (fx84w097-il)
Reynolds number: 200,000
Max Cl/Cd: 73.46 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx84w097-il-200000-n5.txt
Download as CSV file: xf-fx84w097-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4499   0.08867   0.08524  -0.0235   1.0000   0.0178
  -9.000  -0.4543   0.08320   0.07982  -0.0268   1.0000   0.0175
  -8.750  -0.4621   0.07717   0.07386  -0.0307   1.0000   0.0172
  -8.500  -0.4890   0.06711   0.06394  -0.0390   1.0000   0.0165
  -8.250  -0.5147   0.05274   0.04940  -0.0499   1.0000   0.0161
  -8.000  -0.5217   0.04083   0.03690  -0.0575   0.9689   0.0161
  -7.750  -0.5126   0.03370   0.02905  -0.0607   0.9473   0.0163
  -7.500  -0.4947   0.03063   0.02561  -0.0614   0.9325   0.0168
  -7.250  -0.4759   0.02835   0.02298  -0.0612   0.9192   0.0172
  -7.000  -0.4560   0.02654   0.02085  -0.0607   0.9075   0.0180
  -6.750  -0.4347   0.02511   0.01910  -0.0602   0.8969   0.0193
  -6.500  -0.4138   0.02323   0.01677  -0.0593   0.8869   0.0206
  -6.250  -0.3915   0.02149   0.01459  -0.0585   0.8772   0.0214
  -6.000  -0.3691   0.01984   0.01266  -0.0577   0.8686   0.0223
  -5.750  -0.3452   0.01886   0.01155  -0.0572   0.8599   0.0235
  -5.500  -0.3205   0.01813   0.01069  -0.0567   0.8515   0.0250
  -5.250  -0.2954   0.01748   0.00983  -0.0561   0.8436   0.0274
  -5.000  -0.2697   0.01674   0.00890  -0.0556   0.8354   0.0290
  -4.750  -0.2456   0.01576   0.00785  -0.0550   0.8281   0.0311
  -4.500  -0.2196   0.01522   0.00725  -0.0546   0.8197   0.0338
  -4.250  -0.1938   0.01480   0.00668  -0.0541   0.8128   0.0375
  -4.000  -0.1681   0.01416   0.00600  -0.0538   0.8044   0.0412
  -3.750  -0.1420   0.01376   0.00552  -0.0534   0.7975   0.0460
  -3.500  -0.1156   0.01335   0.00507  -0.0531   0.7892   0.0528
  -3.250  -0.0892   0.01302   0.00464  -0.0528   0.7823   0.0609
  -3.000  -0.0625   0.01267   0.00430  -0.0526   0.7743   0.0730
  -2.750  -0.0359   0.01237   0.00400  -0.0523   0.7675   0.0893
  -2.500  -0.0091   0.01206   0.00375  -0.0522   0.7598   0.1137
  -2.250   0.0175   0.01176   0.00352  -0.0520   0.7530   0.1475
  -2.000   0.0441   0.01142   0.00334  -0.0519   0.7453   0.1975
  -1.750   0.0701   0.01103   0.00317  -0.0517   0.7385   0.2702
  -1.500   0.0955   0.01051   0.00304  -0.0515   0.7307   0.3851
  -1.250   0.1182   0.00982   0.00296  -0.0506   0.7240   0.5621
  -1.000   0.1391   0.00932   0.00302  -0.0487   0.7163   0.7257
  -0.750   0.1614   0.00915   0.00305  -0.0468   0.7096   0.8227
  -0.500   0.1875   0.00910   0.00304  -0.0457   0.7017   0.8838
  -0.250   0.2189   0.00909   0.00298  -0.0460   0.6947   0.9244
   0.000   0.2561   0.00908   0.00291  -0.0476   0.6867   0.9546
   0.250   0.2984   0.00908   0.00281  -0.0505   0.6794   0.9782
   0.500   0.3470   0.00906   0.00271  -0.0549   0.6713   1.0000
   0.750   0.3713   0.00912   0.00269  -0.0542   0.6638   1.0000
   1.000   0.3958   0.00918   0.00268  -0.0536   0.6561   1.0000
   1.250   0.4205   0.00926   0.00270  -0.0531   0.6484   1.0000
   1.500   0.4455   0.00934   0.00272  -0.0525   0.6408   1.0000
   1.750   0.4709   0.00943   0.00278  -0.0521   0.6326   1.0000
   2.000   0.4963   0.00953   0.00281  -0.0516   0.6249   1.0000
   2.250   0.5223   0.00962   0.00289  -0.0512   0.6158   1.0000
   2.500   0.5482   0.00973   0.00296  -0.0509   0.6076   1.0000
   2.750   0.5744   0.00984   0.00307  -0.0506   0.5986   1.0000
   3.000   0.6007   0.00996   0.00318  -0.0503   0.5898   1.0000
   3.250   0.6270   0.01009   0.00328  -0.0500   0.5814   1.0000
