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S6061 9% (s6061-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S6061 9% (s6061-il)
Reynolds number: 500,000
Max Cl/Cd: 88.8 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s6061-il-500000.txt
Download as CSV file: xf-s6061-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4999   0.09110   0.08890  -0.0154   1.0000   0.0173
  -9.000  -0.4997   0.08657   0.08440  -0.0183   1.0000   0.0184
  -7.500  -0.5179   0.05377   0.05128  -0.0421   1.0000   0.0200
  -7.250  -0.5161   0.04968   0.04697  -0.0424   1.0000   0.0201
  -7.000  -0.5360   0.04080   0.03784  -0.0418   1.0000   0.0211
  -6.750  -0.5326   0.03884   0.03584  -0.0393   1.0000   0.0216
  -6.500  -0.5118   0.03624   0.03311  -0.0406   0.9968   0.0223
  -6.250  -0.4823   0.03310   0.02973  -0.0433   0.9921   0.0237
  -6.000  -0.4511   0.02991   0.02619  -0.0454   0.9873   0.0260
  -5.750  -0.4205   0.02014   0.01503  -0.0455   0.9828   0.0142
  -5.500  -0.3904   0.01740   0.01205  -0.0462   0.9768   0.0129
  -5.250  -0.3581   0.01516   0.00952  -0.0471   0.9719   0.0126
  -5.000  -0.3285   0.01379   0.00798  -0.0473   0.9646   0.0129
  -4.750  -0.2993   0.01282   0.00686  -0.0475   0.9575   0.0134
  -4.500  -0.2745   0.01197   0.00590  -0.0467   0.9476   0.0140
  -4.250  -0.2513   0.01097   0.00481  -0.0457   0.9381   0.0154
  -4.000  -0.2269   0.01058   0.00437  -0.0449   0.9291   0.0175
  -3.750  -0.2024   0.01014   0.00384  -0.0440   0.9191   0.0192
  -3.500  -0.1777   0.00958   0.00319  -0.0431   0.9098   0.0253
  -3.250  -0.1542   0.00883   0.00271  -0.0422   0.9009   0.0940
  -2.750  -0.1049   0.00784   0.00229  -0.0413   0.8817   0.2573
  -2.500  -0.0811   0.00721   0.00212  -0.0407   0.8727   0.3893
  -2.250  -0.0569   0.00667   0.00198  -0.0402   0.8625   0.5123
  -2.000  -0.0326   0.00628   0.00190  -0.0394   0.8528   0.6160
  -1.750  -0.0082   0.00603   0.00185  -0.0385   0.8434   0.6977
  -1.500   0.0169   0.00588   0.00182  -0.0376   0.8326   0.7545
  -1.250   0.0423   0.00579   0.00179  -0.0367   0.8218   0.7958
  -1.000   0.0678   0.00574   0.00176  -0.0359   0.8112   0.8287
  -0.750   0.0929   0.00571   0.00173  -0.0350   0.8007   0.8566
  -0.500   0.1180   0.00569   0.00170  -0.0340   0.7892   0.8803
  -0.250   0.1431   0.00568   0.00168  -0.0331   0.7775   0.9022
   0.000   0.1682   0.00568   0.00166  -0.0321   0.7658   0.9228
   0.250   0.1945   0.00569   0.00164  -0.0314   0.7539   0.9424
   0.500   0.2251   0.00572   0.00161  -0.0318   0.7415   0.9584
   0.750   0.2596   0.00576   0.00159  -0.0330   0.7286   0.9715
   1.000   0.2974   0.00580   0.00157  -0.0351   0.7152   0.9820
   1.250   0.3388   0.00585   0.00156  -0.0380   0.7011   0.9886
   1.500   0.3788   0.00590   0.00155  -0.0406   0.6860   0.9957
   1.750   0.4132   0.00594   0.00154  -0.0422   0.6700   1.0000
   2.000   0.4360   0.00601   0.00155  -0.0412   0.6542   1.0000
   2.250   0.4594   0.00610   0.00159  -0.0404   0.6380   1.0000
   2.500   0.4834   0.00620   0.00163  -0.0397   0.6215   1.0000
