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NACA 747A315 (naca747a315-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 747A315 (naca747a315-il)
Reynolds number: 50,000
Max Cl/Cd: 17.34 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca747a315-il-50000-n5.txt
Download as CSV file: xf-naca747a315-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 747A315                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.3182   0.13515   0.12883  -0.0239   1.0000   0.1277
 -13.000  -0.3215   0.13222   0.12590  -0.0260   1.0000   0.1257
 -12.500  -0.4634   0.12437   0.11734  -0.0286   1.0000   0.0670
 -12.250  -0.4545   0.12052   0.11350  -0.0295   1.0000   0.0661
 -12.000  -0.4523   0.11598   0.10899  -0.0316   1.0000   0.0657
 -11.750  -0.4516   0.11127   0.10433  -0.0341   1.0000   0.0653
 -11.500  -0.4529   0.10625   0.09936  -0.0369   1.0000   0.0651
 -11.250  -0.4566   0.10074   0.09391  -0.0402   1.0000   0.0648
 -11.000  -0.4613   0.09498   0.08820  -0.0439   1.0000   0.0642
 -10.750  -0.4717   0.08812   0.08138  -0.0490   1.0000   0.0635
 -10.500  -0.4887   0.08164   0.07492  -0.0534   1.0000   0.0626
 -10.250  -0.5100   0.07609   0.06936  -0.0563   1.0000   0.0618
 -10.000  -0.5334   0.07159   0.06481  -0.0572   1.0000   0.0611
  -9.750  -0.5581   0.06832   0.06149  -0.0558   1.0000   0.0607
  -9.500  -0.5880   0.06666   0.05983  -0.0513   1.0000   0.0603
  -9.250  -0.5903   0.06219   0.05501  -0.0530   0.9754   0.0602
  -9.000  -0.5848   0.05785   0.05024  -0.0544   0.9586   0.0602
  -8.750  -0.5755   0.05408   0.04601  -0.0551   0.9438   0.0604
  -8.500  -0.5637   0.05080   0.04230  -0.0551   0.9302   0.0609
  -8.250  -0.5499   0.04811   0.03918  -0.0548   0.9174   0.0623
  -8.000  -0.5351   0.04561   0.03622  -0.0540   0.9057   0.0641
  -7.750  -0.5215   0.04341   0.03352  -0.0525   0.8931   0.0657
  -7.500  -0.5045   0.04132   0.03089  -0.0511   0.8818   0.0670
  -7.250  -0.4800   0.03916   0.02849  -0.0509   0.8733   0.0686
  -7.000  -0.4584   0.03772   0.02692  -0.0503   0.8626   0.0710
  -6.750  -0.4336   0.03632   0.02527  -0.0499   0.8542   0.0748
  -6.500  -0.4065   0.03489   0.02347  -0.0496   0.8452   0.0783
  -6.250  -0.3747   0.03341   0.02193  -0.0501   0.8380   0.0822
  -6.000  -0.3449   0.03238   0.02080  -0.0504   0.8296   0.0884
  -5.750  -0.3076   0.03119   0.01946  -0.0513   0.8239   0.0952
  -5.500  -0.2789   0.03041   0.01861  -0.0515   0.8152   0.1042
  -5.250  -0.2522   0.02953   0.01772  -0.0512   0.8087   0.1146
  -5.000  -0.2308   0.02883   0.01701  -0.0503   0.8011   0.1286
  -4.750  -0.2117   0.02806   0.01631  -0.0490   0.7941   0.1494
  -4.500  -0.1961   0.02708   0.01562  -0.0472   0.7882   0.1892
  -4.250  -0.1913   0.02586   0.01521  -0.0442   0.7802   0.2957
  -4.000  -0.1285   0.02643   0.01761  -0.0439   0.7772   0.7171
  -3.750  -0.1262   0.02699   0.01797  -0.0385   0.7712   0.7704
  -3.500  -0.0606   0.02932   0.01996  -0.0402   0.7662   0.8474
  -3.250  -0.0006   0.03004   0.02033  -0.0440   0.7617   0.8862
  -3.000   0.0405   0.03002   0.02001  -0.0462   0.7575   0.9041
  -2.750   0.0820   0.02986   0.01960  -0.0491   0.7528   0.9169
  -2.500   0.1192   0.02973   0.01929  -0.0516   0.7470   0.9275
  -2.250   0.1499   0.02959   0.01895  -0.0528   0.7421   0.9370
  -2.000   0.1842   0.02931   0.01848  -0.0545   0.7383   0.9452
  -1.750   0.2162   0.02934   0.01840  -0.0566   0.7322   0.9532
  -1.500   0.2470   0.02931   0.01825  -0.0580   0.7274   0.9617
  -1.250   0.2827   0.02910   0.01791  -0.0603   0.7237   0.9684
  -1.000   0.3142   0.02903   0.01773  -0.0618   0.7203   0.9754
  -0.750   0.3463   0.02920   0.01786  -0.0641   0.7150   0.9816
  -0.500   0.3773   0.02924   0.01785  -0.0659   0.7105   0.9872
  -0.250   0.4084   0.02921   0.01774  -0.0673   0.7069   0.9923
   0.000   0.4394   0.02917   0.01763  -0.0686   0.7038   0.9969
   0.250   0.4639   0.02973   0.01823  -0.0699   0.6986   1.0000
   0.500   0.4813   0.03025   0.01875  -0.0692   0.6943   1.0000
   0.750   0.4996   0.03062   0.01911  -0.0684   0.6907   1.0000
