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S6061 9% (s6061-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S6061 9% (s6061-il)
Reynolds number: 100,000
Max Cl/Cd: 51.18 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s6061-il-100000.txt
Download as CSV file: xf-s6061-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6061 9%                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4949   0.11141   0.10649  -0.0089   1.0000   0.0884
  -9.500  -0.5110   0.10866   0.10385  -0.0154   1.0000   0.0905
  -9.250  -0.5109   0.10373   0.09900  -0.0174   1.0000   0.0917
  -9.000  -0.4872   0.09985   0.09506  -0.0135   1.0000   0.0952
  -8.750  -0.3943   0.08801   0.08360  -0.0175   1.0000   0.1111
  -8.500  -0.4016   0.08414   0.07978  -0.0199   1.0000   0.1160
  -8.250  -0.4240   0.08002   0.07576  -0.0252   1.0000   0.1177
  -8.000  -0.4860   0.08510   0.08055  -0.0207   1.0000   0.1095
  -7.750  -0.4917   0.08164   0.07717  -0.0235   1.0000   0.1151
  -7.500  -0.5167   0.07673   0.07221  -0.0343   1.0000   0.1179
  -7.250  -0.4929   0.07362   0.06924  -0.0280   1.0000   0.1243
  -7.000  -0.5154   0.06949   0.06482  -0.0373   1.0000   0.1320
  -6.750  -0.4464   0.05391   0.04988  -0.0329   1.0000   0.1480
  -6.500  -0.4352   0.05080   0.04682  -0.0307   1.0000   0.1538
  -5.500  -0.4696   0.03714   0.03054  -0.0348   1.0000   0.0658
  -5.250  -0.4551   0.03381   0.02700  -0.0329   1.0000   0.0601
  -5.000  -0.4403   0.03005   0.02260  -0.0308   1.0000   0.0550
  -4.750  -0.4213   0.02783   0.01966  -0.0285   1.0000   0.0521
  -4.500  -0.4021   0.02581   0.01729  -0.0269   1.0000   0.0518
  -4.250  -0.3818   0.02349   0.01469  -0.0255   1.0000   0.0525
  -4.000  -0.3613   0.02164   0.01277  -0.0243   1.0000   0.0551
  -3.750  -0.3409   0.02062   0.01165  -0.0231   1.0000   0.0613
  -3.500  -0.3199   0.01919   0.01022  -0.0218   1.0000   0.0686
  -3.250  -0.2993   0.01794   0.00902  -0.0205   1.0000   0.0823
  -3.000  -0.2791   0.01644   0.00791  -0.0194   1.0000   0.1462
  -2.750  -0.2630   0.01416   0.00730  -0.0183   1.0000   0.4200
  -2.500  -0.2535   0.01324   0.00756  -0.0140   1.0000   0.6927
  -2.250  -0.2447   0.01318   0.00783  -0.0088   1.0000   0.8398
  -2.000  -0.1583   0.01340   0.00779  -0.0180   1.0000   0.9963
  -1.750  -0.1448   0.01345   0.00757  -0.0173   0.9986   1.0000
  -1.500  -0.0965   0.01375   0.00756  -0.0224   0.9892   1.0000
  -1.250  -0.0489   0.01406   0.00760  -0.0272   0.9800   1.0000
  -1.000  -0.0001   0.01434   0.00765  -0.0320   0.9711   1.0000
  -0.750   0.0435   0.01455   0.00769  -0.0358   0.9604   1.0000
  -0.500   0.0881   0.01476   0.00775  -0.0396   0.9501   1.0000
  -0.250   0.1423   0.01491   0.00777  -0.0451   0.9427   1.0000
   0.000   0.1849   0.01501   0.00779  -0.0483   0.9313   1.0000
   0.250   0.2290   0.01506   0.00779  -0.0517   0.9203   1.0000
   0.500   0.2721   0.01507   0.00776  -0.0546   0.9095   1.0000
