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S4061-096-84 (s4061-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S4061-096-84 (s4061-il)
Reynolds number: 500,000
Max Cl/Cd: 105.72 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4061-il-500000-n5.txt
Download as CSV file: xf-s4061-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3644   0.10586   0.10359  -0.0280   1.0000   0.0116
  -9.750  -0.2708   0.08587   0.08357  -0.0348   0.8932   0.0082
  -9.500  -0.3532   0.09378   0.09154  -0.0325   0.9858   0.0082
  -9.000  -0.3250   0.08393   0.08164  -0.0437   0.9396   0.0079
  -8.750  -0.3178   0.08021   0.07786  -0.0466   0.9191   0.0076
  -8.250  -0.3239   0.07172   0.06928  -0.0504   0.8845   0.0074
  -7.750  -0.4226   0.02721   0.02354  -0.0827   0.8447   0.0065
  -7.500  -0.4049   0.02370   0.01951  -0.0836   0.8379   0.0065
  -7.250  -0.3831   0.02141   0.01683  -0.0839   0.8309   0.0067
  -7.000  -0.3597   0.01966   0.01475  -0.0840   0.8248   0.0069
  -6.750  -0.3349   0.01818   0.01298  -0.0841   0.8183   0.0071
  -6.500  -0.3096   0.01697   0.01150  -0.0840   0.8120   0.0073
  -6.250  -0.2835   0.01591   0.01022  -0.0840   0.8060   0.0075
  -6.000  -0.2571   0.01501   0.00911  -0.0839   0.7996   0.0078
  -5.750  -0.2305   0.01426   0.00818  -0.0838   0.7939   0.0080
  -5.500  -0.2033   0.01361   0.00739  -0.0837   0.7875   0.0082
  -5.250  -0.1764   0.01295   0.00659  -0.0836   0.7815   0.0085
  -5.000  -0.1493   0.01229   0.00585  -0.0836   0.7756   0.0092
  -4.750  -0.1218   0.01183   0.00531  -0.0836   0.7691   0.0096
  -4.500  -0.0943   0.01138   0.00476  -0.0835   0.7634   0.0101
  -4.250  -0.0664   0.01097   0.00427  -0.0835   0.7569   0.0105
  -4.000  -0.0385   0.01064   0.00382  -0.0834   0.7508   0.0111
  -3.750  -0.0104   0.01031   0.00342  -0.0834   0.7445   0.0117
  -3.500   0.0176   0.01001   0.00305  -0.0834   0.7380   0.0130
  -3.250   0.0457   0.00978   0.00275  -0.0834   0.7319   0.0149
  -3.000   0.0737   0.00948   0.00247  -0.0834   0.7252   0.0232
  -2.750   0.1016   0.00920   0.00225  -0.0834   0.7190   0.0450
  -2.500   0.1298   0.00900   0.00208  -0.0834   0.7122   0.0639
  -2.250   0.1578   0.00882   0.00194  -0.0835   0.7057   0.0875
  -2.000   0.1860   0.00862   0.00184  -0.0835   0.6989   0.1181
  -1.750   0.2140   0.00845   0.00174  -0.0836   0.6921   0.1524
  -1.500   0.2422   0.00833   0.00166  -0.0836   0.6855   0.1783
  -1.250   0.2704   0.00821   0.00159  -0.0837   0.6782   0.2074
  -1.000   0.2985   0.00809   0.00153  -0.0837   0.6715   0.2432
  -0.750   0.3266   0.00796   0.00149  -0.0838   0.6641   0.2850
  -0.250   0.3826   0.00772   0.00145  -0.0839   0.6495   0.3785
   0.000   0.4104   0.00759   0.00145  -0.0839   0.6422   0.4375
   0.250   0.4381   0.00744   0.00146  -0.0839   0.6341   0.5056
   0.500   0.4653   0.00725   0.00149  -0.0838   0.6262   0.5920
   0.750   0.4915   0.00702   0.00154  -0.0835   0.6174   0.6944
   1.000   0.5149   0.00672   0.00160  -0.0823   0.6080   0.8202
   1.250   0.5486   0.00650   0.00157  -0.0831   0.5968   1.0000
   1.500   0.5763   0.00661   0.00160  -0.0830   0.5855   1.0000
   1.750   0.6042   0.00670   0.00163  -0.0830   0.5743   1.0000
   2.000   0.6319   0.00681   0.00168  -0.0829   0.5631   1.0000
   2.250   0.6595   0.00693   0.00174  -0.0829   0.5514   1.0000
   2.500   0.6870   0.00706   0.00181  -0.0828   0.5391   1.0000
   2.750   0.7144   0.00720   0.00189  -0.0827   0.5262   1.0000
   3.000   0.7418   0.00735   0.00199  -0.0826   0.5129   1.0000
