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WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il)
Reynolds number: 200,000
Max Cl/Cd: 70.12 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66a175-il-200000.txt
Download as CSV file: xf-fx66a175-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1670   0.10544   0.10122  -0.0790   0.7306   0.0514
 -11.250  -0.1613   0.10248   0.09817  -0.0801   0.7175   0.0540
 -11.000  -0.1612   0.09861   0.09424  -0.0822   0.7080   0.0565
 -10.750  -0.1184   0.08556   0.08131  -0.0804   0.6754   0.0623
 -10.500  -0.1076   0.08327   0.07893  -0.0800   0.6692   0.0640
 -10.250  -0.1042   0.07984   0.07550  -0.0809   0.6635   0.0664
 -10.000  -0.1092   0.07507   0.07073  -0.0830   0.6599   0.0691
  -7.750  -0.2924   0.03520   0.02855  -0.1059   0.6422   0.0334
  -7.500  -0.2792   0.03149   0.02443  -0.1048   0.6376   0.0306
  -7.250  -0.2616   0.02841   0.02082  -0.1035   0.6329   0.0289
  -7.000  -0.2394   0.02647   0.01858  -0.1027   0.6287   0.0289
  -6.750  -0.2164   0.02519   0.01715  -0.1022   0.6245   0.0302
  -6.500  -0.1929   0.02414   0.01598  -0.1016   0.6198   0.0322
  -6.250  -0.1688   0.02298   0.01465  -0.1009   0.6156   0.0335
  -6.000  -0.1447   0.02193   0.01344  -0.1002   0.6123   0.0345
  -5.750  -0.1213   0.02111   0.01257  -0.0994   0.6080   0.0358
  -5.500  -0.1029   0.01967   0.01114  -0.0982   0.6042   0.0386
  -5.250  -0.0799   0.01904   0.01046  -0.0977   0.6007   0.0440
  -4.750  -0.0359   0.01726   0.00860  -0.0965   0.5938   0.0738
  -4.500  -0.0254   0.01511   0.00813  -0.0953   0.5903   0.4184
  -4.250   0.0023   0.01576   0.00860  -0.0948   0.5867   0.4668
  -4.000   0.0298   0.01656   0.00927  -0.0941   0.5838   0.4949
  -3.750   0.0562   0.01722   0.00992  -0.0933   0.5804   0.5152
  -3.500   0.0827   0.01772   0.01041  -0.0926   0.5769   0.5306
  -3.250   0.1094   0.01817   0.01084  -0.0918   0.5738   0.5446
  -3.000   0.1365   0.01844   0.01103  -0.0913   0.5711   0.5544
  -2.500   0.1902   0.01874   0.01119  -0.0908   0.5655   0.5699
  -2.250   0.2175   0.01873   0.01106  -0.0911   0.5624   0.5755
  -2.000   0.2446   0.01870   0.01095  -0.0910   0.5596   0.5797
  -1.750   0.2723   0.01872   0.01088  -0.0911   0.5572   0.5835
  -1.500   0.3008   0.01872   0.01074  -0.0915   0.5551   0.5866
  -1.250   0.3281   0.01877   0.01068  -0.0918   0.5523   0.5903
  -1.000   0.3545   0.01876   0.01067  -0.0918   0.5491   0.5933
  -0.750   0.3815   0.01878   0.01066  -0.0918   0.5463   0.5962
  -0.500   0.4094   0.01881   0.01062  -0.0921   0.5440   0.5988
  -0.250   0.4377   0.01885   0.01055  -0.0925   0.5420   0.6012
   0.000   0.4666   0.01897   0.01054  -0.0930   0.5402   0.6040
   0.250   0.4925   0.01911   0.01069  -0.0930   0.5376   0.6066
   0.500   0.5184   0.01920   0.01083  -0.0930   0.5347   0.6087
   0.750   0.5453   0.01928   0.01091  -0.0931   0.5320   0.6108
   1.000   0.5730   0.01936   0.01094  -0.0933   0.5297   0.6132
   1.250   0.6014   0.01944   0.01096  -0.0937   0.5277   0.6157
   1.500   0.6302   0.01961   0.01103  -0.0941   0.5260   0.6183
   1.750   0.6552   0.01989   0.01137  -0.0941   0.5237   0.6209
   2.000   0.6797   0.02014   0.01172  -0.0939   0.5212   0.6234
