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WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il)
Reynolds number: 100,000
Max Cl/Cd: 34.23 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66a175-il-100000-n5.txt
Download as CSV file: xf-fx66a175-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2195   0.09538   0.09001  -0.0753   0.7312   0.0214
 -11.000  -0.2255   0.08890   0.08350  -0.0787   0.7215   0.0212
 -10.750  -0.2723   0.07264   0.06718  -0.0890   0.7229   0.0194
  -9.750  -0.3429   0.05241   0.04601  -0.1032   0.6897   0.0185
  -9.500  -0.3566   0.04949   0.04283  -0.1036   0.6826   0.0185
  -9.250  -0.3626   0.04668   0.03979  -0.1033   0.6753   0.0186
  -9.000  -0.3625   0.04374   0.03657  -0.1032   0.6691   0.0190
  -8.750  -0.3556   0.04161   0.03429  -0.1030   0.6621   0.0197
  -8.500  -0.3444   0.03991   0.03237  -0.1028   0.6563   0.0207
  -8.250  -0.3321   0.03804   0.03024  -0.1023   0.6502   0.0217
  -8.000  -0.3180   0.03604   0.02790  -0.1017   0.6446   0.0227
  -7.750  -0.3011   0.03398   0.02546  -0.1011   0.6397   0.0231
  -7.500  -0.2819   0.03207   0.02323  -0.1004   0.6338   0.0238
  -7.250  -0.2607   0.03044   0.02130  -0.0996   0.6286   0.0245
  -7.000  -0.2386   0.02905   0.01967  -0.0988   0.6235   0.0254
  -6.750  -0.2174   0.02768   0.01819  -0.0980   0.6183   0.0267
  -6.500  -0.1974   0.02661   0.01709  -0.0973   0.6139   0.0291
  -6.250  -0.1763   0.02579   0.01619  -0.0966   0.6093   0.0319
  -6.000  -0.1556   0.02495   0.01525  -0.0956   0.6045   0.0343
  -5.750  -0.1356   0.02410   0.01426  -0.0946   0.6005   0.0369
  -5.500  -0.1151   0.02333   0.01337  -0.0939   0.5969   0.0423
  -5.250  -0.0940   0.02258   0.01257  -0.0934   0.5923   0.0510
  -5.000  -0.0728   0.02170   0.01168  -0.0929   0.5884   0.0684
  -4.750  -0.0541   0.02032   0.01068  -0.0927   0.5852   0.1488
  -4.500  -0.0387   0.01925   0.01087  -0.0916   0.5821   0.3883
  -4.250  -0.0121   0.01983   0.01128  -0.0911   0.5781   0.4567
  -4.000   0.0137   0.02058   0.01184  -0.0902   0.5746   0.4908
  -3.750   0.0396   0.02121   0.01237  -0.0890   0.5715   0.5122
  -3.500   0.0661   0.02156   0.01255  -0.0883   0.5690   0.5271
  -3.250   0.0918   0.02172   0.01259  -0.0879   0.5654   0.5372
  -3.000   0.1182   0.02175   0.01245  -0.0877   0.5619   0.5446
  -2.750   0.1449   0.02173   0.01226  -0.0877   0.5587   0.5502
  -2.500   0.1721   0.02172   0.01208  -0.0876   0.5560   0.5548
  -2.250   0.1995   0.02167   0.01183  -0.0878   0.5533   0.5591
  -2.000   0.2257   0.02166   0.01170  -0.0879   0.5498   0.5632
  -1.750   0.2522   0.02168   0.01165  -0.0878   0.5468   0.5664
  -1.500   0.2792   0.02169   0.01154  -0.0879   0.5442   0.5697
  -1.250   0.3069   0.02169   0.01137  -0.0881   0.5419   0.5728
  -1.000   0.3352   0.02170   0.01118  -0.0885   0.5400   0.5761
  -0.750   0.3606   0.02180   0.01128  -0.0884   0.5370   0.5786
  -0.500   0.3866   0.02190   0.01135  -0.0884   0.5342   0.5810
  -0.250   0.4131   0.02199   0.01139  -0.0885   0.5317   0.5834