   3.500   0.6535   0.01022   0.00344  -0.0497   0.5712   1.0000
   3.750   0.6798   0.01035   0.00358  -0.0495   0.5602   1.0000
   4.000   0.7061   0.01050   0.00372  -0.0492   0.5492   1.0000
   4.250   0.7324   0.01066   0.00388  -0.0489   0.5385   1.0000
   4.500   0.7588   0.01082   0.00410  -0.0486   0.5268   1.0000
   4.750   0.7850   0.01099   0.00430  -0.0484   0.5142   1.0000
   5.000   0.8109   0.01117   0.00450  -0.0480   0.4993   1.0000
   5.250   0.8357   0.01139   0.00468  -0.0475   0.4731   1.0000
   5.500   0.8595   0.01170   0.00489  -0.0469   0.4389   1.0000
   5.750   0.8833   0.01205   0.00516  -0.0463   0.4049   1.0000
   6.000   0.9062   0.01250   0.00548  -0.0456   0.3673   1.0000
   6.250   0.9279   0.01308   0.00589  -0.0449   0.3212   1.0000
   6.500   0.9469   0.01392   0.00646  -0.0439   0.2596   1.0000
   6.750   0.9638   0.01502   0.00719  -0.0428   0.1910   1.0000
   7.000   0.9792   0.01626   0.00806  -0.0415   0.1243   1.0000
   7.250   0.9953   0.01741   0.00895  -0.0403   0.0807   1.0000
   7.500   1.0128   0.01837   0.00980  -0.0392   0.0580   1.0000
   7.750   1.0309   0.01924   0.01065  -0.0381   0.0457   1.0000
   8.000   1.0483   0.02012   0.01156  -0.0369   0.0378   1.0000
   8.250   1.0648   0.02103   0.01250  -0.0356   0.0325   1.0000
   8.500   1.0800   0.02199   0.01354  -0.0342   0.0289   1.0000
   8.750   1.0951   0.02289   0.01453  -0.0328   0.0260   1.0000
   9.000   1.1061   0.02401   0.01568  -0.0309   0.0235   1.0000
   9.250   1.1147   0.02510   0.01687  -0.0287   0.0220   1.0000
   9.500   1.1234   0.02625   0.01815  -0.0266   0.0207   1.0000
   9.750   1.1316   0.02750   0.01951  -0.0247   0.0197   1.0000
  10.000   1.1397   0.02884   0.02093  -0.0230   0.0188   1.0000
  10.250   1.1473   0.03031   0.02248  -0.0215   0.0180   1.0000
  10.500   1.1529   0.03203   0.02425  -0.0200   0.0173   1.0000
  10.750   1.1589   0.03390   0.02619  -0.0185   0.0166   1.0000
  11.000   1.1690   0.03539   0.02784  -0.0175   0.0158   1.0000
  11.250   1.1781   0.03700   0.02959  -0.0165   0.0149   1.0000
  11.500   1.1860   0.03885   0.03159  -0.0155   0.0144   1.0000
  11.750   1.1935   0.04078   0.03365  -0.0146   0.0139   1.0000
  12.000   1.2003   0.04280   0.03580  -0.0138   0.0135   1.0000
  12.250   1.2063   0.04495   0.03806  -0.0131   0.0132   1.0000
  12.500   1.2113   0.04726   0.04051  -0.0125   0.0129   1.0000
  12.750   1.2144   0.04982   0.04318  -0.0121   0.0125   1.0000
  13.000   1.2161   0.05279   0.04629  -0.0116   0.0123   1.0000
  13.250   1.2154   0.05611   0.04982  -0.0114   0.0120   1.0000
  13.500   1.2129   0.05953   0.05349  -0.0115   0.0118   1.0000
  13.750   1.2081   0.06329   0.05750  -0.0120   0.0116   1.0000
  14.000   1.2013   0.06746   0.06191  -0.0129   0.0114   1.0000
  14.250   1.1918   0.07214   0.06684  -0.0142   0.0112   1.0000
  14.500   1.1808   0.07724   0.07217  -0.0160   0.0110   1.0000
  14.750   1.1670   0.08315   0.07832  -0.0184   0.0110   1.0000
  15.000   1.1538   0.08921   0.08460  -0.0214   0.0108   1.0000
  15.250   1.1374   0.09630   0.09190  -0.0252   0.0108   1.0000
  15.500   1.1192   0.10427   0.10010  -0.0297   0.0107   1.0000
  15.750   1.0992   0.11314   0.10917  -0.0350   0.0108   1.0000
  16.000   1.0769   0.12327   0.11949  -0.0413   0.0109   1.0000
  16.250   1.0512   0.13521   0.13161  -0.0489   0.0112   1.0000
  16.500   1.0244   0.14857   0.14511  -0.0572   0.0116   1.0000
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