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FX 66-H-80 (fx66h80-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 66-H-80 (fx66h80-il)
Reynolds number: 500,000
Max Cl/Cd: 87.56 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66h80-il-500000.txt
Download as CSV file: xf-fx66h80-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-H-80                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5466   0.09195   0.09003   0.0221   1.0000   0.0118
  -7.750  -0.5467   0.08814   0.08626   0.0192   1.0000   0.0128
  -7.500  -0.5499   0.08449   0.08263   0.0165   1.0000   0.0129
  -7.250  -0.5473   0.08041   0.07855   0.0130   1.0000   0.0132
  -7.000  -0.5354   0.07649   0.07461   0.0086   1.0000   0.0138
  -6.750  -0.5246   0.07236   0.07043   0.0059   1.0000   0.0139
  -6.500  -0.5124   0.06809   0.06610   0.0036   1.0000   0.0140
  -6.250  -0.4935   0.06334   0.06123   0.0003   0.9290   0.0140
  -6.000  -0.4824   0.05983   0.05725   0.0004   0.8093   0.0141
  -5.750  -0.4684   0.03966   0.03686   0.0022   0.7111   0.0148
  -5.500  -0.4571   0.03536   0.03237   0.0019   0.6863   0.0152
  -5.250  -0.4427   0.03168   0.02850   0.0017   0.6638   0.0156
  -5.000  -0.4265   0.02824   0.02485   0.0016   0.6434   0.0161
  -4.750  -0.4086   0.02490   0.02129   0.0017   0.6261   0.0168
  -4.500  -0.3976   0.03631   0.03216   0.0007   0.6343   0.0175
  -4.250  -0.3758   0.03348   0.02901   0.0014   0.6168   0.0187
  -4.000  -0.3521   0.03082   0.02602   0.0024   0.6011   0.0205
  -3.750  -0.3221   0.03064   0.02551   0.0036   0.5856   0.0228
  -3.500  -0.2985   0.02851   0.02301   0.0047   0.5728   0.0229
  -3.250  -0.2820   0.02241   0.01638   0.0061   0.5638   0.0248
  -3.000  -0.2578   0.02070   0.01449   0.0067   0.5530   0.0263
  -2.750  -0.2304   0.01801   0.01134   0.0083   0.5441   0.0205
  -2.500  -0.2037   0.01538   0.00832   0.0096   0.5353   0.0182
  -2.250  -0.1767   0.01453   0.00726   0.0101   0.5269   0.0196
  -2.000  -0.1498   0.01336   0.00591   0.0107   0.5191   0.0194
  -1.750  -0.1236   0.01223   0.00463   0.0115   0.5120   0.0186
  -1.500  -0.0980   0.01143   0.00371   0.0123   0.5054   0.0184
  -1.250  -0.0722   0.01085   0.00304   0.0130   0.4991   0.0192
  -1.000  -0.0460   0.01044   0.00252   0.0136   0.4929   0.0214
  -0.750  -0.0204   0.00988   0.00194   0.0144   0.4876   0.0521
  -0.500   0.0020   0.00894   0.00177   0.0151   0.4821   0.2797
  -0.250   0.0714   0.00713   0.00206   0.0068   0.4749   0.9806
   0.000   0.1531   0.00729   0.00202  -0.0047   0.4670   0.9991
   0.250   0.1824   0.00734   0.00194  -0.0050   0.4622   1.0000
   0.500   0.2075   0.00734   0.00189  -0.0045   0.4573   1.0000
   0.750   0.2328   0.00735   0.00184  -0.0040   0.4525   1.0000
   1.000   0.2579   0.00743   0.00181  -0.0035   0.4482   1.0000
   1.250   0.2834   0.00743   0.00180  -0.0030   0.4438   1.0000
   1.500   0.3088   0.00746   0.00179  -0.0025   0.4394   1.0000
   1.750   0.3342   0.00755   0.00180  -0.0020   0.4350   1.0000
   2.000   0.3598   0.00758   0.00183  -0.0016   0.4305   1.0000
   2.250   0.3853   0.00762   0.00186  -0.0011   0.4261   1.0000
   2.500   0.4107   0.00771   0.00190  -0.0007   0.4221   1.0000
   2.750   0.4363   0.00778   0.00197  -0.0002   0.4178   1.0000
   3.000   0.4619   0.00783   0.00203   0.0002   0.4131   1.0000
   3.250   0.4874   0.00792   0.00212   0.0007   0.4089   1.0000
   3.500   0.5129   0.00802   0.00222   0.0011   0.4048   1.0000
   3.750   0.5386   0.00809   0.00232   0.0015   0.4002   1.0000
   4.000   0.5641   0.00818   0.00242   0.0020   0.3957   1.0000
   4.250   0.5897   0.00831   0.00256   0.0024   0.3915   1.0000
   4.500   0.6155   0.00839   0.00273   0.0028   0.3868   1.0000
   4.750   0.6410   0.00850   0.00286   0.0032   0.3822   1.0000
   5.000   0.6667   0.00854   0.00295   0.0037   0.3739   1.0000
   5.250   0.6922   0.00856   0.00300   0.0041   0.3633   1.0000
   5.500   0.7179   0.00855   0.00303   0.0045   0.3479   1.0000
   5.750   0.7434   0.00862   0.00310   0.0049   0.3242   1.0000
   6.000   0.7688   0.00878   0.00326   0.0053   0.3019   1.0000
   6.250   0.7930   0.00920   0.00353   0.0057   0.2540   1.0000
   6.500   0.8066   0.01212   0.00527   0.0061   0.0343   1.0000
   6.750   0.8296   0.01287   0.00609   0.0068   0.0240   1.0000
   7.000   0.8506   0.01403   0.00741   0.0076   0.0186   1.0000
   7.250   0.8738   0.01457   0.00806   0.0082   0.0164   1.0000
   7.500   0.8951   0.01547   0.00906   0.0089   0.0141   1.0000
   7.750   0.9123   0.01699   0.01071   0.0099   0.0121   1.0000
   8.000   0.9204   0.01982   0.01373   0.0120   0.0110   1.0000
   8.250   0.9431   0.02021   0.01420   0.0126   0.0102   1.0000
   8.500   0.9624   0.02109   0.01516   0.0136   0.0093   1.0000
   8.750   0.9786   0.02244   0.01662   0.0148   0.0087   1.0000
   9.000   0.9944   0.02387   0.01815   0.0161   0.0082   1.0000
   9.250   1.0091   0.02551   0.01994   0.0175   0.0078   1.0000
   9.500   1.0233   0.02722   0.02178   0.0188   0.0075   1.0000
   9.750   1.0356   0.02905   0.02370   0.0200   0.0070   1.0000
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