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S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il)
Reynolds number: 1,000,000
Max Cl/Cd: 75.59 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4095-il-1000000.txt
Download as CSV file: xf-s4095-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4095 (designed for the E-flite UMX ASK-21 scale
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6556   0.10402   0.10253   0.0267   1.0007   0.0121
  -8.500  -0.6604   0.09958   0.09810   0.0250   1.0007   0.0122
  -8.250  -0.6637   0.09470   0.09324   0.0217   1.0007   0.0123
  -8.000  -0.6604   0.08892   0.08745   0.0161   1.0007   0.0124
  -7.750  -0.6657   0.05105   0.04910  -0.0166   1.0007   0.0144
  -7.500  -0.6433   0.05056   0.04858  -0.0178   1.0007   0.0145
  -7.250  -0.6202   0.04850   0.04643  -0.0197   1.0007   0.0147
  -7.000  -0.5841   0.02263   0.01814  -0.0312   1.0007   0.0120
  -6.750  -0.5541   0.02100   0.01630  -0.0320   1.0007   0.0121
  -6.500  -0.5247   0.02020   0.01545  -0.0327   1.0007   0.0125
  -6.250  -0.4947   0.01914   0.01426  -0.0334   1.0007   0.0128
  -6.000  -0.4644   0.01787   0.01281  -0.0340   1.0007   0.0130
  -5.750  -0.4341   0.01691   0.01171  -0.0346   1.0007   0.0133
  -5.500  -0.4040   0.01617   0.01087  -0.0351   1.0007   0.0137
  -5.250  -0.3738   0.01564   0.01025  -0.0356   1.0007   0.0141
  -5.000  -0.3437   0.01489   0.00943  -0.0361   1.0007   0.0144
  -4.750  -0.3136   0.01412   0.00865  -0.0368   1.0007   0.0148
  -4.500  -0.2834   0.01364   0.00816  -0.0374   1.0007   0.0151
  -4.250  -0.2531   0.01323   0.00774  -0.0379   1.0007   0.0155
  -4.000  -0.2228   0.01286   0.00736  -0.0385   1.0007   0.0160
  -3.750  -0.1924   0.01255   0.00703  -0.0390   1.0007   0.0165
  -3.500  -0.1625   0.01264   0.00707  -0.0393   0.9473   0.0174
  -3.250  -0.1390   0.01265   0.00692  -0.0379   0.8917   0.0182
  -3.000  -0.1114   0.01259   0.00669  -0.0377   0.8508   0.0194
  -2.750  -0.0824   0.01248   0.00644  -0.0378   0.8171   0.0209
  -2.250  -0.0232   0.01219   0.00606  -0.0385   0.7595   0.0487
  -2.000   0.0067   0.01202   0.00596  -0.0390   0.7346   0.0875
  -1.750   0.0366   0.01188   0.00587  -0.0395   0.7117   0.1274
  -1.500   0.0665   0.01173   0.00582  -0.0401   0.6911   0.1772
  -1.250   0.0965   0.01158   0.00579  -0.0407   0.6716   0.2352
  -1.000   0.1266   0.01141   0.00578  -0.0414   0.6534   0.3129
  -0.750   0.1567   0.01117   0.00581  -0.0421   0.6358   0.4240
  -0.500   0.1868   0.01078   0.00594  -0.0430   0.6195   0.6062
  -0.250   0.2148   0.01035   0.00616  -0.0431   0.6045   0.8225
   0.000   0.2369   0.00963   0.00572  -0.0413   0.5899   0.9993
   0.250   0.2669   0.00970   0.00569  -0.0417   0.5745   0.9993
   0.500   0.2969   0.00976   0.00567  -0.0422   0.5601   0.9993
   0.750   0.3268   0.00984   0.00565  -0.0427   0.5452   0.9993
   1.000   0.3567   0.00992   0.00563  -0.0431   0.5292   0.9993
   1.250   0.3866   0.00999   0.00563  -0.0436   0.5139   0.9993
   1.500   0.4165   0.01007   0.00564  -0.0440   0.4982   0.9993
   1.750   0.4463   0.01016   0.00564  -0.0445   0.4814   0.9993
   2.000   0.4761   0.01026   0.00566  -0.0450   0.4638   0.9993
   2.250   0.5058   0.01037   0.00568  -0.0454   0.4457   0.9993
   2.500   0.5355   0.01049   0.00571  -0.0459   0.4275   0.9993
   2.750   0.5652   0.01062   0.00575  -0.0464   0.4092   0.9993
   3.000   0.5948   0.01074   0.00580  -0.0468   0.3916   0.9993
