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FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 79-L-100 (fx79l100-il)
Reynolds number: 100,000
Max Cl/Cd: 38.61 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx79l100-il-100000.txt
Download as CSV file: xf-fx79l100-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6541   0.09102   0.08607   0.0022   1.0000   0.1744
  -9.000  -0.8174   0.05953   0.05369  -0.0211   1.0000   0.0771
  -8.750  -0.8135   0.05435   0.04839  -0.0205   1.0000   0.0743
  -8.500  -0.8163   0.04895   0.04256  -0.0191   1.0000   0.0711
  -8.250  -0.8110   0.04518   0.03839  -0.0176   1.0000   0.0720
  -8.000  -0.8023   0.04149   0.03426  -0.0159   1.0000   0.0726
  -7.750  -0.7903   0.03806   0.03037  -0.0142   1.0000   0.0731
  -7.500  -0.7749   0.03485   0.02669  -0.0126   1.0000   0.0737
  -7.250  -0.7573   0.03244   0.02377  -0.0109   1.0000   0.0767
  -7.000  -0.7381   0.02992   0.02087  -0.0096   1.0000   0.0800
  -6.750  -0.7156   0.02776   0.01861  -0.0088   1.0000   0.0838
  -6.500  -0.6922   0.02607   0.01672  -0.0078   1.0000   0.0887
  -6.250  -0.6689   0.02429   0.01483  -0.0069   1.0000   0.0952
  -6.000  -0.6451   0.02286   0.01337  -0.0060   1.0000   0.1026
  -5.750  -0.6222   0.02139   0.01194  -0.0051   1.0000   0.1122
  -5.500  -0.6000   0.02010   0.01069  -0.0039   1.0000   0.1241
  -5.250  -0.5795   0.01889   0.00962  -0.0026   1.0000   0.1395
  -5.000  -0.5605   0.01775   0.00862  -0.0009   1.0000   0.1636
  -4.750  -0.5456   0.01629   0.00759   0.0012   1.0000   0.2071
  -4.500  -0.5419   0.01408   0.00678   0.0050   1.0000   0.3888
  -4.250  -0.5301   0.01373   0.00696   0.0089   1.0000   0.5370
  -4.000  -0.5125   0.01379   0.00709   0.0117   1.0000   0.5925
  -3.750  -0.4941   0.01385   0.00717   0.0142   1.0000   0.6299
  -3.500  -0.4756   0.01389   0.00722   0.0167   1.0000   0.6600
  -3.250  -0.4582   0.01391   0.00723   0.0193   1.0000   0.6877
  -3.000  -0.4410   0.01392   0.00730   0.0219   1.0000   0.7109
  -2.750  -0.4271   0.01391   0.00730   0.0248   1.0000   0.7346
  -2.500  -0.4141   0.01394   0.00739   0.0280   1.0000   0.7564
  -2.250  -0.4040   0.01396   0.00740   0.0312   1.0000   0.7797
  -2.000  -0.3921   0.01402   0.00752   0.0342   1.0000   0.8016
  -1.750  -0.3765   0.01407   0.00756   0.0362   0.9981   0.8253
  -1.500  -0.3305   0.01419   0.00768   0.0328   0.9863   0.8468
  -1.250  -0.2820   0.01426   0.00768   0.0286   0.9747   0.8650
  -1.000  -0.2327   0.01430   0.00767   0.0242   0.9638   0.8812
  -0.750  -0.1799   0.01434   0.00767   0.0192   0.9541   0.8956
  -0.500  -0.1195   0.01439   0.00769   0.0127   0.9469   0.9078
  -0.250  -0.0623   0.01443   0.00771   0.0068   0.9372   0.9193
   0.000   0.0000   0.01443   0.00770   0.0000   0.9296   0.9296
   0.250   0.0622   0.01443   0.00771  -0.0068   0.9194   0.9372
   0.500   0.1194   0.01440   0.00769  -0.0128   0.9078   0.9469
   0.750   0.1801   0.01434   0.00767  -0.0193   0.8956   0.9542
   1.000   0.2328   0.01430   0.00767  -0.0243   0.8815   0.9639
   1.250   0.2822   0.01426   0.00769  -0.0287   0.8654   0.9748
   1.500   0.3300   0.01420   0.00768  -0.0327   0.8469   0.9861
   1.750   0.3764   0.01406   0.00756  -0.0362   0.8254   0.9981
   2.000   0.3920   0.01402   0.00751  -0.0343   0.8015   1.0000
   2.250   0.4039   0.01396   0.00742  -0.0312   0.7798   1.0000
   2.500   0.4139   0.01393   0.00738  -0.0279   0.7562   1.0000
   2.750   0.4270   0.01391   0.00729  -0.0248   0.7345   1.0000
   3.000   0.4409   0.01392   0.00729  -0.0219   0.7108   1.0000
   3.250   0.4581   0.01391   0.00725  -0.0193   0.6877   1.0000
   3.500   0.4755   0.01389   0.00722  -0.0167   0.6602   1.0000
   3.750   0.4940   0.01385   0.00716  -0.0142   0.6299   1.0000
   4.000   0.5124   0.01379   0.00709  -0.0117   0.5924   1.0000
   4.250   0.5301   0.01373   0.00696  -0.0089   0.5373   1.0000
   4.500   0.5416   0.01409   0.00675  -0.0050   0.3870   1.0000
   4.750   0.5457   0.01627   0.00759  -0.0013   0.2087   1.0000
   5.000   0.5604   0.01774   0.00861   0.0009   0.1640   1.0000
   5.250   0.5795   0.01889   0.00962   0.0025   0.1396   1.0000
   5.500   0.6000   0.02010   0.01069   0.0039   0.1242   1.0000
   5.750   0.6221   0.02137   0.01192   0.0051   0.1124   1.0000
   6.000   0.6450   0.02285   0.01335   0.0060   0.1029   1.0000
   6.250   0.6690   0.02427   0.01484   0.0069   0.0958   1.0000
   6.500   0.6923   0.02610   0.01675   0.0078   0.0891   1.0000
   6.750   0.7156   0.02776   0.01862   0.0088   0.0839   1.0000
   7.000   0.7380   0.03002   0.02094   0.0095   0.0796   1.0000
   7.250   0.7571   0.03241   0.02376   0.0110   0.0763   1.0000
   7.500   0.7748   0.03488   0.02672   0.0126   0.0737   1.0000
   7.750   0.7900   0.03805   0.03036   0.0143   0.0727   1.0000
   8.000   0.8027   0.04116   0.03390   0.0159   0.0711   1.0000
   8.250   0.8214   0.04322   0.03589   0.0164   0.0672   1.0000
   8.500   0.8173   0.04871   0.04228   0.0190   0.0702   1.0000
   8.750   0.8126   0.05439   0.04845   0.0205   0.0739   1.0000
   9.000   0.8145   0.05961   0.05382   0.0212   0.0768   1.0000
   9.250   0.6974   0.05163   0.04678   0.0260   0.0836   1.0000
   9.500   0.6540   0.05805   0.05332   0.0243   0.0871   1.0000
   9.750   0.6518   0.09957   0.09453  -0.0048   0.1610   1.0000
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