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SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SD5060 (9.5%) (sd5060-il)
Reynolds number: 100,000
Max Cl/Cd: 50.23 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd5060-il-100000-n5.txt
Download as CSV file: xf-sd5060-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD5060 (9.5%)                                   
  
 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  -0.5173   0.08967   0.08471  -0.0195   1.0000   0.0293
  -9.500  -0.5258   0.08285   0.07796  -0.0235   1.0000   0.0294
  -9.250  -0.5353   0.07599   0.07116  -0.0277   1.0000   0.0293
  -9.000  -0.5492   0.06812   0.06335  -0.0334   1.0000   0.0290
  -8.750  -0.5681   0.05933   0.05459  -0.0423   1.0000   0.0284
  -8.500  -0.5836   0.05195   0.04695  -0.0482   1.0000   0.0281
  -8.250  -0.5909   0.04579   0.04036  -0.0514   1.0000   0.0284
  -8.000  -0.5887   0.04082   0.03489  -0.0527   1.0000   0.0286
  -7.750  -0.5800   0.03680   0.03035  -0.0530   1.0000   0.0289
  -7.500  -0.5671   0.03355   0.02656  -0.0526   1.0000   0.0293
  -7.250  -0.5519   0.03085   0.02347  -0.0518   1.0000   0.0298
  -7.000  -0.5361   0.02862   0.02104  -0.0509   1.0000   0.0306
  -6.750  -0.5191   0.02717   0.01948  -0.0498   1.0000   0.0319
  -6.500  -0.5018   0.02598   0.01814  -0.0486   1.0000   0.0339
  -6.250  -0.4845   0.02468   0.01662  -0.0472   1.0000   0.0357
  -6.000  -0.4670   0.02336   0.01508  -0.0456   1.0000   0.0370
  -5.750  -0.4493   0.02222   0.01373  -0.0441   1.0000   0.0382
  -5.500  -0.4208   0.02088   0.01231  -0.0449   0.9952   0.0402
  -5.250  -0.3864   0.01985   0.01119  -0.0467   0.9879   0.0438
  -5.000  -0.3504   0.01894   0.01014  -0.0487   0.9814   0.0503
  -4.750  -0.3158   0.01801   0.00912  -0.0503   0.9740   0.0604
  -4.500  -0.2796   0.01704   0.00825  -0.0524   0.9679   0.0821
  -4.250  -0.2451   0.01643   0.00772  -0.0540   0.9601   0.1165
  -4.000  -0.2100   0.01602   0.00745  -0.0558   0.9531   0.1602
  -3.750  -0.1762   0.01571   0.00717  -0.0572   0.9448   0.1991
  -3.500  -0.1435   0.01538   0.00686  -0.0582   0.9366   0.2259
  -3.250  -0.1102   0.01507   0.00657  -0.0593   0.9286   0.2542
  -3.000  -0.0803   0.01479   0.00632  -0.0597   0.9190   0.2839
  -2.750  -0.0490   0.01451   0.00609  -0.0602   0.9107   0.3175
  -2.500  -0.0203   0.01423   0.00591  -0.0603   0.9009   0.3538
  -2.250   0.0078   0.01398   0.00576  -0.0601   0.8909   0.3955
  -2.000   0.0366   0.01371   0.00560  -0.0600   0.8822   0.4444
  -1.750   0.0630   0.01346   0.00551  -0.0595   0.8717   0.4995
  -1.500   0.0887   0.01322   0.00545  -0.0586   0.8614   0.5610
  -1.250   0.1143   0.01297   0.00538  -0.0576   0.8520   0.6305
  -1.000   0.1381   0.01273   0.00536  -0.0560   0.8416   0.7048
  -0.750   0.1617   0.01252   0.00534  -0.0542   0.8308   0.7847
  -0.500   0.1920   0.01232   0.00525  -0.0536   0.8212   0.8725
  -0.250   0.2377   0.01214   0.00504  -0.0565   0.8113   0.9632
   0.000   0.2716   0.01213   0.00492  -0.0576   0.7992   1.0000
   0.250   0.2966   0.01219   0.00486  -0.0569   0.7868   1.0000
   0.500   0.3218   0.01225   0.00481  -0.0561   0.7742   1.0000
   0.750   0.3472   0.01231   0.00477  -0.0553   0.7613   1.0000
   1.000   0.3727   0.01237   0.00474  -0.0546   0.7477   1.0000
   1.250   0.3983   0.01244   0.00472  -0.0538   0.7332   1.0000
   1.500   0.4239   0.01251   0.00471  -0.0531   0.7177   1.0000
   1.750   0.4496   0.01259   0.00473  -0.0523   0.7014   1.0000
   2.000   0.4754   0.01268   0.00475  -0.0516   0.6844   1.0000
   2.250   0.5012   0.01277   0.00477  -0.0509   0.6668   1.0000