   3.250   0.6244   0.01088   0.00587  -0.0473   0.3742   0.9993
   3.500   0.6540   0.01102   0.00594  -0.0478   0.3568   0.9993
   3.750   0.6835   0.01117   0.00602  -0.0482   0.3398   0.9993
   4.000   0.7130   0.01134   0.00611  -0.0487   0.3227   0.9993
   4.250   0.7424   0.01151   0.00622  -0.0492   0.3059   0.9993
   4.500   0.7718   0.01169   0.00634  -0.0496   0.2894   0.9993
   4.750   0.8011   0.01188   0.00646  -0.0501   0.2734   0.9993
   5.000   0.8304   0.01208   0.00661  -0.0506   0.2577   0.9993
   5.250   0.8596   0.01229   0.00676  -0.0510   0.2423   0.9993
   5.500   0.8888   0.01251   0.00692  -0.0515   0.2273   0.9993
   5.750   0.9179   0.01275   0.00710  -0.0520   0.2124   0.9993
   6.000   0.9469   0.01299   0.00729  -0.0524   0.1979   0.9993
   6.250   0.9759   0.01326   0.00750  -0.0529   0.1828   0.9993
   6.500   1.0047   0.01353   0.00772  -0.0533   0.1687   0.9993
   6.750   1.0335   0.01381   0.00795  -0.0538   0.1557   0.9993
   7.000   1.0622   0.01414   0.00821  -0.0542   0.1413   0.9993
   7.250   1.0907   0.01448   0.00849  -0.0547   0.1275   0.9993
   7.500   1.1192   0.01481   0.00877  -0.0551   0.1150   0.9993
   7.750   1.1475   0.01518   0.00909  -0.0555   0.1030   0.9993
   8.000   1.1757   0.01556   0.00942  -0.0559   0.0917   0.9993
   8.250   1.2037   0.01598   0.00978  -0.0563   0.0803   0.9993
   8.500   1.2317   0.01637   0.01014  -0.0567   0.0712   0.9993
   8.750   1.2594   0.01682   0.01055  -0.0571   0.0623   0.9993
   9.000   1.2871   0.01727   0.01096  -0.0575   0.0536   0.9993
   9.250   1.3145   0.01774   0.01141  -0.0578   0.0459   0.9993
   9.500   1.3417   0.01825   0.01189  -0.0581   0.0387   0.9993
   9.750   1.3686   0.01882   0.01243  -0.0584   0.0309   0.9993
  10.000   1.3946   0.01961   0.01314  -0.0587   0.0196   0.9993
  10.500   1.4450   0.02150   0.01501  -0.0589   0.0073   0.9993
  10.750   1.4705   0.02224   0.01582  -0.0590   0.0066   0.9993
  11.000   1.4956   0.02299   0.01665  -0.0591   0.0061   0.9993
  11.250   1.5195   0.02394   0.01768  -0.0590   0.0056   0.9993
  11.500   1.5424   0.02500   0.01884  -0.0588   0.0052   0.9993
  11.750   1.5659   0.02582   0.01975  -0.0587   0.0050   0.9993
  12.000   1.5883   0.02676   0.02078  -0.0584   0.0049   0.9993
  12.250   1.6096   0.02780   0.02192  -0.0581   0.0047   0.9993
  12.500   1.6296   0.02892   0.02314  -0.0575   0.0046   0.9993
  12.750   1.6480   0.03013   0.02446  -0.0569   0.0045   0.9993
  13.000   1.6646   0.03145   0.02588  -0.0560   0.0044   0.9993
  13.250   1.6788   0.03291   0.02746  -0.0548   0.0043   0.9993
  13.500   1.6897   0.03456   0.02922  -0.0533   0.0042   0.9993
  13.750   1.6959   0.03645   0.03124  -0.0513   0.0042   0.9993
  14.000   1.6938   0.03875   0.03367  -0.0484   0.0041   0.9993
  14.250   1.6762   0.04202   0.03710  -0.0443   0.0041   0.9993
  14.500   1.6637   0.04622   0.04145  -0.0434   0.0041   0.9993
  14.750   1.6521   0.05128   0.04667  -0.0442   0.0040   0.9993
  15.000   1.6392   0.05709   0.05265  -0.0461   0.0040   0.9993
  15.250   1.6233   0.06363   0.05935  -0.0485   0.0040   0.9993
  15.500   1.6049   0.07073   0.06661  -0.0513   0.0040   0.9993
  15.750   1.5846   0.07821   0.07425  -0.0542   0.0040   0.9993
  16.000   1.5618   0.08615   0.08233  -0.0573   0.0040   0.9993
  16.250   1.5382   0.09436   0.09069  -0.0605   0.0040   0.9993
  16.500   1.5141   0.10269   0.09916  -0.0639   0.0040   0.9993
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