   2.250   0.7053   0.02039   0.01202  -0.0938   0.5190   0.6262
   2.500   0.7318   0.02060   0.01225  -0.0939   0.5169   0.6290
   2.750   0.7592   0.02077   0.01242  -0.0942   0.5149   0.6319
   3.000   0.7875   0.02096   0.01255  -0.0945   0.5132   0.6350
   3.250   0.8156   0.02115   0.01275  -0.0949   0.5118   0.6377
   3.500   0.8388   0.02159   0.01333  -0.0945   0.5097   0.6410
   3.750   0.8602   0.02212   0.01399  -0.0940   0.5072   0.6447
   4.000   0.8836   0.02259   0.01455  -0.0937   0.5050   0.6486
   4.250   0.9080   0.02296   0.01500  -0.0936   0.5030   0.6521
   4.500   0.9335   0.02327   0.01541  -0.0936   0.5013   0.6563
   4.750   0.9596   0.02359   0.01578  -0.0936   0.4998   0.6611
   5.000   0.9865   0.02390   0.01612  -0.0938   0.4985   0.6657
   5.250   1.0138   0.02423   0.01653  -0.0941   0.4972   0.6704
   5.500   1.0309   0.02510   0.01760  -0.0930   0.4949   0.6761
   5.750   1.0439   0.02610   0.01883  -0.0915   0.4915   0.6819
   6.000   1.0632   0.02680   0.01969  -0.0908   0.4891   0.6890
   6.250   1.0855   0.02733   0.02035  -0.0904   0.4872   0.6967
   6.500   1.1102   0.02772   0.02088  -0.0903   0.4858   0.7063
   6.750   1.1357   0.02805   0.02133  -0.0903   0.4845   0.7180
   7.000   1.1621   0.02839   0.02181  -0.0904   0.4833   0.7340
   7.250   1.1601   0.03032   0.02410  -0.0872   0.4792   0.7559
   7.500   1.1549   0.03207   0.02633  -0.0836   0.4746   0.8260
   7.750   1.1883   0.03234   0.02681  -0.0853   0.4725   1.0000
   8.000   1.2179   0.03254   0.02703  -0.0858   0.4710   1.0000
   8.250   1.2501   0.03262   0.02715  -0.0866   0.4699   1.0000
   8.500   1.2829   0.03227   0.02682  -0.0872   0.4671   1.0000
   8.750   1.0941   0.04647   0.04127  -0.0687   0.4526   1.0000
   9.000   1.1398   0.04510   0.03998  -0.0695   0.4528   1.0000
   9.250   1.2243   0.03939   0.03435  -0.0722   0.4489   1.0000
   9.500   1.3946   0.01989   0.01379  -0.0787   0.3597   1.0000
   9.750   1.3670   0.02131   0.01478  -0.0708   0.2933   1.0000
  10.000   1.3372   0.02393   0.01715  -0.0648   0.2505   1.0000
  10.250   1.3073   0.02760   0.02068  -0.0609   0.2181   1.0000
  10.500   1.2839   0.03168   0.02472  -0.0590   0.1969   1.0000
  10.750   1.2536   0.03688   0.02984  -0.0575   0.1696   1.0000
  11.000   1.2312   0.04153   0.03446  -0.0566   0.1504   1.0000
  11.250   1.2044   0.04672   0.03955  -0.0557   0.1246   1.0000
  11.500   1.1766   0.05210   0.04480  -0.0550   0.0963   1.0000
  11.750   1.1498   0.05764   0.05015  -0.0546   0.0630   1.0000
  12.000   1.1350   0.06214   0.05454  -0.0545   0.0417   1.0000
  12.250   1.1187   0.06702   0.05931  -0.0544   0.0275   1.0000
  12.500   1.1125   0.07087   0.06321  -0.0544   0.0232   1.0000
  12.750   1.1109   0.07424   0.06671  -0.0545   0.0211   1.0000
  13.000   1.1101   0.07759   0.07016  -0.0546   0.0200   1.0000
  13.250   1.1079   0.08114   0.07382  -0.0549   0.0190   1.0000
  13.500   1.1036   0.08505   0.07782  -0.0553   0.0182   1.0000
  13.750   1.0993   0.08901   0.08188  -0.0557   0.0176   1.0000
  14.000   1.0948   0.09297   0.08593  -0.0562   0.0171   1.0000
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