Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 79-L-100 (fx79l100-il)
Reynolds number: 500,000
Max Cl/Cd: 57.95 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx79l100-il-500000.txt
Download as CSV file: xf-fx79l100-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.8806   0.09620   0.09383   0.0085   1.0000   0.0146
 -13.250  -0.8907   0.08797   0.08548   0.0029   1.0000   0.0144
 -13.000  -0.9333   0.07434   0.07172  -0.0067   1.0000   0.0140
 -12.750  -0.9665   0.06409   0.06127  -0.0143   1.0000   0.0139
 -12.500  -0.9848   0.05760   0.05458  -0.0190   1.0000   0.0140
 -12.250  -0.9996   0.05237   0.04914  -0.0224   1.0000   0.0141
 -12.000  -1.0229   0.04657   0.04310  -0.0246   1.0000   0.0139
 -11.750  -1.0342   0.04308   0.03937  -0.0249   1.0000   0.0141
 -11.500  -1.0420   0.04033   0.03639  -0.0237   1.0000   0.0142
 -11.250  -1.0544   0.03658   0.03233  -0.0211   1.0000   0.0141
 -11.000  -1.0496   0.03444   0.02994  -0.0195   1.0000   0.0143
 -10.750  -1.0403   0.03267   0.02793  -0.0181   1.0000   0.0144
 -10.500  -1.0433   0.02798   0.02282  -0.0157   1.0000   0.0150
 -10.250  -1.0281   0.02653   0.02126  -0.0146   1.0000   0.0154
 -10.000  -1.0113   0.02522   0.01984  -0.0135   1.0000   0.0158
  -9.750  -0.9920   0.02445   0.01900  -0.0126   1.0000   0.0166
  -9.500  -0.9726   0.02350   0.01794  -0.0117   1.0000   0.0174
  -9.250  -0.9528   0.02248   0.01677  -0.0106   1.0000   0.0182
  -9.000  -0.9323   0.02153   0.01567  -0.0097   1.0000   0.0188
  -8.750  -0.9158   0.01967   0.01364  -0.0082   1.0000   0.0198
  -8.500  -0.8960   0.01868   0.01262  -0.0072   1.0000   0.0210
  -8.250  -0.8746   0.01795   0.01184  -0.0062   1.0000   0.0221
  -8.000  -0.8521   0.01738   0.01121  -0.0054   1.0000   0.0235
  -7.750  -0.8296   0.01679   0.01054  -0.0045   1.0000   0.0246
  -7.500  -0.8108   0.01566   0.00931  -0.0031   1.0000   0.0262
  -7.250  -0.7885   0.01514   0.00881  -0.0023   1.0000   0.0285
  -7.000  -0.7656   0.01467   0.00830  -0.0015   1.0000   0.0304
  -6.750  -0.7417   0.01431   0.00789  -0.0007   1.0000   0.0322
  -6.500  -0.7226   0.01336   0.00689   0.0008   1.0000   0.0351
  -6.250  -0.6998   0.01293   0.00646   0.0016   1.0000   0.0378
  -6.000  -0.6764   0.01255   0.00605   0.0025   1.0000   0.0408
  -5.750  -0.6552   0.01194   0.00540   0.0037   1.0000   0.0446
  -5.500  -0.6325   0.01154   0.00502   0.0047   1.0000   0.0496
  -5.250  -0.6092   0.01121   0.00465   0.0056   1.0000   0.0538
  -5.000  -0.5877   0.01073   0.00421   0.0068   1.0000   0.0619
  -4.750  -0.5656   0.01036   0.00387   0.0079   1.0000   0.0712
  -4.500  -0.5441   0.00998   0.00356   0.0091   1.0000   0.0850
  -4.250  -0.5236   0.00958   0.00327   0.0105   1.0000   0.1077
  -4.000  -0.4872   0.00884   0.00287   0.0081   0.9872   0.1745
  -3.750  -0.4520   0.00797   0.00249   0.0059   0.9731   0.2851
  -3.500  -0.4132   0.00716   0.00221   0.0030   0.9573   0.4184
  -3.250  -0.3676   0.00682   0.00210  -0.0010   0.9374   0.4914
  -3.000  -0.3220   0.00669   0.00200  -0.0049   0.9104   0.5302
  -2.750  -0.2866   0.00668   0.00192  -0.0064   0.8795   0.5541
  -2.500  -0.2583   0.00670   0.00187  -0.0062   0.8518   0.5727
  -2.250  -0.2322   0.00673   0.00182  -0.0057   0.8282   0.5883
  -2.000  -0.2066   0.00676   0.00179  -0.0049   0.8086   0.6040
  -1.750  -0.1812   0.00678   0.00176  -0.0042   0.7913   0.6187
  -1.500  -0.1559   0.00680   0.00175  -0.0035   0.7759   0.6350
  -1.250  -0.1303   0.00682   0.00173  -0.0028   0.7621   0.6487
  -1.000  -0.1047   0.00684   0.00172  -0.0021   0.7496   0.6624
  -0.750  -0.0787   0.00685   0.00171  -0.0015   0.7375   0.6745
