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FX 73-CL1-152 (fx73cl1152-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 73-CL1-152 (fx73cl1152-il)
Reynolds number: 100,000
Max Cl/Cd: 42.1 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx73cl1152-il-100000-n5.txt
Download as CSV file: xf-fx73cl1152-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 73-CL1-152                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0756   0.10610   0.09956  -0.0634   0.6206   0.0781
  -9.250  -0.0680   0.10304   0.09642  -0.0652   0.6114   0.0781
  -8.750  -0.0491   0.09351   0.08678  -0.0680   0.5953   0.0627
  -8.500  -0.0357   0.09094   0.08414  -0.0684   0.5873   0.0620
  -8.250  -0.0288   0.08815   0.08133  -0.0695   0.5803   0.0618
  -8.000  -0.0242   0.08523   0.07838  -0.0708   0.5745   0.0618
  -7.750  -0.0172   0.08253   0.07564  -0.0716   0.5690   0.0612
  -7.500  -0.0117   0.07969   0.07281  -0.0725   0.5632   0.0605
  -7.250  -0.0088   0.07667   0.06978  -0.0737   0.5582   0.0597
  -7.000  -0.0086   0.07351   0.06661  -0.0748   0.5540   0.0590
  -6.750  -0.0122   0.07034   0.06343  -0.0760   0.5504   0.0585
  -6.500  -0.0135   0.06670   0.05982  -0.0785   0.5461   0.0583
  -6.250  -0.0097   0.06315   0.05627  -0.0816   0.5416   0.0590
  -6.000  -0.0056   0.05849   0.05156  -0.0865   0.5379   0.0596
  -5.750  -0.0013   0.05120   0.04410  -0.0945   0.5351   0.0601
  -5.500   0.0008   0.03874   0.03086  -0.1062   0.5336   0.0605
  -5.250   0.0179   0.03285   0.02400  -0.1102   0.5300   0.0623
  -5.000   0.0420   0.03172   0.02276  -0.1104   0.5247   0.0638
  -4.750   0.0669   0.03074   0.02164  -0.1106   0.5200   0.0653
  -4.500   0.0920   0.02919   0.01973  -0.1109   0.5161   0.0668
  -4.250   0.1179   0.02763   0.01769  -0.1112   0.5127   0.0686
  -4.000   0.1441   0.02652   0.01631  -0.1112   0.5083   0.0706
  -3.750   0.1704   0.02602   0.01579  -0.1111   0.5038   0.0727
  -3.500   0.1971   0.02534   0.01491  -0.1109   0.4997   0.0753
  -3.250   0.2243   0.02455   0.01379  -0.1108   0.4961   0.0777
  -3.000   0.2511   0.02406   0.01320  -0.1106   0.4930   0.0800
  -2.750   0.2779   0.02371   0.01285  -0.1103   0.4894   0.0833
  -2.500   0.3052   0.02329   0.01224  -0.1101   0.4858   0.0873
  -2.250   0.3319   0.02293   0.01193  -0.1098   0.4823   0.0904
  -2.000   0.3590   0.02265   0.01156  -0.1095   0.4791   0.0952
  -1.750   0.3862   0.02238   0.01120  -0.1093   0.4762   0.1003
  -1.500   0.4133   0.02219   0.01097  -0.1090   0.4732   0.1063
  -1.250   0.4397   0.02202   0.01086  -0.1086   0.4698   0.1133
  -1.000   0.4666   0.02192   0.01075  -0.1083   0.4666   0.1224
  -0.750   0.4933   0.02181   0.01069  -0.1080   0.4636   0.1332
  -0.500   0.5202   0.02173   0.01062  -0.1077   0.4607   0.1468
  -0.250   0.5475   0.02167   0.01055  -0.1074   0.4580   0.1655
   0.000   0.5749   0.02168   0.01055  -0.1072   0.4556   0.1887
   0.250   0.6008   0.02174   0.01078  -0.1069   0.4523   0.2154
   0.500   0.6267   0.02183   0.01095  -0.1064   0.4491   0.2449
   0.750   0.6526   0.02189   0.01111  -0.1060   0.4459   0.2765
   1.000   0.6792   0.02193   0.01122  -0.1057   0.4430   0.3122
   1.250   0.7067   0.02196   0.01131  -0.1055   0.4405   0.3574
   1.500   0.7342   0.02196   0.01141  -0.1053   0.4383   0.4194
   2.000   0.7863   0.02124   0.01206  -0.1040   0.4321   1.0000
   2.250   0.8122   0.02162   0.01232  -0.1037   0.4289   1.0000
   2.500   0.8385   0.02196   0.01254  -0.1034   0.4261   1.0000
   2.750   0.8653   0.02228   0.01272  -0.1031   0.4236   1.0000
   3.000   0.8926   0.02259   0.01287  -0.1029   0.4214   1.0000
   3.250   0.9206   0.02290   0.01300  -0.1027   0.4193   1.0000
   3.500   0.9427   0.02347   0.01364  -0.1020   0.4158   1.0000
   3.750   0.9661   0.02399   0.01418  -0.1014   0.4125   1.0000
   4.000   0.9904   0.02446   0.01462  -0.1008   0.4097   1.0000
   4.250   1.0154   0.02488   0.01499  -0.1004   0.4072   1.0000
   4.500   1.0415   0.02524   0.01527  -0.1001   0.4049   1.0000
   4.750   1.0686   0.02555   0.01547  -0.0998   0.4028   1.0000
   5.000   1.0933   0.02603   0.01590  -0.0994   0.4004   1.0000
   5.250   1.1116   0.02683   0.01685  -0.0983   0.3967   1.0000
   5.500   1.1324   0.02749   0.01757  -0.0974   0.3935   1.0000
   5.750   1.1549   0.02805   0.01813  -0.0967   0.3908   1.0000
   6.000   1.1787   0.02852   0.01859  -0.0962   0.3885   1.0000
   6.250   1.2040   0.02891   0.01893  -0.0958   0.3865   1.0000
   6.500   1.2309   0.02924   0.01918  -0.0956   0.3848   1.0000
   6.750   1.2467   0.03021   0.02028  -0.0943   0.3816   1.0000
   7.000   1.2587   0.03135   0.02159  -0.0926   0.3778   1.0000
   7.250   1.2757   0.03217   0.02248  -0.0915   0.3747   1.0000
   7.500   1.2959   0.03277   0.02310  -0.0906   0.3722   1.0000
   7.750   1.3185   0.03326   0.02359  -0.0899   0.3702   1.0000
   8.000   1.3438   0.03363   0.02392  -0.0896   0.3685   1.0000
   8.250   1.3685   0.03409   0.02436  -0.0892   0.3669   1.0000
   8.500   1.3495   0.03692   0.02754  -0.0848   0.3619   1.0000
   8.750   1.3461   0.03874   0.02950  -0.0819   0.3583   1.0000
   9.000   1.3542   0.03976   0.03058  -0.0799   0.3556   1.0000
   9.250   1.3726   0.04028   0.03111  -0.0788   0.3536   1.0000
   9.500   1.3971   0.04055   0.03137  -0.0783   0.3521   1.0000
   9.750   1.4274   0.04066   0.03145  -0.0784   0.3509   1.0000
  10.000   1.2112   0.06136   0.05269  -0.0730   0.3343   1.0000
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