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FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 79-L-100 (fx79l100-il)
Reynolds number: 200,000
Max Cl/Cd: 41.49 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx79l100-il-200000-n5.txt
Download as CSV file: xf-fx79l100-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 79-L-100                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.9100   0.06784   0.06377  -0.0171   1.0000   0.0153
 -12.250  -0.9436   0.05874   0.05436  -0.0233   1.0000   0.0151
 -12.000  -0.9603   0.05342   0.04882  -0.0262   1.0000   0.0152
 -11.750  -0.9706   0.04958   0.04480  -0.0277   1.0000   0.0154
 -11.500  -0.9844   0.04560   0.04055  -0.0279   1.0000   0.0154
 -11.250  -0.9899   0.04306   0.03782  -0.0268   1.0000   0.0156
 -11.000  -0.9951   0.04054   0.03507  -0.0247   1.0000   0.0158
 -10.750  -0.9936   0.03821   0.03250  -0.0229   1.0000   0.0161
 -10.500  -0.9884   0.03601   0.03003  -0.0212   1.0000   0.0168
 -10.250  -0.9798   0.03384   0.02759  -0.0197   1.0000   0.0172
 -10.000  -0.9692   0.03166   0.02511  -0.0181   1.0000   0.0178
  -9.750  -0.9554   0.02982   0.02296  -0.0167   1.0000   0.0186
  -9.500  -0.9402   0.02814   0.02106  -0.0155   1.0000   0.0194
  -9.250  -0.9230   0.02713   0.02000  -0.0145   1.0000   0.0204
  -9.000  -0.9046   0.02606   0.01883  -0.0135   1.0000   0.0214
  -8.750  -0.8853   0.02506   0.01769  -0.0125   1.0000   0.0228
  -8.500  -0.8659   0.02384   0.01629  -0.0114   1.0000   0.0240
  -8.250  -0.8462   0.02270   0.01500  -0.0102   1.0000   0.0253
  -8.000  -0.8270   0.02167   0.01394  -0.0092   1.0000   0.0268
  -7.750  -0.8059   0.02098   0.01319  -0.0083   1.0000   0.0287
  -7.500  -0.7849   0.02017   0.01228  -0.0073   1.0000   0.0306
  -7.250  -0.7636   0.01939   0.01138  -0.0062   1.0000   0.0324
  -7.000  -0.7442   0.01845   0.01045  -0.0051   1.0000   0.0348
  -6.750  -0.7225   0.01784   0.00981  -0.0041   1.0000   0.0377
  -6.500  -0.7009   0.01722   0.00909  -0.0031   1.0000   0.0405
  -6.250  -0.6801   0.01651   0.00833  -0.0020   1.0000   0.0432
  -6.000  -0.6587   0.01592   0.00775  -0.0010   1.0000   0.0477
  -5.750  -0.6364   0.01545   0.00721   0.0000   1.0000   0.0524
  -5.500  -0.6153   0.01483   0.00661   0.0011   1.0000   0.0580
  -5.250  -0.5930   0.01440   0.00613   0.0021   1.0000   0.0646
  -5.000  -0.5715   0.01388   0.00567   0.0032   1.0000   0.0740
  -4.750  -0.5497   0.01342   0.00524   0.0042   1.0000   0.0851
  -4.500  -0.5282   0.01295   0.00485   0.0053   1.0000   0.1036
  -4.250  -0.5073   0.01245   0.00448   0.0064   1.0000   0.1304
  -4.000  -0.4823   0.01180   0.00407   0.0065   0.9898   0.1797
  -3.750  -0.4487   0.01093   0.00366   0.0045   0.9711   0.2765
  -3.500  -0.4148   0.01017   0.00338   0.0027   0.9497   0.3923
  -3.250  -0.3772   0.00981   0.00327   0.0005   0.9281   0.4702
  -3.000  -0.3384   0.00965   0.00318  -0.0017   0.9055   0.5167
  -2.750  -0.3019   0.00956   0.00308  -0.0034   0.8831   0.5504
  -2.500  -0.2693   0.00951   0.00302  -0.0042   0.8607   0.5772
  -2.000  -0.2120   0.00948   0.00293  -0.0040   0.8210   0.6231
  -1.750  -0.1853   0.00949   0.00289  -0.0035   0.8037   0.6411
  -1.500  -0.1588   0.00948   0.00284  -0.0029   0.7882   0.6548
  -1.250  -0.1323   0.00947   0.00280  -0.0024   0.7742   0.6660
  -1.000  -0.1059   0.00947   0.00274  -0.0019   0.7612   0.6766
