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FX 66-H-80 (fx66h80-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 66-H-80 (fx66h80-il)
Reynolds number: 50,000
Max Cl/Cd: 31.93 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66h80-il-50000-n5.txt
Download as CSV file: xf-fx66h80-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5610   0.12051   0.11433   0.0281   1.0000   0.0856
  -9.000  -0.5662   0.11808   0.11199   0.0240   1.0000   0.0873
  -8.750  -0.5726   0.11552   0.10954   0.0195   1.0000   0.0879
  -8.500  -0.5481   0.10909   0.10308   0.0238   1.0000   0.0943
  -8.250  -0.5479   0.10589   0.09996   0.0212   1.0000   0.0987
  -8.000  -0.5601   0.10354   0.09775   0.0154   1.0000   0.1012
  -7.750  -0.5446   0.09833   0.09257   0.0174   1.0000   0.1060
  -7.500  -0.5423   0.09490   0.08921   0.0156   1.0000   0.1108
  -7.250  -0.5522   0.09245   0.08678   0.0080   1.0000   0.1151
  -7.000  -0.5370   0.08723   0.08166   0.0103   1.0000   0.1193
  -6.750  -0.5301   0.08357   0.07801   0.0085   1.0000   0.1252
  -6.500  -0.5261   0.07965   0.07410   0.0051   1.0000   0.1316
  -6.250  -0.5142   0.07569   0.07016   0.0047   1.0000   0.1364
  -5.750  -0.4928   0.06804   0.06247   0.0012   1.0000   0.1511
  -5.500  -0.4591   0.05904   0.05282  -0.0050   1.0000   0.0551
  -5.250  -0.4374   0.05435   0.04756  -0.0065   1.0000   0.0468
  -5.000  -0.4203   0.05040   0.04355  -0.0067   1.0000   0.0453
  -4.750  -0.4010   0.04674   0.03968  -0.0069   1.0000   0.0439
  -4.500  -0.3800   0.04324   0.03582  -0.0070   1.0000   0.0427
  -4.250  -0.3574   0.03993   0.03219  -0.0069   1.0000   0.0417
  -4.000  -0.3334   0.03684   0.02873  -0.0069   1.0000   0.0410
  -3.750  -0.2962   0.03361   0.02493  -0.0090   0.9036   0.0406
  -3.500  -0.2626   0.03121   0.02188  -0.0095   0.8516   0.0424
  -3.250  -0.2352   0.02950   0.01950  -0.0085   0.8154   0.0455
  -2.750  -0.1826   0.02617   0.01522  -0.0061   0.7635   0.0495
  -2.500  -0.1545   0.02473   0.01344  -0.0053   0.7423   0.0526
  -2.250  -0.1246   0.02365   0.01195  -0.0046   0.7241   0.0596
  -2.000  -0.0961   0.02264   0.01071  -0.0043   0.7074   0.0723
  -1.750  -0.0703   0.02167   0.00954  -0.0033   0.6927   0.0864
  -1.500   0.0255   0.01711   0.00788  -0.0148   0.6752   1.0000
  -1.250   0.0500   0.01724   0.00744  -0.0140   0.6622   1.0000
  -1.000   0.0744   0.01738   0.00716  -0.0132   0.6504   1.0000
  -0.750   0.0988   0.01754   0.00695  -0.0125   0.6396   1.0000
  -0.500   0.1236   0.01771   0.00682  -0.0120   0.6287   1.0000
  -0.250   0.1486   0.01790   0.00676  -0.0115   0.6185   1.0000
   0.000   0.1734   0.01811   0.00669  -0.0110   0.6092   1.0000
   0.250   0.1981   0.01833   0.00669  -0.0104   0.6004   1.0000
   0.500   0.2234   0.01857   0.00679  -0.0100   0.5913   1.0000
   0.750   0.2482   0.01882   0.00687  -0.0095   0.5834   1.0000
   1.000   0.2732   0.01909   0.00703  -0.0091   0.5750   1.0000
   1.250   0.2981   0.01939   0.00723  -0.0087   0.5673   1.0000
