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WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il)
Reynolds number: 500,000
Max Cl/Cd: 103.29 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66a175-il-500000.txt
Download as CSV file: xf-fx66a175-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.1273   0.11012   0.10653  -0.0687   0.6253   0.0185
 -12.500  -0.1262   0.10566   0.10208  -0.0706   0.6211   0.0185
 -12.250  -0.1385   0.09836   0.09481  -0.0731   0.6193   0.0192
 -12.000  -0.1356   0.09494   0.09135  -0.0742   0.6147   0.0195
 -11.750  -0.1306   0.09213   0.08851  -0.0751   0.6104   0.0200
 -11.500  -0.1299   0.08795   0.08433  -0.0767   0.6066   0.0202
 -11.250  -0.1270   0.08463   0.08100  -0.0779   0.6026   0.0210
 -11.000  -0.1310   0.07936   0.07572  -0.0800   0.5999   0.0214
 -10.750  -0.1363   0.07387   0.07022  -0.0823   0.5975   0.0222
 -10.500  -0.1580   0.06322   0.05961  -0.0874   0.5971   0.0215
  -9.000  -0.3741   0.03454   0.02944  -0.1069   0.5943   0.0122
  -8.750  -0.3752   0.03080   0.02537  -0.1055   0.5905   0.0116
  -8.500  -0.3665   0.02808   0.02228  -0.1042   0.5866   0.0117
  -8.250  -0.3530   0.02568   0.01956  -0.1030   0.5829   0.0116
  -8.000  -0.3351   0.02387   0.01752  -0.1022   0.5789   0.0119
  -7.750  -0.3146   0.02261   0.01605  -0.1015   0.5748   0.0123
  -7.500  -0.2926   0.02170   0.01494  -0.1008   0.5710   0.0127
  -7.250  -0.2721   0.02022   0.01324  -0.1000   0.5675   0.0134
  -7.000  -0.2527   0.01855   0.01149  -0.0991   0.5639   0.0141
  -6.750  -0.2307   0.01764   0.01053  -0.0984   0.5603   0.0147
  -6.500  -0.2082   0.01692   0.00971  -0.0978   0.5569   0.0153
  -6.250  -0.1850   0.01632   0.00901  -0.0972   0.5536   0.0161
  -6.000  -0.1616   0.01565   0.00829  -0.0967   0.5501   0.0169
  -5.750  -0.1364   0.01525   0.00783  -0.0964   0.5467   0.0181
  -5.500  -0.1143   0.01441   0.00686  -0.0958   0.5436   0.0196
  -5.250  -0.0904   0.01384   0.00618  -0.0954   0.5406   0.0215
  -5.000  -0.0646   0.01343   0.00571  -0.0952   0.5378   0.0238
  -4.750  -0.0385   0.01303   0.00523  -0.0950   0.5349   0.0273
  -4.500  -0.0135   0.01243   0.00466  -0.0947   0.5320   0.0471
  -4.250   0.0074   0.01117   0.00400  -0.0945   0.5295   0.1943
  -4.000   0.0287   0.01012   0.00362  -0.0942   0.5270   0.3877
  -3.750   0.0568   0.01024   0.00376  -0.0942   0.5244   0.4366
  -3.500   0.0855   0.01039   0.00385  -0.0943   0.5218   0.4571
  -3.250   0.1139   0.01058   0.00398  -0.0943   0.5192   0.4720
  -3.000   0.1422   0.01075   0.00410  -0.0943   0.5167   0.4826
  -2.750   0.1704   0.01094   0.00420  -0.0942   0.5143   0.4928
  -2.500   0.1988   0.01120   0.00436  -0.0943   0.5120   0.5021
  -2.250   0.2269   0.01129   0.00446  -0.0943   0.5098   0.5089
  -2.000   0.2552   0.01139   0.00453  -0.0943   0.5075   0.5152
  -1.750   0.2837   0.01145   0.00449  -0.0945   0.5052   0.5184
  -1.500   0.3120   0.01139   0.00442  -0.0947   0.5029   0.5210
  -1.250   0.3403   0.01141   0.00441  -0.0948   0.5007   0.5237
  -1.000   0.3688   0.01147   0.00440  -0.0950   0.4986   0.5262
  -0.750   0.3974   0.01157   0.00441  -0.0953   0.4963   0.5282
  -0.500   0.4256   0.01155   0.00438  -0.0955   0.4943   0.5301
  -0.250   0.4540   0.01158   0.00437  -0.0957   0.4921   0.5320
   0.000   0.4823   0.01158   0.00434  -0.0959   0.4899   0.5336
   0.250   0.5105   0.01156   0.00431  -0.0960   0.4878   0.5351
   0.500   0.5387   0.01157   0.00430  -0.0962   0.4857   0.5366
   0.750   0.5670   0.01164   0.00432  -0.0965   0.4836   0.5382
   1.000   0.5953   0.01173   0.00439  -0.0967   0.4815   0.5399
