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WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 66-17A-175 AIRFOIL (fx66a175-il)
Reynolds number: 100,000
Max Cl/Cd: 12.65 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66a175-il-100000.txt
Download as CSV file: xf-fx66a175-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.2539   0.13080   0.12670  -0.0446   1.0000   0.0963
 -11.750  -0.2731   0.12840   0.12445  -0.0493   1.0000   0.1004
 -11.500  -0.2726   0.12416   0.12037  -0.0509   1.0000   0.1020
 -11.250  -0.2267   0.11873   0.11495  -0.0538   0.9376   0.1077
 -11.000  -0.2430   0.11345   0.10965  -0.0697   0.9037   0.1150
 -10.750  -0.1694   0.10639   0.10216  -0.0745   0.8560   0.1269
 -10.500  -0.1617   0.10163   0.09720  -0.0796   0.8290   0.1314
 -10.250  -0.1561   0.09897   0.09439  -0.0822   0.8086   0.1423
 -10.000  -0.1367   0.09531   0.09060  -0.0822   0.7922   0.1480
  -9.750  -0.1624   0.09243   0.08775  -0.0880   0.7829   0.1575
  -9.500  -0.1272   0.08880   0.08396  -0.0856   0.7699   0.1620
  -9.250  -0.1461   0.08550   0.08073  -0.0895   0.7614   0.1732
  -9.000  -0.1205   0.08241   0.07752  -0.0883   0.7515   0.1764
  -8.750  -0.1171   0.07926   0.07431  -0.0893   0.7439   0.1816
  -8.500  -0.2298   0.04279   0.03796  -0.1069   0.7344   0.0829
  -8.250  -0.2816   0.04957   0.04388  -0.1130   0.7427   0.0688
  -8.000  -0.2925   0.04659   0.03990  -0.1116   0.7356   0.0604
  -7.750  -0.2775   0.04275   0.03583  -0.1113   0.7292   0.0591
  -7.500  -0.2642   0.03964   0.03242  -0.1107   0.7222   0.0582
  -7.250  -0.2478   0.03674   0.02915  -0.1099   0.7160   0.0566
  -7.000  -0.2289   0.03427   0.02629  -0.1090   0.7100   0.0556
  -6.750  -0.2076   0.03218   0.02385  -0.1081   0.7039   0.0555
  -6.500  -0.1833   0.03042   0.02174  -0.1072   0.6990   0.0563
  -6.250  -0.1601   0.02925   0.02036  -0.1064   0.6925   0.0590
  -6.000  -0.1366   0.02762   0.01872  -0.1056   0.6874   0.0633
  -5.750  -0.1134   0.02658   0.01766  -0.1046   0.6828   0.0680
  -5.500  -0.0917   0.02580   0.01687  -0.1032   0.6775   0.0737
  -5.250  -0.0728   0.02492   0.01609  -0.1018   0.6732   0.0861
  -5.000  -0.0558   0.02378   0.01507  -0.1005   0.6697   0.1126
  -4.750  -0.0524   0.02241   0.01557  -0.0977   0.6653   0.4569
  -4.500  -0.0290   0.02475   0.01788  -0.0943   0.6606   0.5129
  -4.250  -0.0052   0.02634   0.01940  -0.0912   0.6568   0.5440
  -4.000   0.0150   0.02779   0.02088  -0.0875   0.6524   0.5699
  -3.750   0.0350   0.02854   0.02156  -0.0850   0.6478   0.5924
  -3.500   0.0571   0.02900   0.02192  -0.0827   0.6441   0.6086
  -3.250   0.0806   0.02918   0.02191  -0.0814   0.6412   0.6227
  -3.000   0.0996   0.02943   0.02212  -0.0803   0.6370   0.6336
  -2.750   0.1203   0.02955   0.02218  -0.0791   0.6333   0.6418
  -2.500   0.1454   0.02943   0.02185  -0.0797   0.6301   0.6503
  -2.250   0.1703   0.02939   0.02167  -0.0791   0.6276   0.6558
