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FX 79-L-120 (fx79l120-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 79-L-120 (fx79l120-il)
Reynolds number: 100,000
Max Cl/Cd: 38 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx79l120-il-100000-n5.txt
Download as CSV file: xf-fx79l120-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 79-L-120                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7921   0.09996   0.09443  -0.0087   1.0000   0.0369
 -13.250  -0.8338   0.08702   0.08136  -0.0175   1.0000   0.0360
 -13.000  -0.8743   0.07647   0.07060  -0.0247   1.0000   0.0356
 -12.750  -0.9026   0.06922   0.06313  -0.0290   1.0000   0.0354
 -12.500  -0.9261   0.06334   0.05701  -0.0317   1.0000   0.0353
 -12.250  -0.9471   0.05846   0.05187  -0.0332   1.0000   0.0358
 -12.000  -0.9622   0.05454   0.04769  -0.0335   1.0000   0.0361
 -11.750  -0.9759   0.05109   0.04394  -0.0328   1.0000   0.0366
 -11.500  -0.9870   0.04801   0.04054  -0.0310   1.0000   0.0371
 -11.250  -0.9943   0.04533   0.03749  -0.0285   1.0000   0.0377
 -11.000  -0.9884   0.04307   0.03512  -0.0271   1.0000   0.0385
 -10.750  -0.9790   0.04128   0.03324  -0.0258   1.0000   0.0394
 -10.500  -0.9690   0.03979   0.03165  -0.0244   1.0000   0.0409
 -10.250  -0.9579   0.03814   0.02980  -0.0230   1.0000   0.0425
 -10.000  -0.9457   0.03633   0.02768  -0.0216   1.0000   0.0446
  -9.750  -0.9306   0.03449   0.02555  -0.0203   1.0000   0.0462
  -9.500  -0.9133   0.03293   0.02402  -0.0194   1.0000   0.0478
  -9.250  -0.8963   0.03175   0.02278  -0.0184   1.0000   0.0501
  -9.000  -0.8784   0.03053   0.02141  -0.0173   1.0000   0.0529
  -8.750  -0.8590   0.02929   0.01992  -0.0162   1.0000   0.0555
  -8.500  -0.8410   0.02798   0.01869  -0.0152   1.0000   0.0582
  -8.250  -0.8223   0.02699   0.01767  -0.0141   1.0000   0.0617
  -8.000  -0.8026   0.02601   0.01654  -0.0130   1.0000   0.0654
  -7.750  -0.7845   0.02490   0.01544  -0.0118   1.0000   0.0689
  -7.500  -0.7659   0.02401   0.01456  -0.0106   1.0000   0.0734
  -7.000  -0.7290   0.02226   0.01278  -0.0079   1.0000   0.0839
  -6.750  -0.7098   0.02153   0.01199  -0.0066   1.0000   0.0910
  -6.500  -0.6923   0.02068   0.01121  -0.0052   1.0000   0.0985
  -6.250  -0.6738   0.01994   0.01048  -0.0038   1.0000   0.1080
  -6.000  -0.6556   0.01921   0.00980  -0.0023   1.0000   0.1210
  -5.750  -0.6380   0.01845   0.00915  -0.0008   1.0000   0.1374
  -5.500  -0.6208   0.01768   0.00852   0.0007   1.0000   0.1624
  -5.250  -0.6048   0.01686   0.00794   0.0024   1.0000   0.1999
  -5.000  -0.5903   0.01600   0.00742   0.0043   1.0000   0.2560
  -4.750  -0.5777   0.01519   0.00707   0.0065   1.0000   0.3300
  -4.500  -0.5516   0.01463   0.00688   0.0063   0.9833   0.4139
  -4.250  -0.5147   0.01442   0.00683   0.0043   0.9641   0.4756
  -4.000  -0.4765   0.01435   0.00679   0.0023   0.9463   0.5163
  -3.750  -0.4380   0.01433   0.00673   0.0003   0.9290   0.5472
  -3.500  -0.4014   0.01434   0.00667  -0.0012   0.9113   0.5740
  -3.250  -0.3667   0.01438   0.00666  -0.0022   0.8940   0.5961
  -3.000  -0.3343   0.01442   0.00664  -0.0027   0.8772   0.6158
  -2.750  -0.3038   0.01445   0.00660  -0.0029   0.8613   0.6325
  -2.500  -0.2745   0.01446   0.00654  -0.0028   0.8465   0.6463
  -2.250  -0.2461   0.01445   0.00643  -0.0026   0.8329   0.6579
  -2.000  -0.2190   0.01442   0.00632  -0.0022   0.8194   0.6687
  -1.750  -0.1915   0.01439   0.00625  -0.0019   0.8071   0.6774
  -1.500  -0.1642   0.01436   0.00613  -0.0016   0.7960   0.6872
  -1.250  -0.1360   0.01433   0.00607  -0.0014   0.7855   0.6949
  -1.000  -0.1091   0.01430   0.00598  -0.0011   0.7747   0.7041
  -0.750  -0.0812   0.01428   0.00594  -0.0009   0.7656   0.7118