   1.250   0.6232   0.01175   0.00443  -0.0968   0.4796   0.5417
   1.500   0.6512   0.01179   0.00448  -0.0970   0.4776   0.5435
   1.750   0.6793   0.01184   0.00452  -0.0972   0.4757   0.5452
   2.000   0.7074   0.01190   0.00457  -0.0974   0.4738   0.5470
   2.250   0.7354   0.01193   0.00459  -0.0976   0.4720   0.5489
   2.500   0.7634   0.01199   0.00466  -0.0978   0.4703   0.5509
   2.750   0.7918   0.01215   0.00480  -0.0981   0.4684   0.5528
   3.000   0.8194   0.01223   0.00492  -0.0983   0.4670   0.5547
   3.250   0.8469   0.01229   0.00505  -0.0984   0.4654   0.5568
   3.500   0.8745   0.01238   0.00517  -0.0985   0.4637   0.5590
   3.750   0.9022   0.01248   0.00529  -0.0987   0.4621   0.5611
   4.000   0.9298   0.01256   0.00541  -0.0988   0.4605   0.5634
   4.250   0.9574   0.01264   0.00554  -0.0990   0.4590   0.5660
   4.500   0.9851   0.01275   0.00568  -0.0992   0.4576   0.5688
   4.750   1.0130   0.01288   0.00584  -0.0994   0.4562   0.5720
   5.000   1.0412   0.01310   0.00607  -0.0998   0.4547   0.5749
   5.250   1.0686   0.01329   0.00631  -0.1000   0.4534   0.5776
   5.500   1.0950   0.01338   0.00652  -0.0999   0.4521   0.5806
   5.750   1.1215   0.01351   0.00675  -0.0999   0.4507   0.5842
   6.000   1.1482   0.01366   0.00699  -0.1000   0.4492   0.5882
   6.250   1.1750   0.01380   0.00722  -0.1001   0.4477   0.5922
   6.500   1.2016   0.01392   0.00743  -0.1001   0.4461   0.5964
   6.750   1.2286   0.01404   0.00763  -0.1002   0.4444   0.6014
   7.000   1.2561   0.01408   0.00764  -0.1003   0.4402   0.6068
   7.250   1.2759   0.01375   0.00749  -0.0989   0.4328   0.6125
   7.500   1.3001   0.01363   0.00732  -0.0983   0.4253   0.6199
   7.750   1.3208   0.01344   0.00736  -0.0971   0.4188   0.6282
   8.000   1.3424   0.01333   0.00730  -0.0961   0.4104   0.6389
   8.250   1.3613   0.01318   0.00727  -0.0945   0.3955   0.6532
   8.500   1.3577   0.01389   0.00764  -0.0892   0.3157   0.6713
   8.750   1.3309   0.01578   0.00916  -0.0806   0.2367   0.6978
   9.000   1.2956   0.01773   0.01115  -0.0712   0.1770   0.8165
   9.250   1.2693   0.02071   0.01404  -0.0661   0.1195   1.0000
   9.500   1.2475   0.02383   0.01707  -0.0625   0.0891   1.0000
   9.750   1.2158   0.02877   0.02189  -0.0602   0.0528   1.0000
  10.000   1.1913   0.03360   0.02665  -0.0589   0.0255   1.0000
  10.250   1.1744   0.03777   0.03083  -0.0579   0.0139   1.0000
  10.500   1.1687   0.04091   0.03404  -0.0571   0.0115   1.0000
  10.750   1.1658   0.04377   0.03699  -0.0565   0.0098   1.0000
  11.000   1.1634   0.04661   0.03989  -0.0560   0.0091   1.0000
  11.250   1.1592   0.04968   0.04304  -0.0555   0.0085   1.0000
  11.500   1.1523   0.05313   0.04659  -0.0551   0.0079   1.0000
  11.750   1.1494   0.05629   0.04983  -0.0548   0.0077   1.0000
  12.000   1.1518   0.05892   0.05253  -0.0547   0.0075   1.0000
  12.250   1.1501   0.06209   0.05578  -0.0546   0.0074   1.0000
  12.500   1.1499   0.06513   0.05889  -0.0546   0.0072   1.0000
  12.750   1.1492   0.06831   0.06214  -0.0547   0.0068   1.0000
  13.000   1.1491   0.07142   0.06532  -0.0548   0.0067   1.0000
  13.250   1.1486   0.07465   0.06861  -0.0549   0.0064   1.0000
  13.500   1.1480   0.07793   0.07195  -0.0552   0.0060   1.0000
  13.750   1.1473   0.08127   0.07536  -0.0554   0.0060   1.0000
  14.000   1.1477   0.08445   0.07861  -0.0557   0.0058   1.0000
  14.250   1.1454   0.08804   0.08225  -0.0561   0.0056   1.0000
  14.500   1.1505   0.09068   0.08496  -0.0564   0.0059   1.0000
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