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WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il)
Reynolds number: 200,000
Max Cl/Cd: 71.48 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66a175-il-200000-n5.txt
Download as CSV file: xf-fx66a175-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 66-17A-175 AIRFOIL                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2238   0.09268   0.08792  -0.0794   0.6516   0.0124
 -11.500  -0.2311   0.08630   0.08154  -0.0824   0.6467   0.0121
 -11.250  -0.2568   0.07452   0.06975  -0.0886   0.6456   0.0117
 -11.000  -0.2843   0.06557   0.06068  -0.0946   0.6429   0.0115
 -10.750  -0.3075   0.05908   0.05405  -0.0989   0.6392   0.0114
 -10.500  -0.3256   0.05406   0.04888  -0.1020   0.6345   0.0111
 -10.250  -0.3442   0.04944   0.04407  -0.1044   0.6300   0.0111
 -10.000  -0.3604   0.04546   0.03987  -0.1061   0.6257   0.0111
  -9.750  -0.3729   0.04224   0.03646  -0.1068   0.6208   0.0110
  -9.500  -0.3863   0.03965   0.03362  -0.1056   0.6162   0.0111
  -9.250  -0.3892   0.03707   0.03072  -0.1046   0.6119   0.0111
  -9.000  -0.3862   0.03452   0.02785  -0.1036   0.6069   0.0113
  -8.750  -0.3780   0.03223   0.02522  -0.1026   0.6019   0.0115
  -8.500  -0.3657   0.03018   0.02281  -0.1016   0.5974   0.0118
  -8.250  -0.3496   0.02840   0.02076  -0.1007   0.5921   0.0120
  -8.000  -0.3316   0.02685   0.01893  -0.0999   0.5871   0.0125
  -7.750  -0.3120   0.02559   0.01741  -0.0991   0.5832   0.0128
  -7.500  -0.2926   0.02421   0.01590  -0.0983   0.5786   0.0134
  -7.250  -0.2725   0.02328   0.01490  -0.0978   0.5742   0.0144
  -7.000  -0.2509   0.02260   0.01411  -0.0973   0.5705   0.0156
  -6.750  -0.2295   0.02174   0.01312  -0.0966   0.5670   0.0165
  -6.500  -0.2081   0.02087   0.01216  -0.0959   0.5632   0.0173
  -6.250  -0.1863   0.02011   0.01128  -0.0952   0.5597   0.0181
  -6.000  -0.1652   0.01929   0.01035  -0.0946   0.5566   0.0190
  -5.750  -0.1433   0.01856   0.00951  -0.0941   0.5538   0.0207
  -5.500  -0.1191   0.01805   0.00893  -0.0939   0.5503   0.0236
  -5.250  -0.0947   0.01754   0.00830  -0.0936   0.5469   0.0269
  -5.000  -0.0707   0.01696   0.00763  -0.0933   0.5439   0.0322
  -4.750  -0.0461   0.01645   0.00706  -0.0931   0.5413   0.0450
  -4.500  -0.0225   0.01574   0.00653  -0.0929   0.5387   0.0915
  -4.250  -0.0003   0.01479   0.00600  -0.0929   0.5356   0.1970
  -4.000   0.0200   0.01394   0.00599  -0.0924   0.5326   0.3964
  -3.750   0.0476   0.01420   0.00617  -0.0922   0.5296   0.4477
  -3.500   0.0753   0.01447   0.00630  -0.0920   0.5270   0.4689
  -3.250   0.1028   0.01476   0.00645  -0.0917   0.5244   0.4864
  -3.000   0.1303   0.01496   0.00660  -0.0915   0.5215   0.4980
  -2.750   0.1579   0.01509   0.00664  -0.0914   0.5188   0.5070
  -2.500   0.1857   0.01514   0.00660  -0.0914   0.5163   0.5121
  -2.250   0.2138   0.01516   0.00646  -0.0915   0.5141   0.5165
  -2.000   0.2418   0.01518   0.00633  -0.0916   0.5121   0.5197
  -1.750   0.2697   0.01520   0.00629  -0.0917   0.5099   0.5223
  -1.500   0.2976   0.01520   0.00625  -0.0918   0.5074   0.5244
  -1.250   0.3255   0.01521   0.00618  -0.0920   0.5050   0.5266
  -1.000   0.3534   0.01524   0.00612  -0.0921   0.5027   0.5291
  -0.750   0.3815   0.01527   0.00605  -0.0923   0.5006   0.5314
  -0.500   0.4096   0.01530   0.00598  -0.0925   0.4988   0.5333
  -0.250   0.4376   0.01535   0.00596  -0.0927   0.4971   0.5348
   0.000   0.4652   0.01539   0.00600  -0.0928   0.4949   0.5365
   0.250   0.4926   0.01544   0.00604  -0.0929   0.4924   0.5383
