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WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il)
Reynolds number: 200,000
Max Cl/Cd: 50.15 at α=12.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w153-il-200000.txt
Download as CSV file: xf-fx77w153-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3392   0.09539   0.09055  -0.0077   0.5272   0.0542
  -8.250  -0.3393   0.09122   0.08635  -0.0112   0.5244   0.0557
  -8.000  -0.3691   0.08200   0.07715  -0.0273   0.5255   0.0574
  -7.750  -0.3812   0.07553   0.07053  -0.0320   0.5240   0.0580
  -7.500  -0.3637   0.07326   0.06836  -0.0302   0.5184   0.0586
  -7.250  -0.3515   0.07102   0.06610  -0.0295   0.5141   0.0593
  -7.000  -0.3419   0.06828   0.06329  -0.0299   0.5108   0.0604
  -6.750  -0.3337   0.06498   0.05986  -0.0312   0.5083   0.0620
  -6.500  -0.3433   0.05802   0.05228  -0.0354   0.5077   0.0672
  -6.250  -0.3248   0.05524   0.04963  -0.0352   0.5043   0.0680
  -6.000  -0.3076   0.05308   0.04746  -0.0349   0.5012   0.0693
  -5.750  -0.2913   0.05074   0.04501  -0.0348   0.4985   0.0716
  -5.500  -0.2822   0.04684   0.04053  -0.0346   0.4968   0.0779
  -5.250  -0.2622   0.04452   0.03822  -0.0343   0.4944   0.0793
  -5.000  -0.2424   0.04259   0.03616  -0.0339   0.4924   0.0817
  -4.750  -0.2328   0.03067   0.02218  -0.0285   0.4920   0.0426
  -4.500  -0.2091   0.02835   0.01972  -0.0279   0.4900   0.0418
  -4.250  -0.1844   0.02645   0.01755  -0.0271   0.4879   0.0413
  -4.000  -0.1585   0.02486   0.01566  -0.0263   0.4858   0.0415
  -3.750  -0.1316   0.02361   0.01411  -0.0257   0.4839   0.0422
  -3.500  -0.1046   0.02242   0.01277  -0.0253   0.4820   0.0437
  -3.250  -0.0775   0.02189   0.01223  -0.0251   0.4802   0.0470
  -3.000  -0.0502   0.02105   0.01124  -0.0247   0.4783   0.0511
  -2.750  -0.0233   0.02043   0.01056  -0.0243   0.4760   0.0560
  -2.500   0.0031   0.01974   0.00989  -0.0239   0.4737   0.0610
  -2.250   0.0304   0.01947   0.00960  -0.0236   0.4715   0.0662
  -2.000   0.0568   0.01913   0.00936  -0.0234   0.4695   0.0727
  -1.750   0.0835   0.01888   0.00910  -0.0231   0.4676   0.0783
  -1.500   0.1098   0.01863   0.00891  -0.0227   0.4660   0.0845
  -1.250   0.1359   0.01838   0.00865  -0.0223   0.4644   0.0906
  -1.000   0.1621   0.01815   0.00845  -0.0218   0.4629   0.1014
  -0.750   0.1842   0.01731   0.00823  -0.0210   0.4615   0.2323
  -0.500   0.2573   0.01545   0.00871  -0.0291   0.4595   0.9226
  -0.250   0.3091   0.01609   0.00920  -0.0333   0.4578   0.9730
   0.000   0.3925   0.01639   0.00937  -0.0444   0.4553   0.9986
   0.250   0.4225   0.01660   0.00952  -0.0451   0.4536   1.0000
   0.500   0.4477   0.01682   0.00968  -0.0449   0.4517   1.0000
   0.750   0.4728   0.01702   0.00981  -0.0445   0.4496   1.0000
   1.000   0.4979   0.01718   0.00988  -0.0441   0.4472   1.0000
   1.250   0.5230   0.01734   0.00993  -0.0437   0.4450   1.0000
   1.500   0.5481   0.01761   0.01006  -0.0432   0.4430   1.0000
   1.750   0.5730   0.01800   0.01042  -0.0429   0.4412   1.0000
   2.000   0.5976   0.01833   0.01080  -0.0426   0.4391   1.0000
   2.250   0.6221   0.01867   0.01116  -0.0422   0.4366   1.0000
   2.500   0.6467   0.01895   0.01142  -0.0418   0.4340   1.0000
   2.750   0.6716   0.01915   0.01157  -0.0413   0.4314   1.0000
   3.000   0.6967   0.01937   0.01171  -0.0409   0.4293   1.0000
   3.250   0.7217   0.01966   0.01193  -0.0404   0.4275   1.0000
   3.500   0.7464   0.02018   0.01237  -0.0400   0.4257   1.0000
   3.750   0.7689   0.02068   0.01302  -0.0395   0.4229   1.0000
   4.000   0.7918   0.02117   0.01358  -0.0390   0.4199   1.0000
