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WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il)
Reynolds number: 1,000,000
Max Cl/Cd: 133.1 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w153-il-1000000.txt
Download as CSV file: xf-fx77w153-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 77-W-153 AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2943   0.08490   0.08148  -0.0122   0.4088   0.0196
  -8.750  -0.2946   0.08081   0.07740  -0.0137   0.4080   0.0199
  -8.500  -0.5771   0.03617   0.03180  -0.0330   0.4278   0.0154
  -8.250  -0.5791   0.03111   0.02635  -0.0312   0.4251   0.0150
  -8.000  -0.5828   0.02491   0.01946  -0.0282   0.4234   0.0146
  -7.750  -0.5714   0.02131   0.01537  -0.0261   0.4206   0.0143
  -7.500  -0.5519   0.01938   0.01313  -0.0249   0.4171   0.0142
  -7.250  -0.5290   0.01819   0.01173  -0.0241   0.4137   0.0142
  -7.000  -0.5049   0.01727   0.01064  -0.0234   0.4100   0.0142
  -6.750  -0.4800   0.01648   0.00972  -0.0228   0.4081   0.0143
  -6.500  -0.4549   0.01570   0.00883  -0.0221   0.4065   0.0144
  -6.250  -0.4295   0.01500   0.00801  -0.0215   0.4046   0.0144
  -6.000  -0.4037   0.01440   0.00732  -0.0210   0.4026   0.0144
  -5.750  -0.3775   0.01389   0.00672  -0.0205   0.4006   0.0144
  -5.500  -0.3511   0.01344   0.00619  -0.0201   0.3987   0.0145
  -5.250  -0.3245   0.01305   0.00573  -0.0197   0.3967   0.0146
  -5.000  -0.2976   0.01273   0.00534  -0.0193   0.3947   0.0147
  -4.750  -0.2706   0.01244   0.00498  -0.0190   0.3931   0.0148
  -4.500  -0.2432   0.01215   0.00465  -0.0187   0.3925   0.0150
  -4.250  -0.2156   0.01189   0.00435  -0.0184   0.3918   0.0152
  -4.000  -0.1881   0.01162   0.00405  -0.0181   0.3911   0.0156
  -3.750  -0.1603   0.01142   0.00384  -0.0179   0.3904   0.0163
  -3.500  -0.1320   0.01128   0.00372  -0.0178   0.3896   0.0174
  -3.250  -0.1037   0.01117   0.00361  -0.0177   0.3887   0.0189
  -3.000  -0.0749   0.01113   0.00359  -0.0177   0.3877   0.0215
  -2.750  -0.0464   0.01107   0.00352  -0.0176   0.3868   0.0238
  -2.500  -0.0176   0.01104   0.00347  -0.0176   0.3860   0.0261
  -2.250   0.0104   0.01089   0.00331  -0.0175   0.3853   0.0281
  -2.000   0.0385   0.01077   0.00319  -0.0174   0.3846   0.0298
  -1.750   0.0669   0.01070   0.00309  -0.0174   0.3838   0.0311
  -1.500   0.0952   0.01060   0.00298  -0.0173   0.3829   0.0323
  -1.250   0.1233   0.01051   0.00287  -0.0173   0.3818   0.0337
  -1.000   0.1516   0.01045   0.00280  -0.0172   0.3805   0.0352
  -0.750   0.1799   0.01043   0.00276  -0.0172   0.3791   0.0365
  -0.500   0.2080   0.01044   0.00277  -0.0172   0.3774   0.0384
  -0.250   0.2366   0.01036   0.00271  -0.0172   0.3767   0.0407
   0.000   0.2653   0.01029   0.00266  -0.0172   0.3759   0.0437
   0.250   0.2939   0.01024   0.00263  -0.0173   0.3750   0.0495
   0.500   0.3222   0.01015   0.00259  -0.0173   0.3742   0.0628
   0.750   0.3498   0.00997   0.00257  -0.0172   0.3735   0.1165
   1.000   0.3771   0.00977   0.00257  -0.0171   0.3728   0.1855
   1.250   0.4037   0.00950   0.00258  -0.0169   0.3720   0.2867
   1.500   0.4294   0.00916   0.00259  -0.0166   0.3712   0.4121
   1.750   0.4524   0.00861   0.00261  -0.0158   0.3704   0.6027
   2.000   0.4700   0.00792   0.00263  -0.0136   0.3695   0.8158
   2.250   0.5200   0.00785   0.00292  -0.0178   0.3682   0.9574
   2.500   0.5555   0.00803   0.00307  -0.0192   0.3670   0.9760
   2.750   0.5969   0.00819   0.00319  -0.0221   0.3658   0.9821
   3.000   0.6398   0.00835   0.00330  -0.0253   0.3643   0.9856
