Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S4061-096-84 (s4061-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S4061-096-84 (s4061-il)
Reynolds number: 500,000
Max Cl/Cd: 116.6 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4061-il-500000.txt
Download as CSV file: xf-s4061-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4061-096-84                                    
  
 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  -0.3379   0.09472   0.09254  -0.0357   1.0000   0.0203
  -9.000  -0.3346   0.09096   0.08882  -0.0381   1.0000   0.0204
  -8.750  -0.3385   0.08583   0.08375  -0.0405   1.0000   0.0207
  -8.500  -0.3323   0.08373   0.08167  -0.0402   1.0000   0.0212
  -8.250  -0.3172   0.08144   0.07940  -0.0421   0.9872   0.0218
  -8.000  -0.2955   0.07712   0.07507  -0.0485   0.9723   0.0226
  -7.750  -0.2771   0.07228   0.07020  -0.0555   0.9545   0.0236
  -7.500  -0.2742   0.06838   0.06625  -0.0589   0.9314   0.0242
  -7.000  -0.2704   0.05376   0.05141  -0.0758   0.8953   0.0261
  -6.750  -0.2779   0.04280   0.04005  -0.0833   0.8830   0.0267
  -6.500  -0.2629   0.04046   0.03769  -0.0838   0.8747   0.0273
  -6.250  -0.2458   0.03811   0.03523  -0.0847   0.8673   0.0279
  -6.000  -0.2402   0.02217   0.01747  -0.0876   0.8586   0.0160
  -5.750  -0.2187   0.01849   0.01340  -0.0875   0.8524   0.0153
  -5.500  -0.1934   0.01656   0.01110  -0.0873   0.8457   0.0153
  -5.250  -0.1675   0.01527   0.00951  -0.0868   0.8401   0.0155
  -5.000  -0.1404   0.01432   0.00838  -0.0867   0.8333   0.0158
  -4.750  -0.1141   0.01321   0.00708  -0.0863   0.8274   0.0162
  -4.500  -0.0877   0.01220   0.00599  -0.0861   0.8212   0.0169
  -4.250  -0.0604   0.01175   0.00550  -0.0860   0.8147   0.0183
  -4.000  -0.0331   0.01126   0.00491  -0.0858   0.8091   0.0194
  -3.750  -0.0052   0.01078   0.00435  -0.0857   0.8022   0.0203
  -3.500   0.0222   0.01019   0.00368  -0.0855   0.7964   0.0227
  -3.250   0.0504   0.00983   0.00326  -0.0854   0.7898   0.0269
  -3.000   0.0780   0.00924   0.00281  -0.0853   0.7835   0.0618
  -2.750   0.1058   0.00900   0.00264  -0.0853   0.7773   0.0929
  -2.500   0.1339   0.00879   0.00248  -0.0853   0.7706   0.1196
  -2.250   0.1616   0.00860   0.00235  -0.0853   0.7647   0.1529
  -2.000   0.1897   0.00838   0.00226  -0.0854   0.7576   0.1953
  -1.750   0.2175   0.00819   0.00215  -0.0853   0.7514   0.2399
  -1.500   0.2456   0.00800   0.00208  -0.0854   0.7445   0.2862
  -1.250   0.2733   0.00779   0.00201  -0.0854   0.7379   0.3447
  -1.000   0.3010   0.00756   0.00197  -0.0854   0.7312   0.4175
  -0.750   0.3283   0.00728   0.00195  -0.0853   0.7242   0.5126
  -0.500   0.3548   0.00698   0.00195  -0.0851   0.7176   0.6250
  -0.250   0.3788   0.00655   0.00198  -0.0840   0.7103   0.7714
   0.000   0.4115   0.00614   0.00191  -0.0843   0.7038   0.9863
   0.250   0.4413   0.00617   0.00187  -0.0847   0.6959   1.0000
   0.500   0.4692   0.00624   0.00185  -0.0846   0.6887   1.0000
   0.750   0.4972   0.00629   0.00184  -0.0846   0.6804   1.0000
   1.000   0.5252   0.00636   0.00184  -0.0845   0.6722   1.0000
   1.250   0.5530   0.00643   0.00183  -0.0844   0.6630   1.0000
   1.500   0.5810   0.00649   0.00185  -0.0843   0.6534   1.0000
   1.750   0.6087   0.00658   0.00187  -0.0843   0.6447   1.0000
   2.000   0.6366   0.00666   0.00190  -0.0842   0.6349   1.0000
   2.250   0.6644   0.00674   0.00196  -0.0841   0.6252   1.0000
   2.500   0.6920   0.00685   0.00200  -0.0840   0.6156   1.0000
   2.750   0.7197   0.00694   0.00206  -0.0840   0.6048   1.0000
   3.000   0.7474   0.00704   0.00214  -0.0839   0.5942   1.0000
   3.250   0.7749   0.00716   0.00223  -0.0838   0.5834   1.0000
   3.500   0.8022   0.00729   0.00231  -0.0837   0.5720   1.0000
   3.750   0.8296   0.00741   0.00241  -0.0836   0.5595   1.0000
   4.000   0.8568   0.00755   0.00252  -0.0835   0.5463   1.0000