   4.250   0.8156   0.02151   0.01394  -0.0384   0.4170   1.0000
   4.500   0.8403   0.02173   0.01411  -0.0379   0.4145   1.0000
   4.750   0.8655   0.02191   0.01424  -0.0375   0.4123   1.0000
   5.000   0.8909   0.02220   0.01444  -0.0370   0.4103   1.0000
   5.250   0.9117   0.02288   0.01524  -0.0363   0.4072   1.0000
   5.500   0.9321   0.02351   0.01600  -0.0355   0.4034   1.0000
   5.750   0.9551   0.02387   0.01639  -0.0349   0.4004   1.0000
   6.000   0.9800   0.02401   0.01650  -0.0344   0.3978   1.0000
   6.250   1.0060   0.02408   0.01651  -0.0340   0.3956   1.0000
   6.500   1.0320   0.02435   0.01671  -0.0337   0.3936   1.0000
   6.750   1.0476   0.02531   0.01789  -0.0325   0.3896   1.0000
   7.000   1.0668   0.02595   0.01865  -0.0315   0.3859   1.0000
   7.250   1.0902   0.02622   0.01894  -0.0309   0.3832   1.0000
   7.500   1.1151   0.02635   0.01907  -0.0305   0.3809   1.0000
   7.750   1.1418   0.02643   0.01910  -0.0302   0.3790   1.0000
   8.000   1.1660   0.02685   0.01950  -0.0298   0.3769   1.0000
   8.250   1.1738   0.02817   0.02113  -0.0278   0.3715   1.0000
   8.500   1.1951   0.02854   0.02156  -0.0270   0.3683   1.0000
   8.750   1.2195   0.02864   0.02167  -0.0265   0.3659   1.0000
   9.000   1.2470   0.02858   0.02158  -0.0263   0.3639   1.0000
   9.250   1.2755   0.02863   0.02158  -0.0263   0.3622   1.0000
   9.500   1.2740   0.03051   0.02380  -0.0234   0.3564   1.0000
   9.750   1.2922   0.03098   0.02436  -0.0224   0.3529   1.0000
  10.000   1.3182   0.03084   0.02423  -0.0220   0.3503   1.0000
  10.250   1.3510   0.03021   0.02354  -0.0223   0.3481   1.0000
  10.500   1.3802   0.02995   0.02323  -0.0223   0.3454   1.0000
  10.750   1.3748   0.03158   0.02518  -0.0190   0.3391   1.0000
  11.000   1.4017   0.03101   0.02464  -0.0186   0.3354   1.0000
  11.250   1.4365   0.03000   0.02355  -0.0189   0.3327   1.0000
  11.500   1.4620   0.02981   0.02336  -0.0186   0.3295   1.0000
  11.750   1.4536   0.03151   0.02537  -0.0152   0.3239   1.0000
  12.000   1.4751   0.03128   0.02520  -0.0143   0.3202   1.0000
  12.250   1.5105   0.03012   0.02398  -0.0147   0.3172   1.0000
  12.500   1.5072   0.03131   0.02537  -0.0117   0.3123   1.0000
  12.750   1.5080   0.03193   0.02610  -0.0090   0.3077   1.0000
  13.000   1.5384   0.03086   0.02500  -0.0088   0.3037   1.0000
  13.250   1.5398   0.03187   0.02611  -0.0068   0.2993   1.0000
  13.500   1.5341   0.03368   0.02806  -0.0053   0.2944   1.0000
  13.750   1.5564   0.03347   0.02784  -0.0049   0.2901   1.0000
  14.000   1.5678   0.03435   0.02876  -0.0043   0.2856   1.0000
  14.250   1.5416   0.03894   0.03356  -0.0043   0.2804   1.0000
  14.500   1.5504   0.04031   0.03496  -0.0042   0.2756   1.0000
  14.750   1.5671   0.04086   0.03549  -0.0038   0.2708   1.0000
  15.000   1.5011   0.05093   0.04583  -0.0061   0.2651   1.0000
  15.250   1.5092   0.05248   0.04740  -0.0062   0.2599   1.0000
  15.500   1.4995   0.05619   0.05117  -0.0068   0.2544   1.0000
  15.750   1.3953   0.07208   0.06723  -0.0108   0.2472   1.0000
  16.000   1.5098   0.05991   0.05490  -0.0072   0.2423   1.0000
  16.250   1.2661   0.09618   0.09143  -0.0170   0.2306   1.0000
  16.500   1.4170   0.07747   0.07275  -0.0116   0.2316   1.0000
  16.750   1.4630   0.07394   0.06917  -0.0103   0.2257   1.0000
  17.000   1.2803   0.10314   0.09860  -0.0188   0.2159   1.0000
  17.250   1.4452   0.08199   0.07733  -0.0124   0.2129   1.0000
  17.500   1.3637   0.09669   0.09224  -0.0168   0.2081   1.0000
  17.750   1.3397   0.10338   0.09901  -0.0189   0.2012   1.0000
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