   0.000   0.4403   0.02207   0.01138  -0.0886   0.5294   0.5860
   0.250   0.4680   0.02214   0.01133  -0.0889   0.5273   0.5890
   0.500   0.4960   0.02222   0.01130  -0.0892   0.5254   0.5921
   0.750   0.5198   0.02246   0.01162  -0.0889   0.5222   0.5945
   1.000   0.5449   0.02267   0.01186  -0.0888   0.5195   0.5972
   1.250   0.5708   0.02286   0.01204  -0.0888   0.5172   0.5999
   1.500   0.5976   0.02305   0.01218  -0.0889   0.5152   0.6029
   1.750   0.6251   0.02321   0.01228  -0.0892   0.5133   0.6063
   2.000   0.6528   0.02333   0.01239  -0.0894   0.5117   0.6092
   2.250   0.6759   0.02368   0.01282  -0.0890   0.5090   0.6123
   2.500   0.6985   0.02407   0.01329  -0.0886   0.5060   0.6157
   2.750   0.7229   0.02439   0.01366  -0.0885   0.5034   0.6195
   3.000   0.7480   0.02464   0.01395  -0.0883   0.5012   0.6229
   3.250   0.7742   0.02484   0.01417  -0.0883   0.4993   0.6266
   3.500   0.8012   0.02505   0.01438  -0.0885   0.4978   0.6306
   3.750   0.8278   0.02536   0.01471  -0.0886   0.4963   0.6347
   4.000   0.8449   0.02612   0.01568  -0.0876   0.4933   0.6385
   4.250   0.8650   0.02674   0.01643  -0.0870   0.4905   0.6431
   4.500   0.8875   0.02723   0.01700  -0.0866   0.4881   0.6485
   4.750   0.9118   0.02759   0.01746  -0.0865   0.4861   0.6534
   5.000   0.9378   0.02788   0.01782  -0.0865   0.4845   0.6591
   5.250   0.9646   0.02818   0.01817  -0.0867   0.4831   0.6654
   5.500   0.9847   0.02883   0.01901  -0.0861   0.4812   0.6718
   6.000   1.0045   0.03126   0.02189  -0.0827   0.4748   0.6872
   6.250   1.0225   0.03200   0.02279  -0.0819   0.4727   0.6981
   6.500   1.0440   0.03250   0.02345  -0.0814   0.4710   0.7123
   6.750   1.0684   0.03278   0.02393  -0.0812   0.4695   0.7324
   7.250   1.0431   0.03728   0.02926  -0.0735   0.4601   1.0000
   7.500   1.0501   0.03869   0.03072  -0.0718   0.4575   1.0000
   7.750   1.0706   0.03937   0.03145  -0.0714   0.4559   1.0000
   8.000   1.0981   0.03965   0.03178  -0.0716   0.4547   1.0000
   9.000   0.9215   0.06588   0.05820  -0.0636   0.4140   1.0000
   9.250   0.9448   0.06632   0.05871  -0.0634   0.4126   1.0000
   9.500   0.9692   0.06668   0.05916  -0.0631   0.4115   1.0000
  10.000   0.9628   0.07296   0.06557  -0.0627   0.3986   1.0000
  10.500   0.9621   0.07874   0.07154  -0.0625   0.3860   1.0000
  10.750   0.9859   0.07903   0.07196  -0.0621   0.3845   1.0000
  11.250   0.9856   0.08492   0.07804  -0.0621   0.3715   1.0000
  11.500   1.0110   0.08491   0.07817  -0.0617   0.3700   1.0000
  12.000   1.0182   0.08968   0.08317  -0.0616   0.3566   1.0000
  12.500   1.0621   0.08791   0.08175  -0.0599   0.3411   1.0000
  13.000   1.0783   0.08830   0.08231  -0.0588   0.2977   1.0000
  13.500   1.0777   0.09129   0.08347  -0.0574   0.0947   1.0000
  13.750   1.0552   0.09764   0.08934  -0.0585   0.0463   1.0000
  14.000   1.0469   0.10219   0.09372  -0.0592   0.0299   1.0000
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