   1.500   0.3226   0.01969   0.00743  -0.0081   0.5600   1.0000
   1.750   0.3476   0.02004   0.00775  -0.0078   0.5522   1.0000
   2.000   0.3720   0.02037   0.00803  -0.0072   0.5457   1.0000
   2.250   0.3973   0.02077   0.00844  -0.0071   0.5380   1.0000
   2.500   0.4219   0.02113   0.00875  -0.0065   0.5318   1.0000
   2.750   0.4470   0.02160   0.00928  -0.0064   0.5245   1.0000
   3.000   0.4714   0.02200   0.00968  -0.0058   0.5185   1.0000
   3.250   0.4962   0.02252   0.01035  -0.0056   0.5114   1.0000
   3.500   0.5205   0.02298   0.01086  -0.0051   0.5054   1.0000
   3.750   0.5450   0.02356   0.01154  -0.0049   0.4989   1.0000
   4.000   0.5693   0.02410   0.01218  -0.0045   0.4925   1.0000
   4.250   0.5935   0.02469   0.01290  -0.0042   0.4866   1.0000
   4.500   0.6176   0.02537   0.01383  -0.0040   0.4799   1.0000
   4.750   0.6416   0.02591   0.01449  -0.0033   0.4747   1.0000
   5.000   0.6652   0.02679   0.01563  -0.0034   0.4673   1.0000
   5.250   0.6891   0.02732   0.01629  -0.0026   0.4624   1.0000
   5.500   0.7119   0.02838   0.01769  -0.0028   0.4545   1.0000
   5.750   0.7356   0.02899   0.01848  -0.0021   0.4492   1.0000
   6.000   0.7576   0.03016   0.02010  -0.0022   0.4412   1.0000
   6.250   0.7810   0.03078   0.02098  -0.0014   0.4356   1.0000
   6.500   0.8019   0.03207   0.02267  -0.0015   0.4269   1.0000
   6.750   0.8258   0.03250   0.02340  -0.0003   0.4211   1.0000
   7.000   0.8469   0.03207   0.02332   0.0015   0.3996   1.0000
   7.250   0.8698   0.02749   0.01878   0.0064   0.3295   1.0000
   7.500   0.8812   0.02760   0.01799   0.0082   0.1491   1.0000
   7.750   0.8795   0.03182   0.02146   0.0082   0.0837   1.0000
   8.000   0.8818   0.03501   0.02460   0.0085   0.0688   1.0000
   8.250   0.8827   0.03796   0.02756   0.0088   0.0602   1.0000
   8.500   0.8826   0.04077   0.03044   0.0091   0.0536   1.0000
   8.750   0.8802   0.04365   0.03336   0.0092   0.0504   1.0000
   9.000   0.8804   0.04617   0.03603   0.0099   0.0478   1.0000
   9.250   0.8833   0.04847   0.03846   0.0110   0.0453   1.0000
   9.500   0.8895   0.05051   0.04056   0.0124   0.0430   1.0000
   9.750   0.8996   0.05229   0.04229   0.0150   0.0399   1.0000
  10.000   0.9116   0.05430   0.04460   0.0163   0.0366   1.0000
  10.250   0.9242   0.05646   0.04703   0.0178   0.0338   1.0000
  10.500   0.9399   0.05886   0.04971   0.0196   0.0324   1.0000
  10.750   0.9483   0.06202   0.05322   0.0204   0.0315   1.0000
  11.000   0.9506   0.06571   0.05716   0.0202   0.0309   1.0000
  11.250   0.9481   0.06976   0.06145   0.0193   0.0307   1.0000
  11.500   0.9416   0.07428   0.06620   0.0177   0.0306   1.0000
  11.750   0.9318   0.07933   0.07147   0.0154   0.0306   1.0000
  12.000   0.9196   0.08481   0.07715   0.0124   0.0308   1.0000
  12.250   0.9048   0.09098   0.08350   0.0087   0.0310   1.0000
  12.500   0.8874   0.09801   0.09068   0.0043   0.0314   1.0000
  12.750   0.8681   0.10600   0.09881  -0.0008   0.0320   1.0000
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