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FX 66-H-60 (fx66h60-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 66-H-60 (fx66h60-il)
Reynolds number: 100,000
Max Cl/Cd: 40.05 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66h60-il-100000-n5.txt
Download as CSV file: xf-fx66h60-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-H-60                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6220   0.10988   0.10531   0.0249   1.0000   0.0306
  -8.250  -0.6222   0.10606   0.10153   0.0216   1.0000   0.0307
  -8.000  -0.6208   0.10234   0.09782   0.0193   1.0000   0.0307
  -7.750  -0.6163   0.09840   0.09386   0.0170   1.0000   0.0308
  -7.500  -0.6107   0.09441   0.08983   0.0149   1.0000   0.0308
  -7.250  -0.6088   0.08757   0.08309   0.0148   1.0000   0.0315
  -7.000  -0.6030   0.08280   0.07835   0.0151   1.0000   0.0323
  -6.750  -0.5959   0.07867   0.07422   0.0146   1.0000   0.0331
  -6.500  -0.5874   0.07469   0.07021   0.0134   1.0000   0.0339
  -6.250  -0.5774   0.07068   0.06614   0.0122   1.0000   0.0348
  -6.000  -0.5656   0.06675   0.06212   0.0109   1.0000   0.0359
  -5.750  -0.5519   0.06282   0.05809   0.0098   1.0000   0.0371
  -5.500  -0.5362   0.05897   0.05408   0.0089   1.0000   0.0386
  -5.250  -0.5093   0.05775   0.05220   0.0078   1.0000   0.0436
  -4.750  -0.4770   0.04819   0.04239   0.0078   1.0000   0.0448
  -4.500  -0.4625   0.04472   0.03904   0.0079   1.0000   0.0512
  -4.000  -0.4094   0.03689   0.03027   0.0103   1.0000   0.0295
  -3.750  -0.3879   0.03336   0.02650   0.0109   1.0000   0.0275
  -3.500  -0.3636   0.03034   0.02304   0.0119   1.0000   0.0259
  -3.250  -0.3380   0.02763   0.01995   0.0129   1.0000   0.0247
  -3.000  -0.3116   0.02520   0.01713   0.0139   1.0000   0.0237
  -2.750  -0.2845   0.02301   0.01456   0.0149   1.0000   0.0229
  -2.500  -0.2571   0.02109   0.01232   0.0158   1.0000   0.0225
  -2.250  -0.2297   0.01941   0.01042   0.0165   1.0000   0.0224
  -2.000  -0.2027   0.01795   0.00883   0.0172   1.0000   0.0228
  -1.750  -0.1766   0.01668   0.00752   0.0180   1.0000   0.0236
  -1.500  -0.1331   0.01548   0.00612   0.0151   0.8532   0.0265
  -1.250  -0.1032   0.01502   0.00524   0.0153   0.7603   0.0364
  -1.000  -0.0790   0.01460   0.00443   0.0168   0.7018   0.0455
  -0.750   0.0272   0.01166   0.00393   0.0035   0.6270   1.0000
  -0.500   0.0512   0.01177   0.00365   0.0043   0.5899   1.0000
  -0.250   0.0753   0.01187   0.00340   0.0051   0.5582   1.0000
   0.250   0.1238   0.01208   0.00311   0.0066   0.5076   1.0000
   0.500   0.1473   0.01221   0.00302   0.0074   0.4869   1.0000
   0.750   0.1709   0.01234   0.00298   0.0083   0.4681   1.0000
   1.000   0.1949   0.01248   0.00297   0.0090   0.4512   1.0000
   1.250   0.2190   0.01262   0.00297   0.0097   0.4360   1.0000
   1.500   0.2431   0.01278   0.00301   0.0104   0.4220   1.0000
   1.750   0.2670   0.01295   0.00308   0.0111   0.4090   1.0000
   2.000   0.2909   0.01312   0.00319   0.0119   0.3969   1.0000
   2.250   0.3148   0.01331   0.00332   0.0126   0.3858   1.0000
   2.500   0.3387   0.01352   0.00352   0.0133   0.3758   1.0000
   2.750   0.3624   0.01375   0.00369   0.0141   0.3663   1.0000
   3.000   0.3865   0.01397   0.00392   0.0148   0.3564   1.0000
   3.250   0.4106   0.01422   0.00417   0.0155   0.3479   1.0000
   3.500   0.4345   0.01449   0.00444   0.0162   0.3402   1.0000
   3.750   0.4588   0.01476   0.00478   0.0169   0.3317   1.0000
   4.000   0.4828   0.01506   0.00520   0.0176   0.3247   1.0000
   4.250   0.5071   0.01537   0.00563   0.0182   0.3172   1.0000
   4.500   0.5313   0.01571   0.00603   0.0189   0.3110   1.0000
   4.750   0.5557   0.01606   0.00653   0.0195   0.3036   1.0000
   5.000   0.5800   0.01644   0.00702   0.0201   0.2977   1.0000
   5.250   0.6046   0.01684   0.00765   0.0207   0.2910   1.0000
   5.500   0.6290   0.01726   0.00820   0.0214   0.2854   1.0000
   5.750   0.6530   0.01728   0.00862   0.0221   0.2662   1.0000
   6.000   0.6765   0.01689   0.00833   0.0228   0.2169   1.0000
   6.250   0.6926   0.01931   0.00967   0.0231   0.0393   1.0000
   6.500   0.7133   0.02112   0.01170   0.0239   0.0278   1.0000
   6.750   0.7342   0.02268   0.01362   0.0246   0.0237   1.0000
   7.000   0.7516   0.02470   0.01588   0.0252   0.0193   1.0000
   7.250   0.7707   0.02620   0.01760   0.0260   0.0166   1.0000
   7.500   0.7886   0.02795   0.01953   0.0271   0.0156   1.0000
   7.750   0.8064   0.02994   0.02169   0.0283   0.0149   1.0000
   8.000   0.8244   0.03215   0.02421   0.0294   0.0144   1.0000
   8.250   0.8416   0.03477   0.02711   0.0304   0.0140   1.0000
   8.500   0.8569   0.03772   0.03040   0.0312   0.0137   1.0000
   8.750   0.8692   0.04098   0.03406   0.0318   0.0135   1.0000
   9.000   0.8771   0.04459   0.03808   0.0320   0.0135   1.0000
   9.250   0.8798   0.04845   0.04235   0.0319   0.0134   1.0000
   9.500   0.8770   0.05244   0.04669   0.0311   0.0135   1.0000
   9.750   0.8675   0.05654   0.05105   0.0297   0.0136   1.0000
  10.000   0.8536   0.06115   0.05582   0.0260   0.0137   1.0000
  10.250   0.8409   0.06673   0.06155   0.0209   0.0138   1.0000
  10.500   0.8258   0.07349   0.06843   0.0151   0.0139   1.0000
  10.750   0.8114   0.08053   0.07555   0.0095   0.0141   1.0000
  11.000   0.7970   0.08803   0.08310   0.0042   0.0143   1.0000
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