   2.500   0.5270   0.01288   0.00480  -0.0501   0.6489   1.0000
   2.750   0.5528   0.01301   0.00490  -0.0495   0.6285   1.0000
   3.000   0.5785   0.01315   0.00497  -0.0488   0.6076   1.0000
   3.250   0.6041   0.01331   0.00508  -0.0481   0.5849   1.0000
   3.500   0.6296   0.01350   0.00520  -0.0474   0.5610   1.0000
   3.750   0.6548   0.01372   0.00535  -0.0467   0.5343   1.0000
   4.000   0.6799   0.01397   0.00552  -0.0460   0.5061   1.0000
   4.250   0.7047   0.01427   0.00572  -0.0453   0.4760   1.0000
   4.500   0.7291   0.01462   0.00598  -0.0446   0.4445   1.0000
   4.750   0.7533   0.01501   0.00627  -0.0439   0.4111   1.0000
   5.000   0.7771   0.01547   0.00660  -0.0432   0.3772   1.0000
   5.250   0.8005   0.01598   0.00698  -0.0425   0.3447   1.0000
   5.500   0.8237   0.01654   0.00744  -0.0418   0.3143   1.0000
   5.750   0.8468   0.01712   0.00793  -0.0411   0.2866   1.0000
   6.000   0.8698   0.01773   0.00846  -0.0405   0.2617   1.0000
   6.250   0.8924   0.01838   0.00904  -0.0398   0.2405   1.0000
   6.500   0.9152   0.01901   0.00968  -0.0391   0.2217   1.0000
   6.750   0.9376   0.01968   0.01033  -0.0385   0.2050   1.0000
   7.000   0.9599   0.02037   0.01102  -0.0378   0.1903   1.0000
   7.250   0.9820   0.02108   0.01174  -0.0370   0.1773   1.0000
   7.500   1.0037   0.02182   0.01250  -0.0363   0.1654   1.0000
   7.750   1.0248   0.02261   0.01331  -0.0355   0.1547   1.0000
   8.000   1.0459   0.02338   0.01414  -0.0348   0.1443   1.0000
   8.250   1.0670   0.02416   0.01502  -0.0340   0.1342   1.0000
   8.500   1.0870   0.02503   0.01594  -0.0331   0.1255   1.0000
   8.750   1.1063   0.02590   0.01686  -0.0322   0.1166   1.0000
   9.000   1.1259   0.02679   0.01793  -0.0313   0.1080   1.0000
   9.250   1.1434   0.02779   0.01896  -0.0302   0.1005   1.0000
   9.500   1.1613   0.02875   0.02008  -0.0292   0.0925   1.0000
   9.750   1.1774   0.02988   0.02131  -0.0280   0.0858   1.0000
  10.000   1.1926   0.03095   0.02250  -0.0268   0.0789   1.0000
  10.250   1.2064   0.03223   0.02391  -0.0255   0.0728   1.0000
  10.750   1.2277   0.03486   0.02681  -0.0223   0.0619   1.0000
  11.000   1.2353   0.03626   0.02838  -0.0205   0.0569   1.0000
  11.250   1.2379   0.03792   0.03002  -0.0186   0.0532   1.0000
  11.500   1.2441   0.03964   0.03203  -0.0171   0.0485   1.0000
  11.750   1.2462   0.04151   0.03402  -0.0159   0.0450   1.0000
  12.000   1.2454   0.04382   0.03641  -0.0148   0.0419   1.0000
  12.250   1.2461   0.04625   0.03908  -0.0141   0.0383   1.0000
  12.500   1.2439   0.04894   0.04191  -0.0138   0.0358   1.0000
  12.750   1.2381   0.05218   0.04521  -0.0140   0.0340   1.0000
  13.000   1.2329   0.05579   0.04906  -0.0144   0.0320   1.0000
  13.250   1.2260   0.05981   0.05331  -0.0152   0.0303   1.0000
  13.500   1.2175   0.06421   0.05791  -0.0166   0.0290   1.0000
  13.750   1.2076   0.06905   0.06291  -0.0187   0.0279   1.0000
  14.000   1.1959   0.07444   0.06844  -0.0213   0.0271   1.0000
  14.250   1.1829   0.08035   0.07450  -0.0243   0.0265   1.0000
  14.500   1.1688   0.08675   0.08102  -0.0277   0.0260   1.0000
  14.750   1.1548   0.09344   0.08786  -0.0313   0.0256   1.0000
  15.000   1.1371   0.10149   0.09608  -0.0360   0.0254   1.0000
  15.250   1.1186   0.11008   0.10486  -0.0410   0.0253   1.0000
  15.500   1.0993   0.11925   0.11420  -0.0464   0.0253   1.0000
  15.750   1.0802   0.12874   0.12383  -0.0519   0.0254   1.0000
  16.000   1.0580   0.13958   0.13481  -0.0583   0.0255   1.0000
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