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S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il)
Reynolds number: 100,000
Max Cl/Cd: 47.1 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4094-il-100000-n5.txt
Download as CSV file: xf-s4094-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4094 (root airfoil designed for and used on the
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5833   0.10021   0.09545   0.0044   1.0004   0.0338
  -8.500  -0.5802   0.09655   0.09182   0.0039   1.0004   0.0332
  -8.250  -0.5812   0.09225   0.08756   0.0020   1.0004   0.0326
  -8.000  -0.5799   0.08708   0.08242  -0.0020   1.0004   0.0319
  -7.750  -0.5763   0.08096   0.07628  -0.0074   1.0004   0.0312
  -7.500  -0.5703   0.07378   0.06904  -0.0139   1.0004   0.0304
  -7.250  -0.5614   0.06515   0.06023  -0.0210   1.0004   0.0294
  -7.000  -0.5493   0.05474   0.04938  -0.0281   1.0004   0.0283
  -6.750  -0.5308   0.04504   0.03888  -0.0334   1.0004   0.0275
  -6.500  -0.5065   0.03967   0.03288  -0.0358   1.0004   0.0275
  -6.250  -0.4804   0.03701   0.02992  -0.0371   1.0004   0.0285
  -6.000  -0.4529   0.03441   0.02693  -0.0383   1.0004   0.0300
  -5.750  -0.4238   0.03149   0.02349  -0.0393   1.0004   0.0311
  -5.500  -0.3942   0.02879   0.02032  -0.0401   1.0004   0.0315
  -5.250  -0.3644   0.02660   0.01773  -0.0407   1.0004   0.0321
  -5.000  -0.3348   0.02479   0.01562  -0.0411   1.0004   0.0328
  -4.750  -0.3054   0.02329   0.01387  -0.0414   1.0004   0.0338
  -4.500  -0.2765   0.02186   0.01237  -0.0417   1.0004   0.0350
  -4.250  -0.2476   0.02086   0.01137  -0.0422   1.0004   0.0375
  -4.000  -0.2186   0.02005   0.01050  -0.0425   1.0004   0.0417
  -3.750  -0.1894   0.01912   0.00952  -0.0429   1.0004   0.0457
  -3.500  -0.1602   0.01831   0.00869  -0.0433   1.0004   0.0520
  -3.250  -0.1308   0.01749   0.00791  -0.0438   1.0004   0.0664
  -3.000  -0.1020   0.01675   0.00739  -0.0443   1.0004   0.1024
  -2.750  -0.0739   0.01609   0.00712  -0.0450   1.0004   0.1701
  -2.500  -0.0431   0.01547   0.00697  -0.0463   0.9895   0.2688
  -2.250  -0.0055   0.01494   0.00683  -0.0487   0.9565   0.3837
  -2.000   0.0290   0.01443   0.00675  -0.0500   0.9254   0.5199
  -1.750   0.0552   0.01389   0.00673  -0.0488   0.8955   0.6840
  -1.500   0.0745   0.01323   0.00647  -0.0451   0.8671   0.8954
  -1.250   0.1068   0.01298   0.00599  -0.0456   0.8397   0.9996
  -1.000   0.1343   0.01312   0.00586  -0.0452   0.8164   0.9996
  -0.750   0.1617   0.01327   0.00576  -0.0448   0.7956   0.9996
  -0.500   0.1895   0.01342   0.00569  -0.0445   0.7756   0.9996
  -0.250   0.2175   0.01357   0.00563  -0.0444   0.7568   0.9996
   0.000   0.2456   0.01373   0.00560  -0.0442   0.7392   0.9996
   0.250   0.2737   0.01389   0.00559  -0.0441   0.7222   0.9996
   0.500   0.3019   0.01406   0.00559  -0.0440   0.7058   0.9996
   0.750   0.3303   0.01423   0.00561  -0.0439   0.6896   0.9996
   1.000   0.3587   0.01440   0.00565  -0.0439   0.6735   0.9996
   1.250   0.3872   0.01458   0.00571  -0.0440   0.6576   0.9996
   1.500   0.4158   0.01477   0.00578  -0.0440   0.6418   0.9996
   1.750   0.4443   0.01495   0.00587  -0.0441   0.6261   0.9996
   2.000   0.4729   0.01515   0.00598  -0.0441   0.6102   0.9996