   3.250   0.7691   0.00750   0.00209  -0.0825   0.4988   1.0000
   3.500   0.7962   0.00767   0.00221  -0.0824   0.4841   1.0000
   3.750   0.8231   0.00786   0.00233  -0.0823   0.4683   1.0000
   4.000   0.8498   0.00807   0.00249  -0.0821   0.4507   1.0000
   4.250   0.8764   0.00829   0.00265  -0.0820   0.4320   1.0000
   4.500   0.9025   0.00855   0.00283  -0.0818   0.4116   1.0000
   4.750   0.9285   0.00884   0.00304  -0.0815   0.3902   1.0000
   5.000   0.9540   0.00915   0.00327  -0.0813   0.3667   1.0000
   5.250   0.9793   0.00949   0.00352  -0.0810   0.3418   1.0000
   5.500   1.0041   0.00988   0.00381  -0.0806   0.3154   1.0000
   5.750   1.0285   0.01031   0.00412  -0.0802   0.2889   1.0000
   6.000   1.0521   0.01080   0.00447  -0.0797   0.2586   1.0000
   6.250   1.0754   0.01132   0.00485  -0.0792   0.2298   1.0000
   6.500   1.0988   0.01180   0.00524  -0.0787   0.2060   1.0000
   6.750   1.1217   0.01233   0.00565  -0.0782   0.1803   1.0000
   7.000   1.1442   0.01286   0.00608  -0.0775   0.1573   1.0000
   7.250   1.1667   0.01338   0.00651  -0.0769   0.1380   1.0000
   7.500   1.1884   0.01395   0.00699  -0.0762   0.1178   1.0000
   7.750   1.2098   0.01452   0.00749  -0.0755   0.0997   1.0000
   8.000   1.2307   0.01512   0.00801  -0.0746   0.0844   1.0000
   8.250   1.2509   0.01573   0.00856  -0.0737   0.0694   1.0000
   8.500   1.2704   0.01638   0.00916  -0.0727   0.0559   1.0000
   8.750   1.2892   0.01705   0.00978  -0.0716   0.0446   1.0000
   9.000   1.3072   0.01774   0.01044  -0.0704   0.0354   1.0000
   9.250   1.3244   0.01845   0.01113  -0.0691   0.0276   1.0000
   9.500   1.3398   0.01922   0.01188  -0.0675   0.0203   1.0000
   9.750   1.3525   0.02002   0.01268  -0.0655   0.0154   1.0000
  10.000   1.3644   0.02078   0.01348  -0.0634   0.0132   1.0000
  10.250   1.3756   0.02162   0.01436  -0.0613   0.0119   1.0000
  10.500   1.3869   0.02249   0.01530  -0.0593   0.0111   1.0000
  10.750   1.3983   0.02339   0.01629  -0.0576   0.0105   1.0000
  11.000   1.4089   0.02440   0.01737  -0.0559   0.0100   1.0000
  11.250   1.4184   0.02553   0.01859  -0.0542   0.0095   1.0000
  11.500   1.4268   0.02679   0.01992  -0.0525   0.0091   1.0000
  11.750   1.4327   0.02830   0.02152  -0.0508   0.0086   1.0000
  12.000   1.4401   0.02976   0.02307  -0.0494   0.0085   1.0000
  12.250   1.4474   0.03127   0.02468  -0.0481   0.0083   1.0000
  12.500   1.4535   0.03293   0.02645  -0.0469   0.0081   1.0000
  12.750   1.4582   0.03480   0.02843  -0.0458   0.0080   1.0000
  13.000   1.4625   0.03676   0.03050  -0.0448   0.0078   1.0000
  13.250   1.4654   0.03894   0.03280  -0.0439   0.0077   1.0000
  13.500   1.4674   0.04129   0.03526  -0.0432   0.0075   1.0000
  13.750   1.4687   0.04379   0.03788  -0.0427   0.0074   1.0000
  14.000   1.4689   0.04652   0.04071  -0.0423   0.0073   1.0000
  14.250   1.4681   0.04944   0.04375  -0.0422   0.0071   1.0000
  14.500   1.4662   0.05262   0.04705  -0.0422   0.0070   1.0000
  14.750   1.4641   0.05597   0.05052  -0.0425   0.0069   1.0000
  15.000   1.4603   0.05967   0.05434  -0.0430   0.0068   1.0000
  15.250   1.4558   0.06365   0.05843  -0.0438   0.0067   1.0000
  15.500   1.4508   0.06784   0.06273  -0.0448   0.0065   1.0000
  15.750   1.4442   0.07242   0.06744  -0.0461   0.0065   1.0000
  16.000   1.4353   0.07751   0.07265  -0.0477   0.0064   1.0000
  16.250   1.4259   0.08286   0.07813  -0.0496   0.0063   1.0000
  16.500   1.4149   0.08864   0.08403  -0.0518   0.0062   1.0000
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