  -0.500  -0.0544   0.01426   0.00589  -0.0006   0.7557   0.7208
  -0.250  -0.0270   0.01425   0.00588  -0.0003   0.7466   0.7289
   0.000   0.0000   0.01425   0.00586   0.0000   0.7378   0.7379
   0.250   0.0271   0.01425   0.00588   0.0003   0.7289   0.7467
   0.500   0.0545   0.01426   0.00589   0.0006   0.7208   0.7557
   0.750   0.0813   0.01428   0.00594   0.0009   0.7118   0.7656
   1.000   0.1092   0.01430   0.00598   0.0012   0.7039   0.7747
   1.250   0.1360   0.01433   0.00607   0.0014   0.6949   0.7855
   1.500   0.1643   0.01436   0.00612   0.0016   0.6872   0.7959
   1.750   0.1915   0.01439   0.00625   0.0019   0.6774   0.8072
   2.000   0.2191   0.01442   0.00632   0.0022   0.6687   0.8196
   2.250   0.2461   0.01445   0.00643   0.0026   0.6578   0.8330
   2.500   0.2745   0.01446   0.00653   0.0028   0.6461   0.8466
   2.750   0.3039   0.01445   0.00660   0.0029   0.6326   0.8613
   3.000   0.3343   0.01442   0.00664   0.0028   0.6158   0.8772
   3.250   0.3667   0.01438   0.00666   0.0022   0.5959   0.8941
   3.500   0.4014   0.01434   0.00667   0.0012   0.5737   0.9113
   3.750   0.4381   0.01433   0.00673  -0.0003   0.5470   0.9290
   4.000   0.4765   0.01435   0.00679  -0.0023   0.5155   0.9464
   4.250   0.5149   0.01442   0.00683  -0.0043   0.4752   0.9643
   4.500   0.5517   0.01463   0.00689  -0.0063   0.4135   0.9834
   4.750   0.5776   0.01520   0.00707  -0.0064   0.3291   1.0000
   5.000   0.5903   0.01600   0.00742  -0.0042   0.2555   1.0000
   5.250   0.6048   0.01686   0.00794  -0.0024   0.1997   1.0000
   5.500   0.6209   0.01769   0.00852  -0.0007   0.1623   1.0000
   5.750   0.6380   0.01846   0.00915   0.0009   0.1374   1.0000
   6.000   0.6555   0.01922   0.00980   0.0024   0.1207   1.0000
   6.250   0.6738   0.01995   0.01048   0.0038   0.1079   1.0000
   6.500   0.6923   0.02068   0.01121   0.0052   0.0983   1.0000
   6.750   0.7099   0.02153   0.01199   0.0066   0.0908   1.0000
   7.000   0.7291   0.02226   0.01278   0.0079   0.0837   1.0000
   7.250   0.7462   0.02323   0.01365   0.0093   0.0786   1.0000
   7.500   0.7659   0.02402   0.01457   0.0106   0.0733   1.0000
   7.750   0.7845   0.02490   0.01544   0.0118   0.0687   1.0000
   8.000   0.8027   0.02602   0.01655   0.0130   0.0654   1.0000
   8.250   0.8224   0.02700   0.01767   0.0141   0.0616   1.0000
   8.500   0.8411   0.02800   0.01870   0.0152   0.0581   1.0000
   8.750   0.8592   0.02930   0.01992   0.0162   0.0555   1.0000
   9.000   0.8785   0.03053   0.02141   0.0173   0.0527   1.0000
   9.250   0.8964   0.03175   0.02278   0.0184   0.0500   1.0000
   9.500   0.9135   0.03295   0.02403   0.0194   0.0478   1.0000
   9.750   0.9308   0.03451   0.02557   0.0203   0.0461   1.0000
  10.000   0.9457   0.03634   0.02770   0.0216   0.0445   1.0000
  10.250   0.9583   0.03814   0.02980   0.0230   0.0425   1.0000
  10.500   0.9692   0.03977   0.03162   0.0244   0.0408   1.0000
  10.750   0.9792   0.04134   0.03331   0.0258   0.0395   1.0000
  11.000   0.9888   0.04309   0.03514   0.0270   0.0385   1.0000
  11.250   0.9946   0.04536   0.03752   0.0285   0.0378   1.0000
  11.500   0.9877   0.04806   0.04058   0.0310   0.0372   1.0000
  11.750   0.9764   0.05112   0.04397   0.0327   0.0366   1.0000
  12.000   0.9624   0.05465   0.04781   0.0335   0.0361   1.0000
  12.250   0.9453   0.05872   0.05215   0.0331   0.0356   1.0000
  12.500   0.9268   0.06351   0.05719   0.0316   0.0356   1.0000
  12.750   0.9025   0.06939   0.06331   0.0288   0.0354   1.0000
  13.000   0.8748   0.07663   0.07076   0.0245   0.0358   1.0000
  13.250   0.8370   0.08665   0.08099   0.0177   0.0362   1.0000
  13.500   0.7910   0.10056   0.09504   0.0081   0.0369   1.0000
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