  -0.500  -0.0526   0.00685   0.00171  -0.0010   0.7265   0.6856
  -0.250  -0.0264   0.00685   0.00170  -0.0005   0.7163   0.6955
   0.000   0.0000   0.00685   0.00169   0.0000   0.7060   0.7060
   0.250   0.0263   0.00685   0.00170   0.0005   0.6958   0.7165
   0.500   0.0525   0.00685   0.00171   0.0010   0.6857   0.7265
   0.750   0.0786   0.00685   0.00171   0.0015   0.6746   0.7376
   1.000   0.1046   0.00684   0.00172   0.0021   0.6627   0.7496
   1.250   0.1303   0.00682   0.00174   0.0028   0.6489   0.7622
   1.500   0.1558   0.00680   0.00174   0.0035   0.6341   0.7757
   1.750   0.1812   0.00678   0.00176   0.0042   0.6189   0.7911
   2.000   0.2066   0.00676   0.00178   0.0049   0.6038   0.8084
   2.250   0.2321   0.00673   0.00182   0.0056   0.5883   0.8283
   2.500   0.2582   0.00670   0.00187   0.0062   0.5728   0.8519
   2.750   0.2867   0.00667   0.00192   0.0063   0.5551   0.8798
   3.000   0.3220   0.00669   0.00200   0.0049   0.5299   0.9107
   3.250   0.3674   0.00683   0.00209   0.0011   0.4896   0.9373
   3.500   0.4132   0.00713   0.00221  -0.0030   0.4224   0.9570
   3.750   0.4521   0.00794   0.00248  -0.0059   0.2888   0.9729
   4.000   0.4871   0.00885   0.00287  -0.0081   0.1728   0.9873
   4.250   0.5236   0.00959   0.00327  -0.0105   0.1074   1.0000
   4.500   0.5440   0.00998   0.00356  -0.0091   0.0845   1.0000
   4.750   0.5656   0.01035   0.00387  -0.0080   0.0718   1.0000
   5.000   0.5876   0.01074   0.00423  -0.0068   0.0621   1.0000
   5.250   0.6093   0.01120   0.00464  -0.0057   0.0542   1.0000
   5.500   0.6322   0.01156   0.00505  -0.0047   0.0499   1.0000
   5.750   0.6551   0.01195   0.00543  -0.0037   0.0453   1.0000
   6.000   0.6760   0.01259   0.00608  -0.0025   0.0411   1.0000
   6.250   0.6999   0.01289   0.00642  -0.0017   0.0381   1.0000
   6.500   0.7230   0.01329   0.00681  -0.0009   0.0349   1.0000
   6.750   0.7424   0.01420   0.00777   0.0005   0.0322   1.0000
   7.000   0.7661   0.01458   0.00821   0.0013   0.0301   1.0000
   7.250   0.7890   0.01504   0.00870   0.0022   0.0282   1.0000
   7.500   0.8106   0.01567   0.00932   0.0031   0.0261   1.0000
   7.750   0.8305   0.01662   0.01036   0.0044   0.0243   1.0000
   8.000   0.8529   0.01722   0.01104   0.0053   0.0229   1.0000
   8.250   0.8750   0.01784   0.01171   0.0061   0.0216   1.0000
   8.500   0.8962   0.01857   0.01248   0.0071   0.0206   1.0000
   8.750   0.9135   0.02008   0.01406   0.0084   0.0194   1.0000
   9.000   0.9317   0.02164   0.01579   0.0098   0.0187   1.0000
   9.250   0.9522   0.02258   0.01689   0.0107   0.0181   1.0000
   9.500   0.9718   0.02367   0.01812   0.0118   0.0173   1.0000
   9.750   0.9908   0.02471   0.01929   0.0128   0.0167   1.0000
  10.000   1.0084   0.02597   0.02068   0.0139   0.0161   1.0000
  10.250   1.0273   0.02666   0.02141   0.0147   0.0155   1.0000
  10.500   1.0423   0.02817   0.02304   0.0159   0.0151   1.0000
  10.750   1.0506   0.03083   0.02593   0.0175   0.0148   1.0000
  11.250   1.0502   0.03727   0.03305   0.0213   0.0142   1.0000
  11.500   1.0430   0.04014   0.03621   0.0237   0.0141   1.0000
  11.750   1.0343   0.04304   0.03933   0.0249   0.0141   1.0000
  12.000   1.0199   0.04704   0.04357   0.0245   0.0141   1.0000
  12.250   1.0012   0.05218   0.04893   0.0224   0.0141   1.0000
  12.500   0.9793   0.05850   0.05548   0.0186   0.0142   1.0000
  12.750   0.9573   0.06570   0.06288   0.0134   0.0142   1.0000
  13.000   0.9228   0.07614   0.07348   0.0059   0.0144   1.0000
<< Back to FX 79-L-100 (fx79l100-il)

Polar data table (+)

Polar graphs


<< Back to FX 79-L-100 (fx79l100-il)