  -2.000   0.1916   0.02960   0.02179  -0.0793   0.6242   0.6630
  -1.750   0.2106   0.02986   0.02203  -0.0786   0.6201   0.6680
  -1.500   0.2344   0.02994   0.02201  -0.0786   0.6166   0.6727
  -1.250   0.2624   0.02991   0.02179  -0.0796   0.6139   0.6772
  -1.000   0.2888   0.03002   0.02175  -0.0800   0.6117   0.6810
  -0.750   0.3013   0.03089   0.02273  -0.0790   0.6078   0.6846
  -0.500   0.3207   0.03146   0.02326  -0.0790   0.6043   0.6885
  -0.250   0.3457   0.03178   0.02347  -0.0796   0.6014   0.6927
   0.000   0.3733   0.03187   0.02344  -0.0800   0.5991   0.6957
   0.250   0.3924   0.03259   0.02414  -0.0798   0.5964   0.6984
   0.500   0.3936   0.03445   0.02613  -0.0783   0.5917   0.7014
   0.750   0.4098   0.03543   0.02708  -0.0781   0.5884   0.7049
   1.000   0.4341   0.03604   0.02759  -0.0786   0.5861   0.7082
   1.250   0.4604   0.03640   0.02790  -0.0789   0.5845   0.7109
   1.500   0.4426   0.03983   0.03148  -0.0763   0.5809   0.7133
   1.750   0.2576   0.05661   0.04873  -0.0688   0.6262   0.7126
   2.000   0.2804   0.05657   0.04862  -0.0681   0.6112   0.7159
   2.250   0.2112   0.06272   0.05492  -0.0662   0.6576   0.7171
   2.500   0.2474   0.06457   0.05669  -0.0683   0.6559   0.7211
   2.750   0.2362   0.06499   0.05708  -0.0655   0.6452   0.7239
   3.000   0.2696   0.06648   0.05854  -0.0668   0.6423   0.7282
   3.250   0.2646   0.06742   0.05947  -0.0649   0.6338   0.7315
   3.500   0.2909   0.06877   0.06077  -0.0659   0.6296   0.7358
   3.750   0.3267   0.07060   0.06258  -0.0676   0.6273   0.7404
   4.000   0.3181   0.07137   0.06336  -0.0656   0.6175   0.7441
   4.250   0.3480   0.07298   0.06492  -0.0669   0.6143   0.7502
   4.500   0.3841   0.07511   0.06706  -0.0688   0.6126   0.7566
   4.750   0.3719   0.07574   0.06771  -0.0667   0.6021   0.7613
   5.000   0.4051   0.07753   0.06951  -0.0682   0.5992   0.7691
   5.250   0.4426   0.07998   0.07200  -0.0702   0.5978   0.7788
   5.500   0.4236   0.08038   0.07246  -0.0678   0.5870   0.7852
   5.750   0.4566   0.08232   0.07447  -0.0693   0.5845   0.7978
   6.000   0.4502   0.08358   0.07584  -0.0682   0.5758   0.8095
   6.250   0.4769   0.08514   0.07762  -0.0693   0.5717   0.8378
   6.500   0.5132   0.08723   0.07991  -0.0715   0.5696   1.0000
   6.750   0.5012   0.08853   0.08119  -0.0705   0.5599   1.0000
   7.000   0.5327   0.09064   0.08326  -0.0722   0.5563   1.0000
   7.250   0.5706   0.09352   0.08612  -0.0744   0.5546   1.0000
   7.500   0.5520   0.09444   0.08704  -0.0728   0.5438   1.0000
   7.750   0.5859   0.09685   0.08941  -0.0743   0.5410   1.0000
   8.000   0.5744   0.09853   0.09111  -0.0734   0.5322   1.0000
   8.250   0.6015   0.10057   0.09313  -0.0742   0.5279   1.0000
   8.500   0.6380   0.10349   0.09609  -0.0756   0.5260   1.0000
   8.750   0.6166   0.10472   0.09733  -0.0743   0.5157   1.0000
   9.000   0.6463   0.10710   0.09974  -0.0752   0.5126   1.0000
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