  -0.500  -0.0530   0.00946   0.00268  -0.0009   0.7376   0.6963
  -0.250  -0.0265   0.00946   0.00266  -0.0005   0.7265   0.7062
   0.000   0.0000   0.00947   0.00265   0.0000   0.7165   0.7166
   0.250   0.0264   0.00946   0.00266   0.0005   0.7062   0.7266
   0.500   0.0529   0.00946   0.00268   0.0009   0.6965   0.7375
   1.000   0.1058   0.00947   0.00274   0.0019   0.6768   0.7614
   1.250   0.1323   0.00947   0.00280   0.0024   0.6663   0.7743
   1.500   0.1588   0.00948   0.00284   0.0029   0.6549   0.7884
   1.750   0.1853   0.00949   0.00289   0.0035   0.6413   0.8038
   2.000   0.2119   0.00948   0.00293   0.0040   0.6231   0.8211
   2.250   0.2393   0.00949   0.00297   0.0044   0.6017   0.8401
   2.500   0.2692   0.00951   0.00302   0.0042   0.5770   0.8605
   2.750   0.3018   0.00956   0.00308   0.0034   0.5504   0.8832
   3.000   0.3384   0.00965   0.00318   0.0017   0.5159   0.9058
   3.250   0.3771   0.00981   0.00327  -0.0005   0.4704   0.9278
   3.500   0.4146   0.01016   0.00338  -0.0027   0.3952   0.9493
   3.750   0.4485   0.01095   0.00366  -0.0045   0.2742   0.9711
   4.000   0.4822   0.01180   0.00407  -0.0065   0.1797   0.9898
   4.250   0.5073   0.01245   0.00448  -0.0064   0.1308   1.0000
   4.500   0.5281   0.01295   0.00484  -0.0053   0.1034   1.0000
   4.750   0.5497   0.01341   0.00524  -0.0042   0.0857   1.0000
   5.000   0.5714   0.01388   0.00567  -0.0032   0.0740   1.0000
   5.250   0.5929   0.01440   0.00613  -0.0021   0.0647   1.0000
   5.500   0.6153   0.01483   0.00661  -0.0012   0.0578   1.0000
   5.750   0.6363   0.01544   0.00721   0.0000   0.0525   1.0000
   6.000   0.6585   0.01593   0.00777   0.0010   0.0481   1.0000
   6.250   0.6802   0.01649   0.00832   0.0019   0.0437   1.0000
   6.500   0.7008   0.01722   0.00909   0.0031   0.0407   1.0000
   6.750   0.7224   0.01785   0.00982   0.0042   0.0379   1.0000
   7.000   0.7443   0.01843   0.01042   0.0050   0.0346   1.0000
   7.250   0.7636   0.01939   0.01138   0.0062   0.0324   1.0000
   7.500   0.7851   0.02012   0.01223   0.0073   0.0305   1.0000
   7.750   0.8063   0.02084   0.01304   0.0082   0.0282   1.0000
   8.000   0.8273   0.02152   0.01377   0.0091   0.0263   1.0000
   8.250   0.8459   0.02271   0.01499   0.0102   0.0249   1.0000
   8.500   0.8659   0.02379   0.01625   0.0113   0.0237   1.0000
   8.750   0.8852   0.02501   0.01765   0.0125   0.0225   1.0000
   9.000   0.9041   0.02614   0.01891   0.0135   0.0213   1.0000
   9.250   0.9230   0.02700   0.01984   0.0144   0.0202   1.0000
   9.500   0.9391   0.02828   0.02117   0.0155   0.0191   1.0000
   9.750   0.9551   0.02986   0.02303   0.0168   0.0184   1.0000
  10.000   0.9686   0.03177   0.02523   0.0182   0.0177   1.0000
  10.250   0.9797   0.03383   0.02758   0.0197   0.0171   1.0000
  10.500   0.9880   0.03602   0.03005   0.0212   0.0167   1.0000
  10.750   0.9926   0.03839   0.03269   0.0229   0.0162   1.0000
  11.000   0.9936   0.04076   0.03531   0.0247   0.0159   1.0000
  11.250   0.9895   0.04313   0.03789   0.0268   0.0156   1.0000
  11.500   0.9833   0.04576   0.04072   0.0279   0.0154   1.0000
  11.750   0.9726   0.04931   0.04450   0.0277   0.0153   1.0000
  12.000   0.9574   0.05391   0.04934   0.0260   0.0153   1.0000
  12.250   0.9374   0.05985   0.05553   0.0226   0.0153   1.0000
  12.500   0.9063   0.06865   0.06460   0.0164   0.0154   1.0000
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