   0.750   0.3158   0.01502   0.00768  -0.0575   0.8993   1.0000
   1.000   0.3511   0.01498   0.00763  -0.0586   0.8870   1.0000
   1.250   0.3802   0.01499   0.00765  -0.0584   0.8733   1.0000
   1.500   0.4071   0.01500   0.00765  -0.0578   0.8593   1.0000
   1.750   0.4325   0.01500   0.00765  -0.0567   0.8451   1.0000
   2.000   0.4569   0.01500   0.00764  -0.0554   0.8307   1.0000
   2.250   0.4807   0.01498   0.00766  -0.0539   0.8161   1.0000
   2.500   0.5040   0.01498   0.00766  -0.0523   0.8008   1.0000
   2.750   0.5264   0.01502   0.00772  -0.0507   0.7841   1.0000
   3.000   0.5496   0.01503   0.00775  -0.0491   0.7672   1.0000
   3.250   0.5733   0.01500   0.00778  -0.0475   0.7501   1.0000
   3.500   0.5976   0.01493   0.00773  -0.0459   0.7327   1.0000
   3.750   0.6212   0.01494   0.00777  -0.0444   0.7128   1.0000
   4.000   0.6452   0.01492   0.00777  -0.0429   0.6919   1.0000
   4.250   0.6692   0.01494   0.00785  -0.0414   0.6694   1.0000
   4.500   0.6937   0.01494   0.00784  -0.0399   0.6462   1.0000
   4.750   0.7173   0.01501   0.00794  -0.0385   0.6189   1.0000
   5.000   0.7407   0.01512   0.00805  -0.0370   0.5890   1.0000
   5.250   0.7635   0.01528   0.00828  -0.0356   0.5548   1.0000
   5.500   0.7861   0.01549   0.00844  -0.0341   0.5179   1.0000
   5.750   0.8076   0.01578   0.00868  -0.0325   0.4747   1.0000
   6.000   0.8275   0.01618   0.00896  -0.0308   0.4233   1.0000
   6.250   0.8453   0.01675   0.00931  -0.0291   0.3600   1.0000
   6.500   0.8621   0.01758   0.00987  -0.0275   0.2928   1.0000
   6.750   0.8779   0.01868   0.01068  -0.0259   0.2186   1.0000
   7.000   0.8845   0.02123   0.01235  -0.0234   0.1089   1.0000
   7.250   0.8950   0.02355   0.01432  -0.0210   0.0784   1.0000
   7.500   0.9122   0.02529   0.01605  -0.0193   0.0682   1.0000
   7.750   0.9324   0.02736   0.01810  -0.0180   0.0623   1.0000
   8.000   0.9540   0.02900   0.01981  -0.0170   0.0563   1.0000
   8.250   0.9786   0.03199   0.02280  -0.0166   0.0528   1.0000
   8.500   1.0024   0.03442   0.02558  -0.0157   0.0514   1.0000
   8.750   1.0234   0.03738   0.02894  -0.0145   0.0506   1.0000
   9.000   1.0403   0.04072   0.03274  -0.0131   0.0503   1.0000
   9.250   1.0519   0.04405   0.03656  -0.0113   0.0495   1.0000
   9.500   1.0592   0.04739   0.04037  -0.0094   0.0483   1.0000
   9.750   1.0616   0.05114   0.04457  -0.0074   0.0479   1.0000
  10.000   1.0581   0.05550   0.04936  -0.0054   0.0488   1.0000
  10.250   1.0499   0.05995   0.05415  -0.0034   0.0498   1.0000
  10.500   1.0388   0.06423   0.05869  -0.0017   0.0508   1.0000
  10.750   1.0241   0.06836   0.06300   0.0000   0.0515   1.0000
  11.000   1.0121   0.07330   0.06805   0.0005   0.0524   1.0000
  11.250   0.8969   0.07014   0.06539   0.0037   0.0518   1.0000
  11.500   0.8733   0.07637   0.07174   0.0019   0.0522   1.0000
  11.750   0.8655   0.08290   0.07833   0.0008   0.0533   1.0000
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