   3.250   0.6804   0.00856   0.00346  -0.0280   0.3626   0.9900
   3.500   0.7261   0.00870   0.00358  -0.0318   0.3614   0.9937
   3.750   0.7711   0.00873   0.00360  -0.0355   0.3606   0.9963
   4.000   0.8219   0.00876   0.00363  -0.0405   0.3595   1.0000
   4.250   0.8487   0.00881   0.00368  -0.0403   0.3584   1.0000
   4.500   0.8754   0.00886   0.00374  -0.0401   0.3571   1.0000
   4.750   0.9021   0.00891   0.00379  -0.0399   0.3556   1.0000
   5.000   0.9288   0.00897   0.00384  -0.0398   0.3542   1.0000
   5.250   0.9554   0.00905   0.00392  -0.0396   0.3528   1.0000
   5.500   0.9818   0.00913   0.00400  -0.0394   0.3513   1.0000
   5.750   1.0081   0.00925   0.00410  -0.0392   0.3496   1.0000
   6.000   1.0342   0.00944   0.00427  -0.0390   0.3474   1.0000
   6.250   1.0603   0.00955   0.00440  -0.0388   0.3454   1.0000
   6.500   1.0869   0.00952   0.00441  -0.0386   0.3435   1.0000
   6.750   1.1134   0.00950   0.00442  -0.0384   0.3406   1.0000
   7.000   1.1399   0.00950   0.00442  -0.0382   0.3370   1.0000
   7.250   1.1658   0.00956   0.00446  -0.0380   0.3331   1.0000
   7.500   1.1916   0.00966   0.00457  -0.0377   0.3299   1.0000
   7.750   1.2181   0.00968   0.00464  -0.0376   0.3273   1.0000
   8.000   1.2445   0.00971   0.00470  -0.0374   0.3233   1.0000
   8.250   1.2705   0.00975   0.00475  -0.0372   0.3183   1.0000
   8.500   1.2964   0.00982   0.00483  -0.0370   0.3118   1.0000
   8.750   1.3217   0.00993   0.00490  -0.0367   0.3019   1.0000
   9.000   1.3459   0.01015   0.00507  -0.0363   0.2930   1.0000
   9.250   1.3693   0.01043   0.00532  -0.0358   0.2842   1.0000
   9.500   1.3921   0.01074   0.00561  -0.0352   0.2759   1.0000
   9.750   1.4151   0.01101   0.00588  -0.0346   0.2686   1.0000
  10.000   1.4370   0.01137   0.00620  -0.0339   0.2578   1.0000
  10.250   1.4585   0.01172   0.00654  -0.0331   0.2475   1.0000
  10.500   1.4790   0.01214   0.00692  -0.0322   0.2388   1.0000
  10.750   1.4987   0.01257   0.00733  -0.0312   0.2312   1.0000
  11.000   1.5189   0.01295   0.00771  -0.0303   0.2245   1.0000
  11.250   1.5366   0.01346   0.00820  -0.0290   0.2143   1.0000
  11.500   1.5539   0.01397   0.00868  -0.0277   0.2016   1.0000
  11.750   1.5662   0.01472   0.00935  -0.0257   0.1869   1.0000
  12.000   1.5773   0.01549   0.01006  -0.0235   0.1744   1.0000
  12.250   1.5892   0.01616   0.01072  -0.0215   0.1650   1.0000
  12.500   1.5887   0.01744   0.01189  -0.0181   0.1418   1.0000
  12.750   1.5796   0.01892   0.01329  -0.0137   0.1276   1.0000
  13.000   1.5729   0.02080   0.01515  -0.0109   0.1133   1.0000
  13.250   1.5575   0.02422   0.01857  -0.0098   0.0979   1.0000
  13.500   1.5450   0.02859   0.02300  -0.0110   0.0901   1.0000
  13.750   1.5346   0.03307   0.02757  -0.0124   0.0839   1.0000
  14.250   1.4933   0.04385   0.03852  -0.0143   0.0744   1.0000
  14.500   1.4698   0.04928   0.04404  -0.0149   0.0682   1.0000
  14.750   1.4456   0.05476   0.04958  -0.0155   0.0648   1.0000
  15.000   1.4244   0.05990   0.05478  -0.0161   0.0618   1.0000
  15.250   1.4061   0.06493   0.05985  -0.0168   0.0581   1.0000
  15.500   1.3953   0.06918   0.06415  -0.0175   0.0540   1.0000
  15.750   1.3833   0.07366   0.06867  -0.0182   0.0501   1.0000
  16.000   1.3708   0.07826   0.07331  -0.0191   0.0464   1.0000
  16.250   1.3613   0.08253   0.07760  -0.0199   0.0388   1.0000
  16.500   1.3440   0.08787   0.08294  -0.0210   0.0334   1.0000
  16.750   1.3368   0.09192   0.08701  -0.0219   0.0298   1.0000
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