   4.250   0.8839   0.00770   0.00266  -0.0833   0.5325   1.0000
   4.500   0.9107   0.00787   0.00279  -0.0832   0.5176   1.0000
   4.750   0.9373   0.00805   0.00294  -0.0830   0.5015   1.0000
   5.250   0.9899   0.00849   0.00331  -0.0825   0.4653   1.0000
   5.500   1.0157   0.00875   0.00351  -0.0822   0.4438   1.0000
   5.750   1.0410   0.00905   0.00375  -0.0819   0.4202   1.0000
   6.000   1.0655   0.00943   0.00402  -0.0814   0.3909   1.0000
   6.250   1.0893   0.00986   0.00434  -0.0809   0.3582   1.0000
   6.500   1.1127   0.01034   0.00468  -0.0804   0.3263   1.0000
   6.750   1.1353   0.01089   0.00509  -0.0797   0.2933   1.0000
   7.000   1.1577   0.01145   0.00552  -0.0791   0.2616   1.0000
   7.250   1.1794   0.01206   0.00598  -0.0784   0.2303   1.0000
   7.500   1.2007   0.01269   0.00646  -0.0776   0.2010   1.0000
   7.750   1.2220   0.01328   0.00696  -0.0768   0.1778   1.0000
   8.000   1.2430   0.01388   0.00747  -0.0760   0.1547   1.0000
   8.250   1.2634   0.01451   0.00800  -0.0751   0.1332   1.0000
   8.500   1.2829   0.01519   0.00858  -0.0741   0.1129   1.0000
   8.750   1.3020   0.01587   0.00919  -0.0730   0.0947   1.0000
   9.000   1.3198   0.01660   0.00984  -0.0718   0.0775   1.0000
   9.250   1.3361   0.01741   0.01057  -0.0704   0.0619   1.0000
   9.500   1.3513   0.01825   0.01134  -0.0688   0.0470   1.0000
   9.750   1.3612   0.01937   0.01236  -0.0664   0.0313   1.0000
  10.000   1.3682   0.02045   0.01343  -0.0635   0.0233   1.0000
  10.500   1.3843   0.02255   0.01563  -0.0586   0.0183   1.0000
  10.750   1.3935   0.02361   0.01675  -0.0566   0.0169   1.0000
  11.000   1.3992   0.02497   0.01816  -0.0544   0.0158   1.0000
  11.250   1.4008   0.02672   0.02001  -0.0521   0.0151   1.0000
  11.500   1.4081   0.02811   0.02151  -0.0504   0.0146   1.0000
  11.750   1.4139   0.02969   0.02319  -0.0488   0.0142   1.0000
  12.000   1.4189   0.03140   0.02502  -0.0473   0.0137   1.0000
  12.250   1.4229   0.03327   0.02699  -0.0459   0.0134   1.0000
  12.500   1.4264   0.03527   0.02909  -0.0448   0.0130   1.0000
  12.750   1.4285   0.03747   0.03138  -0.0437   0.0127   1.0000
  13.000   1.4294   0.03988   0.03389  -0.0428   0.0124   1.0000
  13.250   1.4289   0.04255   0.03665  -0.0420   0.0122   1.0000
  13.500   1.4259   0.04556   0.03975  -0.0413   0.0119   1.0000
  13.750   1.4208   0.04894   0.04325  -0.0408   0.0116   1.0000
  14.000   1.4137   0.05268   0.04711  -0.0402   0.0114   1.0000
  14.250   1.4169   0.05533   0.04990  -0.0403   0.0112   1.0000
  14.500   1.4172   0.05841   0.05311  -0.0404   0.0111   1.0000
  14.750   1.4172   0.06166   0.05649  -0.0407   0.0109   1.0000
  15.000   1.4161   0.06515   0.06012  -0.0411   0.0107   1.0000
  15.250   1.4143   0.06883   0.06394  -0.0418   0.0106   1.0000
  15.500   1.4114   0.07277   0.06802  -0.0425   0.0105   1.0000
  15.750   1.4080   0.07691   0.07230  -0.0436   0.0103   1.0000
  16.000   1.4039   0.08131   0.07684  -0.0448   0.0102   1.0000
  16.250   1.3984   0.08601   0.08169  -0.0463   0.0101   1.0000
  16.500   1.3928   0.09091   0.08673  -0.0481   0.0100   1.0000
  16.750   1.3858   0.09614   0.09212  -0.0502   0.0099   1.0000
  17.000   1.3781   0.10167   0.09779  -0.0526   0.0098   1.0000
  17.250   1.3697   0.10746   0.10374  -0.0553   0.0097   1.0000
  17.500   1.3597   0.11375   0.11019  -0.0584   0.0097   1.0000
  17.750   1.3495   0.12022   0.11682  -0.0618   0.0096   1.0000
  18.000   1.3380   0.12716   0.12391  -0.0657   0.0096   1.0000
  18.250   1.3258   0.13446   0.13138  -0.0699   0.0096   1.0000
  18.500   1.3125   0.14223   0.13931  -0.0747   0.0096   1.0000
  18.750   1.2976   0.15070   0.14796  -0.0800   0.0096   1.0000
  19.000   1.2799   0.16024   0.15768  -0.0863   0.0097   1.0000
  19.250   1.2569   0.17173   0.16937  -0.0940   0.0098   1.0000
<< Back to S4061-096-84 (s4061-il)

Polar data table (+)

Polar graphs


<< Back to S4061-096-84 (s4061-il)