   2.750   0.5077   0.00632   0.00169  -0.0390   0.6045   1.0000
   3.000   0.5326   0.00644   0.00176  -0.0384   0.5860   1.0000
   3.250   0.5578   0.00658   0.00186  -0.0379   0.5658   1.0000
   3.500   0.5832   0.00674   0.00196  -0.0375   0.5439   1.0000
   3.750   0.6087   0.00692   0.00208  -0.0370   0.5208   1.0000
   4.000   0.6340   0.00714   0.00221  -0.0366   0.4917   1.0000
   4.250   0.6584   0.00747   0.00238  -0.0361   0.4426   1.0000
   4.500   0.6821   0.00792   0.00258  -0.0355   0.3850   1.0000
   4.750   0.7063   0.00836   0.00282  -0.0351   0.3376   1.0000
   5.000   0.7309   0.00877   0.00309  -0.0347   0.2979   1.0000
   5.250   0.7550   0.00927   0.00340  -0.0343   0.2525   1.0000
   5.500   0.7789   0.00979   0.00374  -0.0338   0.2083   1.0000
   5.750   0.8023   0.01039   0.00412  -0.0334   0.1603   1.0000
   6.000   0.8242   0.01118   0.00461  -0.0327   0.1037   1.0000
   6.250   0.8432   0.01242   0.00540  -0.0317   0.0337   1.0000
   6.500   0.8663   0.01311   0.00608  -0.0310   0.0237   1.0000
   6.750   0.8898   0.01372   0.00678  -0.0303   0.0214   1.0000
   7.000   0.9132   0.01432   0.00748  -0.0296   0.0201   1.0000
   7.250   0.9358   0.01500   0.00823  -0.0289   0.0189   1.0000
   7.500   0.9575   0.01574   0.00904  -0.0281   0.0175   1.0000
   7.750   0.9766   0.01681   0.01019  -0.0269   0.0163   1.0000
   8.000   0.9926   0.01829   0.01182  -0.0253   0.0156   1.0000
   8.250   1.0087   0.01993   0.01358  -0.0237   0.0152   1.0000
   8.500   1.0288   0.02098   0.01475  -0.0226   0.0149   1.0000
   8.750   1.0494   0.02193   0.01581  -0.0217   0.0143   1.0000
   9.000   1.0689   0.02302   0.01702  -0.0207   0.0136   1.0000
   9.250   1.0874   0.02437   0.01849  -0.0195   0.0130   1.0000
   9.500   1.1049   0.02590   0.02016  -0.0183   0.0125   1.0000
   9.750   1.1213   0.02762   0.02206  -0.0171   0.0121   1.0000
  10.000   1.1360   0.02943   0.02404  -0.0157   0.0117   1.0000
  10.250   1.1484   0.03146   0.02626  -0.0141   0.0114   1.0000
  10.500   1.1576   0.03378   0.02875  -0.0125   0.0110   1.0000
  10.750   1.1613   0.03689   0.03209  -0.0104   0.0107   1.0000
  11.000   1.1556   0.04054   0.03603  -0.0075   0.0105   1.0000
  11.250   1.1465   0.04349   0.03921  -0.0043   0.0104   1.0000
  11.500   1.1220   0.04828   0.04432  -0.0013   0.0103   1.0000
  11.750   1.1013   0.05255   0.04884   0.0002   0.0102   1.0000
  12.000   1.0836   0.05671   0.05321   0.0006   0.0102   1.0000
  12.250   1.0649   0.06140   0.05810  -0.0002   0.0102   1.0000
  12.500   1.0567   0.06506   0.06189  -0.0014   0.0102   1.0000
  12.750   1.0358   0.07111   0.06812  -0.0043   0.0102   1.0000
  13.000   1.0331   0.07468   0.07179  -0.0064   0.0103   1.0000
  13.250   1.0152   0.08140   0.07867  -0.0106   0.0103   1.0000
  13.500   1.0025   0.08778   0.08517  -0.0150   0.0104   1.0000
  13.750   0.9955   0.09362   0.09113  -0.0192   0.0106   1.0000
  14.000   0.9726   0.10369   0.10133  -0.0262   0.0105   1.0000
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