   2.250   0.5015   0.01534   0.00610  -0.0442   0.5942   0.9996
   2.500   0.5300   0.01555   0.00622  -0.0443   0.5780   0.9996
   2.750   0.5585   0.01576   0.00638  -0.0444   0.5616   0.9996
   3.000   0.5870   0.01597   0.00653  -0.0445   0.5450   0.9996
   3.250   0.6154   0.01620   0.00669  -0.0445   0.5283   0.9996
   3.500   0.6439   0.01642   0.00691  -0.0447   0.5102   0.9996
   3.750   0.6724   0.01666   0.00711  -0.0448   0.4918   0.9996
   4.000   0.7007   0.01691   0.00732  -0.0449   0.4732   0.9996
   4.250   0.7288   0.01719   0.00754  -0.0450   0.4547   0.9996
   4.500   0.7571   0.01747   0.00784  -0.0452   0.4349   0.9996
   4.750   0.7851   0.01779   0.00812  -0.0453   0.4154   0.9996
   5.000   0.8129   0.01814   0.00842  -0.0454   0.3964   0.9996
   5.250   0.8408   0.01850   0.00881  -0.0456   0.3767   0.9996
   5.500   0.8684   0.01890   0.00919  -0.0457   0.3573   0.9996
   5.750   0.8958   0.01934   0.00959  -0.0458   0.3389   0.9996
   6.000   0.9232   0.01978   0.01005  -0.0460   0.3197   0.9996
   6.250   0.9504   0.02025   0.01056  -0.0461   0.3013   0.9996
   6.500   0.9773   0.02077   0.01107  -0.0462   0.2832   0.9996
   6.750   1.0039   0.02132   0.01162  -0.0463   0.2660   0.9996
   7.000   1.0305   0.02188   0.01222  -0.0464   0.2485   0.9996
   7.250   1.0568   0.02248   0.01289  -0.0465   0.2319   0.9996
   7.500   1.0826   0.02312   0.01358  -0.0465   0.2158   0.9996
   7.750   1.1081   0.02380   0.01431  -0.0465   0.2006   0.9996
   8.000   1.1332   0.02453   0.01509  -0.0465   0.1857   0.9996
   8.250   1.1578   0.02530   0.01592  -0.0464   0.1716   0.9996
   8.500   1.1820   0.02612   0.01684  -0.0462   0.1582   0.9996
   8.750   1.2055   0.02699   0.01779  -0.0460   0.1455   0.9996
   9.000   1.2284   0.02792   0.01881  -0.0458   0.1340   0.9996
   9.250   1.2504   0.02893   0.01989  -0.0454   0.1233   0.9996
   9.500   1.2710   0.03004   0.02106  -0.0450   0.1138   0.9996
   9.750   1.2920   0.03111   0.02234  -0.0444   0.1042   0.9996
  10.000   1.3111   0.03235   0.02370  -0.0438   0.0963   0.9996
  10.250   1.3284   0.03367   0.02511  -0.0429   0.0891   0.9996
  10.500   1.3455   0.03498   0.02662  -0.0421   0.0809   0.9996
  10.750   1.3598   0.03637   0.02812  -0.0411   0.0725   0.9996
  11.000   1.3713   0.03786   0.02965  -0.0400   0.0638   0.9996
  11.250   1.3834   0.03929   0.03132  -0.0389   0.0547   0.9996
  11.500   1.3903   0.04112   0.03331  -0.0373   0.0486   0.9996
  11.750   1.3918   0.04325   0.03557  -0.0354   0.0437   0.9996
  12.000   1.3873   0.04567   0.03816  -0.0329   0.0398   0.9996
  12.250   1.3816   0.04863   0.04130  -0.0315   0.0362   0.9996
  12.500   1.3715   0.05253   0.04531  -0.0312   0.0339   0.9996
  12.750   1.3637   0.05666   0.04966  -0.0315   0.0314   0.9996
  13.000   1.3538   0.06137   0.05459  -0.0325   0.0295   0.9996
  13.250   1.3418   0.06667   0.06007  -0.0342   0.0281   0.9996
  13.500   1.3277   0.07254   0.06610  -0.0365   0.0271   0.9996
  13.750   1.3117   0.07889   0.07259  -0.0391   0.0265   0.9996
  14.000   1.2946   0.08561   0.07945  -0.0419   0.0260   0.9996
  14.250   1.2784   0.09234   0.08633  -0.0447   0.0255   0.9996
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