   0.500   0.5202   0.01549   0.00609  -0.0930   0.4900   0.5403
   0.750   0.5478   0.01556   0.00612  -0.0931   0.4879   0.5426
   1.000   0.5755   0.01564   0.00616  -0.0933   0.4860   0.5451
   1.250   0.6034   0.01573   0.00619  -0.0935   0.4844   0.5474
   1.500   0.6313   0.01582   0.00625  -0.0936   0.4829   0.5491
   1.750   0.6585   0.01591   0.00638  -0.0937   0.4810   0.5509
   2.000   0.6852   0.01601   0.00652  -0.0937   0.4786   0.5529
   2.250   0.7121   0.01610   0.00665  -0.0937   0.4762   0.5552
   2.500   0.7391   0.01620   0.00676  -0.0938   0.4739   0.5579
   2.750   0.7664   0.01631   0.00688  -0.0939   0.4720   0.5607
   3.000   0.7937   0.01642   0.00699  -0.0940   0.4704   0.5632
   3.250   0.8211   0.01654   0.00713  -0.0941   0.4690   0.5656
   3.500   0.8482   0.01669   0.00733  -0.0942   0.4675   0.5684
   3.750   0.8741   0.01687   0.00760  -0.0941   0.4656   0.5713
   4.000   0.9001   0.01704   0.00785  -0.0940   0.4636   0.5743
   4.250   0.9263   0.01721   0.00809  -0.0940   0.4616   0.5772
   4.500   0.9525   0.01735   0.00832  -0.0940   0.4597   0.5800
   4.750   0.9789   0.01751   0.00854  -0.0939   0.4581   0.5834
   5.000   1.0056   0.01768   0.00877  -0.0940   0.4566   0.5873
   5.250   1.0325   0.01787   0.00901  -0.0941   0.4554   0.5913
   5.500   1.0595   0.01805   0.00926  -0.0942   0.4542   0.5948
   5.750   1.0840   0.01831   0.00968  -0.0939   0.4525   0.5989
   6.000   1.1082   0.01860   0.01011  -0.0937   0.4507   0.6036
   6.250   1.1327   0.01887   0.01055  -0.0934   0.4489   0.6084
   6.500   1.1572   0.01914   0.01096  -0.0932   0.4472   0.6138
   6.750   1.1820   0.01941   0.01135  -0.0929   0.4456   0.6203
   7.000   1.2068   0.01965   0.01174  -0.0927   0.4441   0.6271
   7.250   1.2321   0.01988   0.01211  -0.0926   0.4427   0.6359
   7.500   1.2579   0.02008   0.01244  -0.0925   0.4412   0.6465
   7.750   1.2847   0.02031   0.01280  -0.0926   0.4400   0.6599
   8.000   1.3055   0.02070   0.01345  -0.0918   0.4380   0.6770
   8.250   1.3227   0.02063   0.01364  -0.0901   0.4310   0.7021
   8.500   1.3381   0.01979   0.01300  -0.0876   0.4167   0.7564
   8.750   1.3581   0.01923   0.01281  -0.0863   0.4017   1.0000
   9.000   1.3695   0.01916   0.01269  -0.0836   0.3830   1.0000
   9.250   1.3704   0.01954   0.01306  -0.0793   0.3517   1.0000
   9.750   1.3250   0.02307   0.01597  -0.0665   0.2528   1.0000
  10.000   1.2965   0.02636   0.01912  -0.0621   0.2190   1.0000
  10.250   1.2681   0.03064   0.02332  -0.0596   0.1932   1.0000
  10.500   1.2467   0.03495   0.02760  -0.0583   0.1710   1.0000
  10.750   1.2173   0.04023   0.03279  -0.0572   0.1457   1.0000
  11.000   1.1969   0.04476   0.03727  -0.0563   0.1249   1.0000
  11.250   1.1696   0.05006   0.04244  -0.0556   0.0973   1.0000
  11.500   1.1427   0.05548   0.04769  -0.0550   0.0652   1.0000
  11.750   1.1167   0.06112   0.05311  -0.0548   0.0301   1.0000
  12.000   1.1108   0.06475   0.05671  -0.0548   0.0199   1.0000
  12.250   1.1056   0.06839   0.06036  -0.0548   0.0136   1.0000
  12.500   1.1037   0.07172   0.06374  -0.0549   0.0115   1.0000
  12.750   1.1056   0.07466   0.06679  -0.0550   0.0103   1.0000
  13.000   1.1080   0.07758   0.06981  -0.0552   0.0097   1.0000
  13.250   1.1098   0.08058   0.07290  -0.0554   0.0091   1.0000
  13.500   1.1107   0.08376   0.07618  -0.0557   0.0086   1.0000
  13.750   1.1108   0.08709   0.07960  -0.0561   0.0082   1.0000
  14.000   1.1099   0.09060   0.08321  -0.0566   0.0080   1.0000
  14.250   1.1089   0.09417   0.08689  -0.0571   0.0077   1.0000
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