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TSAGI 12% AIRFOIL (tsagi12-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: TSAGI 12% AIRFOIL (tsagi12-il)
Reynolds number: 100,000
Max Cl/Cd: 49.59 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-tsagi12-il-100000.txt
Download as CSV file: xf-tsagi12-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TSAGI 12% AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4630   0.10460   0.09958  -0.0223   1.0000   0.1229
 -10.000  -0.4758   0.10087   0.09594  -0.0257   1.0000   0.1282
  -9.750  -0.5191   0.09595   0.09118  -0.0346   1.0000   0.1298
  -9.500  -0.4741   0.09291   0.08804  -0.0268   1.0000   0.1348
  -9.250  -0.4766   0.08942   0.08460  -0.0279   1.0000   0.1400
  -9.000  -0.5223   0.08452   0.07984  -0.0346   1.0000   0.1436
  -8.750  -0.5756   0.08242   0.07773  -0.0331   1.0000   0.1444
  -8.500  -0.5102   0.07724   0.07262  -0.0320   1.0000   0.1519
  -8.250  -0.5377   0.07436   0.06978  -0.0305   1.0000   0.1561
  -8.000  -0.6068   0.07392   0.06909  -0.0266   1.0000   0.1594
  -7.750  -0.5547   0.06795   0.06341  -0.0268   1.0000   0.1658
  -7.500  -0.6100   0.06809   0.06322  -0.0215   1.0000   0.1743
  -7.250  -0.6359   0.04991   0.04411  -0.0181   1.0000   0.0857
  -7.000  -0.6384   0.04645   0.04053  -0.0141   1.0000   0.0824
  -6.750  -0.6470   0.04327   0.03704  -0.0088   1.0000   0.0803
  -6.500  -0.6521   0.04084   0.03433  -0.0039   1.0000   0.0801
  -6.250  -0.6557   0.03839   0.03154   0.0010   1.0000   0.0795
  -6.000  -0.6562   0.03603   0.02882   0.0055   1.0000   0.0793
  -5.750  -0.6531   0.03384   0.02624   0.0095   1.0000   0.0790
  -5.500  -0.6461   0.03203   0.02411   0.0128   1.0000   0.0802
  -5.250  -0.6371   0.03069   0.02245   0.0158   1.0000   0.0833
  -5.000  -0.5982   0.02890   0.01995   0.0139   0.9925   0.0877
  -4.750  -0.5562   0.02656   0.01757   0.0105   0.9853   0.0949
  -4.500  -0.5118   0.02500   0.01564   0.0075   0.9768   0.1026
  -4.250  -0.4621   0.02365   0.01421   0.0031   0.9697   0.1157
  -4.000  -0.4202   0.02229   0.01291   0.0003   0.9599   0.1304
  -3.750  -0.3769   0.02111   0.01193  -0.0030   0.9517   0.1568
  -3.500  -0.3367   0.01997   0.01104  -0.0056   0.9428   0.1936
  -3.250  -0.3034   0.01883   0.01036  -0.0070   0.9329   0.2590
  -3.000  -0.1734   0.01786   0.01208  -0.0214   0.9468   0.9028
  -2.750  -0.0798   0.01887   0.01268  -0.0320   0.9470   0.9441
  -2.500   0.0359   0.01886   0.01233  -0.0479   0.9510   0.9781
  -2.250   0.1306   0.01796   0.01118  -0.0614   0.9494   1.0000
  -2.000   0.1808   0.01745   0.01050  -0.0665   0.9364   1.0000
  -1.750   0.2258   0.01700   0.00991  -0.0705   0.9209   1.0000
  -1.500   0.2644   0.01666   0.00944  -0.0731   0.9036   1.0000
  -1.250   0.2967   0.01643   0.00909  -0.0743   0.8855   1.0000
  -1.000   0.3243   0.01629   0.00883  -0.0744   0.8676   1.0000
  -0.750   0.3478   0.01623   0.00866  -0.0737   0.8504   1.0000
  -0.500   0.3690   0.01623   0.00855  -0.0725   0.8339   1.0000
  -0.250   0.3886   0.01627   0.00850  -0.0709   0.8174   1.0000
   0.000   0.4078   0.01634   0.00849  -0.0693   0.8013   1.0000
   0.250   0.4272   0.01641   0.00850  -0.0678   0.7859   1.0000
   0.500   0.4468   0.01650   0.00851  -0.0662   0.7709   1.0000
   0.750   0.4667   0.01659   0.00853  -0.0646   0.7564   1.0000
   1.000   0.4869   0.01669   0.00856  -0.0631   0.7425   1.0000
   1.250   0.5069   0.01681   0.00866  -0.0617   0.7283   1.0000
   1.500   0.5270   0.01695   0.00876  -0.0602   0.7143   1.0000
