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SA7038 (sa7038-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SA7038 (sa7038-il)
Reynolds number: 100,000
Max Cl/Cd: 56.72 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7038-il-100000-n5.txt
Download as CSV file: xf-sa7038-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7038                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3647   0.11146   0.10634  -0.0302   1.0000   0.0496
  -9.500  -0.3706   0.10904   0.10401  -0.0339   1.0000   0.0508
  -9.250  -0.3738   0.10625   0.10130  -0.0365   1.0000   0.0511
  -8.750  -0.3616   0.09810   0.09323  -0.0348   1.0000   0.0531
  -8.500  -0.3584   0.09519   0.09037  -0.0348   1.0000   0.0536
  -8.250  -0.3573   0.09228   0.08752  -0.0346   1.0000   0.0543
  -8.000  -0.3597   0.08952   0.08483  -0.0346   1.0000   0.0545
  -7.750  -0.3018   0.07440   0.07009  -0.0346   1.0000   0.0362
  -7.500  -0.3105   0.07153   0.06730  -0.0333   1.0000   0.0348
  -7.250  -0.3889   0.07996   0.07551  -0.0334   1.0000   0.0367
  -7.000  -0.3960   0.07708   0.07271  -0.0328   1.0000   0.0350
  -6.750  -0.4043   0.07354   0.06923  -0.0336   1.0000   0.0332
  -6.500  -0.4119   0.06491   0.06048  -0.0411   1.0000   0.0281
  -6.250  -0.4126   0.06158   0.05714  -0.0409   1.0000   0.0276
  -6.000  -0.3881   0.05564   0.05102  -0.0474   0.9943   0.0267
  -5.750  -0.3619   0.04934   0.04443  -0.0537   0.9878   0.0258
  -5.500  -0.3317   0.04300   0.03765  -0.0596   0.9823   0.0250
  -5.250  -0.3033   0.03782   0.03194  -0.0633   0.9759   0.0244
  -5.000  -0.2699   0.03322   0.02670  -0.0667   0.9713   0.0239
  -4.750  -0.2395   0.02982   0.02271  -0.0684   0.9655   0.0239
  -4.500  -0.2062   0.02710   0.01945  -0.0701   0.9604   0.0242
  -4.250  -0.1693   0.02515   0.01702  -0.0721   0.9568   0.0259
  -4.000  -0.1391   0.02376   0.01522  -0.0725   0.9499   0.0280
  -3.750  -0.1034   0.02228   0.01345  -0.0740   0.9453   0.0286
  -3.500  -0.0696   0.02063   0.01170  -0.0752   0.9405   0.0299
  -3.250  -0.0384   0.01961   0.01061  -0.0759   0.9335   0.0315
  -3.000  -0.0009   0.01870   0.00957  -0.0777   0.9292   0.0344
  -2.750   0.0283   0.01803   0.00874  -0.0778   0.9209   0.0385
  -2.500   0.0637   0.01718   0.00793  -0.0792   0.9156   0.0546
  -2.250   0.0920   0.01624   0.00739  -0.0795   0.9072   0.1346
  -2.000   0.1237   0.01502   0.00716  -0.0809   0.9012   0.3632
  -1.750   0.1487   0.01435   0.00704  -0.0801   0.8918   0.5251
  -1.500   0.1772   0.01377   0.00688  -0.0793   0.8853   0.6749
  -1.250   0.1989   0.01335   0.00675  -0.0768   0.8752   0.8113
  -1.000   0.2564   0.01292   0.00630  -0.0817   0.8703   1.0000
  -0.750   0.2848   0.01287   0.00605  -0.0817   0.8594   1.0000
  -0.500   0.3123   0.01285   0.00584  -0.0814   0.8478   1.0000
  -0.250   0.3405   0.01282   0.00564  -0.0812   0.8363   1.0000
   0.000   0.3690   0.01278   0.00545  -0.0810   0.8245   1.0000
   0.250   0.3975   0.01274   0.00527  -0.0808   0.8121   1.0000
   0.500   0.4255   0.01272   0.00512  -0.0805   0.7988   1.0000
   0.750   0.4532   0.01271   0.00500  -0.0802   0.7846   1.0000
   1.000   0.4806   0.01272   0.00491  -0.0797   0.7696   1.0000
   1.250   0.5079   0.01275   0.00484  -0.0793   0.7539   1.0000
   1.500   0.5352   0.01279   0.00478  -0.0789   0.7377   1.0000
   1.750   0.5624   0.01285   0.00474  -0.0784   0.7209   1.0000
   2.000   0.5896   0.01292   0.00473  -0.0780   0.7035   1.0000
   2.250   0.6161   0.01304   0.00475  -0.0774   0.6849   1.0000
   2.500   0.6423   0.01317   0.00480  -0.0768   0.6655   1.0000
   2.750   0.6686   0.01333   0.00485  -0.0763   0.6463   1.0000
   3.000   0.6943   0.01351   0.00499  -0.0757   0.6260   1.0000