   1.000   0.5190   0.03087   0.01933  -0.0674   0.6878   1.0000
   1.250   0.5314   0.03183   0.02036  -0.0665   0.6823   1.0000
   1.500   0.5450   0.03261   0.02117  -0.0654   0.6778   1.0000
   1.750   0.5614   0.03311   0.02169  -0.0642   0.6742   1.0000
   2.000   0.5800   0.03345   0.02203  -0.0630   0.6712   1.0000
   2.250   0.5843   0.03478   0.02345  -0.0611   0.6652   1.0000
   2.500   0.5931   0.03572   0.02445  -0.0592   0.6602   1.0000
   2.750   0.6090   0.03618   0.02494  -0.0577   0.6565   1.0000
   3.000   0.6289   0.03644   0.02523  -0.0565   0.6538   1.0000
   3.250   0.6148   0.03852   0.02739  -0.0525   0.6451   1.0000
   3.500   0.6266   0.03916   0.02809  -0.0505   0.6408   1.0000
   3.750   0.6468   0.03938   0.02836  -0.0493   0.6378   1.0000
   4.000   0.6237   0.04159   0.03062  -0.0440   0.6285   1.0000
   4.250   0.6355   0.04214   0.03123  -0.0418   0.6239   1.0000
   4.500   0.6577   0.04228   0.03145  -0.0407   0.6209   1.0000
   5.000   0.6404   0.04490   0.03416  -0.0323   0.6060   1.0000
   5.500   0.6172   0.04715   0.03645  -0.0226   0.5907   1.0000
   5.750   0.6436   0.04717   0.03658  -0.0219   0.5870   1.0000
   6.000   0.6053   0.04894   0.03830  -0.0143   0.5754   1.0000
   6.250   0.6353   0.04880   0.03830  -0.0138   0.5715   1.0000
   6.500   0.6096   0.05044   0.03990  -0.0081   0.5597   1.0000
   6.750   0.6411   0.05020   0.03980  -0.0076   0.5554   1.0000
   7.000   0.6269   0.05176   0.04136  -0.0037   0.5432   1.0000
   7.250   0.6626   0.05125   0.04102  -0.0035   0.5388   1.0000
   7.500   0.6550   0.05278   0.04258  -0.0005   0.5259   1.0000
   7.750   0.6603   0.05380   0.04371   0.0014   0.5149   1.0000
   8.000   0.6904   0.05338   0.04346   0.0021   0.5081   1.0000
   8.250   0.6929   0.05459   0.04476   0.0040   0.4950   1.0000
   8.500   0.7041   0.05527   0.04557   0.0055   0.4832   1.0000
   8.750   0.7395   0.05398   0.04453   0.0065   0.4753   1.0000
   9.000   0.7487   0.05445   0.04513   0.0082   0.4604   1.0000
   9.250   0.7626   0.05436   0.04520   0.0099   0.4449   1.0000
   9.500   0.7798   0.05379   0.04482   0.0118   0.4286   1.0000
   9.750   0.7805   0.05500   0.04615   0.0133   0.4080   1.0000
  10.000   0.7948   0.05467   0.04600   0.0150   0.3879   1.0000
  10.250   0.8096   0.05388   0.04536   0.0170   0.3610   1.0000
  10.500   0.8337   0.05184   0.04332   0.0194   0.3181   1.0000
  10.750   0.8549   0.05049   0.04156   0.0220   0.2581   1.0000
  11.000   0.8562   0.05200   0.04263   0.0237   0.2105   1.0000
  11.250   0.8514   0.05457   0.04486   0.0247   0.1751   1.0000
  11.500   0.8468   0.05740   0.04742   0.0254   0.1483   1.0000
  11.750   0.8434   0.06027   0.05007   0.0260   0.1282   1.0000
  12.000   0.8426   0.06301   0.05263   0.0264   0.1132   1.0000
  12.250   0.8448   0.06551   0.05504   0.0268   0.1009   1.0000
  12.500   0.8505   0.06771   0.05721   0.0273   0.0915   1.0000
  12.750   0.8573   0.06978   0.05921   0.0278   0.0846   1.0000
  13.000   0.8671   0.07167   0.06119   0.0283   0.0780   1.0000
  13.250   0.8787   0.07331   0.06279   0.0290   0.0733   1.0000
  13.500   0.8920   0.07502   0.06472   0.0295   0.0686   1.0000
  13.750   0.9047   0.07667   0.06638   0.0300   0.0649   1.0000
  14.000   0.9202   0.07837   0.06824   0.0306   0.0616   1.0000
  14.250   0.9334   0.08052   0.07066   0.0310   0.0590   1.0000
  14.500   0.9432   0.08291   0.07321   0.0310   0.0566   1.0000
  14.750   0.9563   0.08486   0.07519   0.0312   0.0546   1.0000
  15.000   0.9559   0.08873   0.07932   0.0305   0.0533   1.0000
  15.250   0.9493   0.09345   0.08437   0.0292   0.0524   1.0000
  15.500   0.9400   0.09870   0.08990   0.0274   0.0518   1.0000
  15.750   0.9265   0.10473   0.09620   0.0250   0.0515   1.0000
  16.000   0.9083   0.11181   0.10354   0.0217   0.0515   1.0000
  16.250   0.8844   0.12048   0.11243   0.0172   0.0516   1.0000
  16.500   0.8551   0.13114   0.12329   0.0111   0.0520   1.0000
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