   1.750   0.5474   0.01711   0.00890  -0.0589   0.7009   1.0000
   2.000   0.5680   0.01728   0.00905  -0.0575   0.6881   1.0000
   2.250   0.5889   0.01745   0.00921  -0.0562   0.6761   1.0000
   2.500   0.6109   0.01760   0.00931  -0.0550   0.6653   1.0000
   2.750   0.6318   0.01779   0.00952  -0.0538   0.6534   1.0000
   3.000   0.6524   0.01804   0.00982  -0.0525   0.6417   1.0000
   3.250   0.6737   0.01827   0.01007  -0.0513   0.6311   1.0000
   3.500   0.6965   0.01842   0.01019  -0.0502   0.6216   1.0000
   3.750   0.7164   0.01872   0.01058  -0.0489   0.6100   1.0000
   4.000   0.7373   0.01900   0.01094  -0.0477   0.5995   1.0000
   4.250   0.7605   0.01916   0.01107  -0.0466   0.5906   1.0000
   4.500   0.7801   0.01948   0.01151  -0.0452   0.5792   1.0000
   4.750   0.8004   0.01980   0.01192  -0.0439   0.5687   1.0000
   5.000   0.8231   0.01998   0.01214  -0.0427   0.5595   1.0000
   5.250   0.8433   0.02028   0.01255  -0.0413   0.5486   1.0000
   5.500   0.8629   0.02059   0.01298  -0.0398   0.5372   1.0000
   5.750   0.8836   0.02077   0.01323  -0.0383   0.5254   1.0000
   6.000   0.9045   0.02080   0.01333  -0.0367   0.5118   1.0000
   6.250   0.9247   0.02081   0.01339  -0.0349   0.4969   1.0000
   6.500   0.9440   0.02074   0.01336  -0.0329   0.4794   1.0000
   6.750   0.9637   0.02039   0.01292  -0.0306   0.4576   1.0000
   7.000   0.9778   0.02028   0.01288  -0.0278   0.4324   1.0000
   7.250   0.9926   0.02026   0.01289  -0.0251   0.4083   1.0000
   7.500   1.0060   0.02034   0.01302  -0.0222   0.3829   1.0000
   7.750   1.0156   0.02048   0.01328  -0.0188   0.3493   1.0000
   8.000   1.0186   0.02086   0.01358  -0.0143   0.2857   1.0000
   8.250   1.0003   0.02292   0.01472  -0.0073   0.1661   1.0000
   8.500   0.9821   0.02538   0.01655  -0.0006   0.1129   1.0000
   8.750   0.9718   0.02719   0.01822   0.0051   0.0951   1.0000
   9.000   0.9627   0.02866   0.01961   0.0105   0.0874   1.0000
   9.250   0.9559   0.02998   0.02095   0.0157   0.0799   1.0000
   9.500   0.9504   0.03151   0.02238   0.0200   0.0746   1.0000
   9.750   0.9546   0.03291   0.02383   0.0231   0.0695   1.0000
  10.000   0.9635   0.03437   0.02526   0.0256   0.0651   1.0000
  10.250   0.9896   0.03641   0.02716   0.0261   0.0607   1.0000
  10.500   1.0065   0.03793   0.02886   0.0277   0.0574   1.0000
  10.750   1.0235   0.03966   0.03069   0.0289   0.0541   1.0000
  11.000   1.0660   0.04282   0.03387   0.0267   0.0516   1.0000
  11.250   1.0992   0.04723   0.03850   0.0251   0.0505   1.0000
  11.500   1.0979   0.04930   0.04090   0.0286   0.0500   1.0000
  11.750   1.0935   0.05143   0.04330   0.0323   0.0496   1.0000
  12.000   1.0833   0.05348   0.04562   0.0363   0.0491   1.0000
  12.250   1.0719   0.05581   0.04822   0.0396   0.0486   1.0000
  12.500   1.0584   0.05851   0.05118   0.0423   0.0482   1.0000
  12.750   1.0461   0.06175   0.05466   0.0443   0.0483   1.0000
  13.000   1.0313   0.06526   0.05840   0.0456   0.0485   1.0000
  13.250   1.0148   0.06915   0.06251   0.0464   0.0488   1.0000
  13.500   0.9973   0.07338   0.06693   0.0465   0.0491   1.0000
  13.750   0.9781   0.07817   0.07190   0.0460   0.0495   1.0000
  14.000   0.9582   0.08334   0.07723   0.0448   0.0498   1.0000
  14.250   0.9400   0.08891   0.08293   0.0433   0.0502   1.0000
  14.500   0.9257   0.09451   0.08866   0.0417   0.0508   1.0000
  14.750   0.8911   0.10130   0.09567   0.0372   0.0514   1.0000
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