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S2060 8% (s2060-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S2060 8% (s2060-il)
Reynolds number: 50,000
Max Cl/Cd: 36.4 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2060-il-50000.txt
Download as CSV file: xf-s2060-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2060 8%                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4668   0.09358   0.08679  -0.0081   1.0000   0.2927
  -7.500  -0.4682   0.09083   0.08413  -0.0074   1.0000   0.3076
  -7.250  -0.4694   0.08804   0.08142  -0.0063   1.0000   0.3223
  -7.000  -0.4748   0.08557   0.07906  -0.0050   1.0000   0.3372
  -6.750  -0.4566   0.08147   0.07495  -0.0024   1.0000   0.3645
  -6.500  -0.4489   0.07834   0.07183   0.0003   1.0000   0.3927
  -6.250  -0.4411   0.07496   0.06849   0.0025   1.0000   0.4149
  -6.000  -0.4844   0.06148   0.05496  -0.0310   1.0000   0.2041
  -5.750  -0.4731   0.05048   0.04323  -0.0406   1.0000   0.1459
  -5.500  -0.4591   0.04493   0.03716  -0.0422   1.0000   0.1407
  -5.250  -0.4421   0.04115   0.03301  -0.0422   1.0000   0.1447
  -5.000  -0.4220   0.03697   0.02823  -0.0424   1.0000   0.1460
  -4.750  -0.4016   0.03399   0.02485  -0.0420   1.0000   0.1563
  -4.500  -0.3777   0.03100   0.02120  -0.0416   1.0000   0.1633
  -4.250  -0.3551   0.02891   0.01876  -0.0409   1.0000   0.1782
  -4.000  -0.3312   0.02681   0.01644  -0.0401   1.0000   0.1903
  -3.750  -0.3074   0.02515   0.01455  -0.0392   1.0000   0.2094
  -3.500  -0.2838   0.02361   0.01300  -0.0382   1.0000   0.2304
  -3.250  -0.2599   0.02225   0.01164  -0.0373   1.0000   0.2611
  -3.000  -0.2368   0.02092   0.01041  -0.0361   1.0000   0.3049
  -2.750  -0.2136   0.01944   0.00939  -0.0349   1.0000   0.3865
  -2.500  -0.1992   0.01746   0.00888  -0.0310   1.0000   0.5905
  -2.250  -0.1495   0.01639   0.00852  -0.0289   1.0000   1.0000
  -2.000  -0.1360   0.01621   0.00789  -0.0278   1.0000   1.0000
  -1.750  -0.1170   0.01617   0.00743  -0.0272   1.0000   1.0000
  -1.500  -0.0966   0.01620   0.00713  -0.0267   1.0000   1.0000
  -1.250  -0.0756   0.01628   0.00692  -0.0262   1.0000   1.0000
  -1.000  -0.0543   0.01639   0.00679  -0.0257   1.0000   1.0000
  -0.750  -0.0329   0.01655   0.00670  -0.0252   1.0000   1.0000
  -0.500  -0.0116   0.01674   0.00670  -0.0247   1.0000   1.0000
  -0.250   0.0096   0.01696   0.00676  -0.0243   1.0000   1.0000
   0.000   0.0307   0.01722   0.00688  -0.0239   1.0000   1.0000
   0.250   0.0515   0.01752   0.00707  -0.0235   1.0000   1.0000
   0.500   0.0721   0.01785   0.00729  -0.0231   1.0000   1.0000
   0.750   0.0923   0.01824   0.00760  -0.0227   1.0000   1.0000
   1.000   0.1122   0.01866   0.00797  -0.0224   1.0000   1.0000
   1.250   0.1317   0.01915   0.00841  -0.0221   1.0000   1.0000
   1.500   0.1508   0.01968   0.00892  -0.0219   1.0000   1.0000
   1.750   0.1694   0.02028   0.00951  -0.0217   1.0000   1.0000
   2.000   0.1874   0.02095   0.01019  -0.0216   1.0000   1.0000
   2.250   0.2049   0.02170   0.01096  -0.0216   1.0000   1.0000
   2.500   0.2218   0.02253   0.01184  -0.0216   1.0000   1.0000
   2.750   0.2844   0.02408   0.01353  -0.0301   0.9760   1.0000
   3.000   0.3465   0.02532   0.01495  -0.0378   0.9493   1.0000
   3.250   0.4068   0.02621   0.01610  -0.0445   0.9211   1.0000
   3.500   0.4661   0.02674   0.01690  -0.0503   0.8914   1.0000
   3.750   0.5286   0.02679   0.01734  -0.0555   0.8603   1.0000
   4.000   0.5999   0.02607   0.01706  -0.0607   0.8286   1.0000
   4.250   0.6475   0.02532   0.01665  -0.0614   0.7920   1.0000
   4.500   0.6967   0.02406   0.01578  -0.0610   0.7532   1.0000
   4.750   0.7344   0.02297   0.01492  -0.0586   0.7074   1.0000
   5.000   0.7656   0.02218   0.01424  -0.0553   0.6537   1.0000
   5.250   0.7900   0.02197   0.01393  -0.0515   0.5898   1.0000
   5.500   0.8098   0.02225   0.01394  -0.0477   0.5168   1.0000
   5.750   0.8251   0.02303   0.01433  -0.0438   0.4350   1.0000
   6.000   0.8372   0.02435   0.01505  -0.0401   0.3451   1.0000
   6.250   0.8447   0.02620   0.01621  -0.0364   0.2485   1.0000
   6.500   0.8573   0.02875   0.01810  -0.0338   0.1725   1.0000
   6.750   0.8812   0.03146   0.02063  -0.0325   0.1364   1.0000
   7.000   0.9073   0.03420   0.02325  -0.0318   0.1185   1.0000
   7.250   0.9336   0.03712   0.02658  -0.0308   0.1102   1.0000
   7.500   0.9583   0.04065   0.03026  -0.0301   0.1054   1.0000
   7.750   0.9751   0.04402   0.03433  -0.0284   0.1019   1.0000
   8.000   0.9898   0.04745   0.03826  -0.0268   0.0982   1.0000
   8.250   1.0026   0.05120   0.04246  -0.0253   0.0963   1.0000
   8.500   1.0070   0.05593   0.04781  -0.0235   0.0974   1.0000
   8.750   1.0055   0.06104   0.05346  -0.0218   0.0995   1.0000
   9.000   1.0000   0.06627   0.05909  -0.0205   0.1017   1.0000
   9.250   0.9954   0.07145   0.06452  -0.0197   0.1038   1.0000
   9.500   1.0060   0.07705   0.07015  -0.0194   0.1060   1.0000
   9.750   0.9433   0.08254   0.07612  -0.0195   0.1101   1.0000
  10.000   0.9069   0.08966   0.08325  -0.0229   0.1137   1.0000
  10.250   0.8956   0.09644   0.09003  -0.0259   0.1175   1.0000
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