   3.250   0.7199   0.01372   0.00512  -0.0751   0.6058   1.0000
   3.500   0.7454   0.01395   0.00527  -0.0744   0.5855   1.0000
   3.750   0.7705   0.01420   0.00546  -0.0738   0.5645   1.0000
   4.000   0.7954   0.01447   0.00569  -0.0731   0.5437   1.0000
   4.250   0.8200   0.01476   0.00593  -0.0724   0.5220   1.0000
   4.500   0.8444   0.01508   0.00619  -0.0717   0.5006   1.0000
   4.750   0.8685   0.01542   0.00648  -0.0710   0.4788   1.0000
   5.000   0.8923   0.01578   0.00683  -0.0702   0.4574   1.0000
   5.250   0.9160   0.01616   0.00718  -0.0695   0.4358   1.0000
   5.500   0.9393   0.01656   0.00755  -0.0687   0.4146   1.0000
   5.750   0.9622   0.01699   0.00796  -0.0679   0.3929   1.0000
   6.000   0.9849   0.01745   0.00839  -0.0670   0.3715   1.0000
   6.250   1.0071   0.01794   0.00890  -0.0661   0.3499   1.0000
   6.500   1.0291   0.01845   0.00940  -0.0652   0.3292   1.0000
   6.750   1.0507   0.01899   0.00994  -0.0643   0.3085   1.0000
   7.000   1.0717   0.01958   0.01052  -0.0633   0.2895   1.0000
   7.250   1.0928   0.02017   0.01118  -0.0623   0.2699   1.0000
   7.500   1.1130   0.02081   0.01184  -0.0613   0.2514   1.0000
   7.750   1.1325   0.02151   0.01254  -0.0602   0.2333   1.0000
   8.000   1.1519   0.02221   0.01329  -0.0591   0.2147   1.0000
   8.250   1.1701   0.02297   0.01407  -0.0578   0.1963   1.0000
   8.500   1.1873   0.02381   0.01491  -0.0565   0.1793   1.0000
   8.750   1.2044   0.02465   0.01584  -0.0551   0.1627   1.0000
   9.000   1.2206   0.02554   0.01680  -0.0537   0.1473   1.0000
   9.250   1.2357   0.02650   0.01782  -0.0522   0.1326   1.0000
   9.500   1.2494   0.02754   0.01892  -0.0505   0.1193   1.0000
   9.750   1.2616   0.02865   0.02009  -0.0487   0.1070   1.0000
  10.000   1.2709   0.02983   0.02131  -0.0465   0.0961   1.0000
  10.250   1.2783   0.03114   0.02268  -0.0442   0.0868   1.0000
  10.500   1.2864   0.03248   0.02415  -0.0421   0.0778   1.0000
  10.750   1.2916   0.03403   0.02582  -0.0399   0.0702   1.0000
  11.000   1.2955   0.03571   0.02760  -0.0378   0.0636   1.0000
  11.250   1.2989   0.03756   0.02958  -0.0358   0.0579   1.0000
  11.500   1.3000   0.03955   0.03163  -0.0341   0.0514   1.0000
  11.750   1.3033   0.04152   0.03376  -0.0328   0.0444   1.0000
  12.000   1.3005   0.04405   0.03631  -0.0316   0.0393   1.0000
  12.250   1.3019   0.04642   0.03890  -0.0308   0.0339   1.0000
  12.500   1.2960   0.04963   0.04218  -0.0303   0.0308   1.0000
  12.750   1.2909   0.05301   0.04576  -0.0300   0.0279   1.0000
  13.000   1.2847   0.05672   0.04967  -0.0301   0.0256   1.0000
  13.250   1.2768   0.06084   0.05396  -0.0307   0.0241   1.0000
  13.500   1.2659   0.06560   0.05885  -0.0320   0.0229   1.0000
  13.750   1.2525   0.07098   0.06435  -0.0337   0.0220   1.0000
  14.000   1.2437   0.07599   0.06956  -0.0353   0.0211   1.0000
  14.250   1.2343   0.08130   0.07509  -0.0372   0.0204   1.0000
  14.500   1.2234   0.08713   0.08114  -0.0396   0.0195   1.0000
  14.750   1.2126   0.09315   0.08734  -0.0423   0.0190   1.0000
  15.000   1.2013   0.09949   0.09386  -0.0454   0.0185   1.0000
  15.250   1.1894   0.10620   0.10074  -0.0488   0.0181   1.0000
  15.500   1.1774   0.11316   0.10787  -0.0525   0.0177   1.0000
  15.750   1.1655   0.12034   0.11522  -0.0564   0.0176   1.0000
  16.000   1.1528   0.12801   0.12303  -0.0608   0.0173   1.0000
  16.250   1.1396   0.13609   0.13128  -0.0654   0.0173   1.0000
  16.500   1.1251   0.14485   0.14019  -0.0705   0.0173   1.0000
  16.750   1.1061   0.15556   0.15109  -0.0769   0.0177   1.0000
  17.000   1.0781   0.17011   0.16579  -0.0854   0.0186   1.0000
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