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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=9


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: 44.88 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4094-il-100000.txt
Download as CSV file: xf-s4094-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4285   0.09997   0.09555   0.0006   1.0004   0.1091
  -8.250  -0.4471   0.09613   0.09178  -0.0035   1.0004   0.1127
  -8.000  -0.4786   0.09216   0.08791  -0.0096   1.0004   0.1135
  -7.750  -0.4442   0.08695   0.08268  -0.0044   1.0004   0.1167
  -7.500  -0.4374   0.08330   0.07905  -0.0039   1.0004   0.1206
  -7.250  -0.5528   0.08639   0.08189  -0.0083   1.0004   0.1153
  -7.000  -0.5385   0.08340   0.07892  -0.0049   1.0004   0.1184
  -6.750  -0.5303   0.07650   0.07176  -0.0196   1.0004   0.1289
  -6.500  -0.5151   0.07313   0.06853  -0.0154   1.0004   0.1312
  -6.250  -0.4984   0.06963   0.06501  -0.0163   1.0004   0.1375
  -6.000  -0.4751   0.06475   0.05954  -0.0282   1.0004   0.1574
  -5.750  -0.4593   0.05996   0.05505  -0.0256   1.0004   0.1599
  -5.500  -0.4376   0.05641   0.05141  -0.0276   1.0004   0.1747
  -5.250  -0.3803   0.03866   0.03188  -0.0403   1.0004   0.0819
  -5.000  -0.3441   0.03280   0.02494  -0.0422   1.0004   0.0706
  -4.750  -0.3130   0.02944   0.02117  -0.0431   1.0004   0.0691
  -4.500  -0.2814   0.02675   0.01803  -0.0437   1.0004   0.0688
  -4.250  -0.2501   0.02467   0.01555  -0.0440   1.0004   0.0702
  -4.000  -0.2201   0.02277   0.01349  -0.0444   1.0004   0.0747
  -3.750  -0.1905   0.02136   0.01204  -0.0446   1.0004   0.0802
  -3.500  -0.1608   0.01986   0.01045  -0.0446   1.0004   0.0872
  -3.250  -0.1319   0.01852   0.00930  -0.0448   1.0004   0.1040
  -3.000  -0.1030   0.01701   0.00817  -0.0452   1.0004   0.1611
  -2.750  -0.0752   0.01577   0.00763  -0.0458   1.0004   0.2767
  -2.500  -0.0505   0.01445   0.00740  -0.0457   1.0004   0.4822
  -2.250  -0.0337   0.01340   0.00743  -0.0425   1.0004   0.7373
  -2.000  -0.0171   0.01302   0.00739  -0.0398   1.0004   0.9996
  -1.750   0.0046   0.01364   0.00775  -0.0399   1.0004   0.9996
  -1.250   0.0942   0.01386   0.00742  -0.0486   0.9821   0.9996
  -1.000   0.1458   0.01368   0.00700  -0.0537   0.9641   0.9996
  -0.750   0.1925   0.01360   0.00673  -0.0576   0.9442   0.9996
  -0.500   0.2291   0.01368   0.00663  -0.0591   0.9196   0.9996
  -0.250   0.2585   0.01388   0.00666  -0.0588   0.8957   0.9996
   0.000   0.2841   0.01414   0.00676  -0.0578   0.8719   0.9996
   0.250   0.3088   0.01440   0.00687  -0.0565   0.8505   0.9996
   0.500   0.3338   0.01466   0.00700  -0.0555   0.8293   0.9996
   0.750   0.3589   0.01493   0.00712  -0.0543   0.8101   0.9996
   1.000   0.3845   0.01519   0.00725  -0.0534   0.7915   0.9996
   1.250   0.4110   0.01545   0.00740  -0.0528   0.7721   0.9996
   1.500   0.4375   0.01570   0.00754  -0.0521   0.7536   0.9996
   1.750   0.4640   0.01596   0.00768  -0.0515   0.7357   0.9996
   2.000   0.4906   0.01622   0.00783  -0.0508   0.7183   0.9996
   2.250   0.5180   0.01647   0.00801  -0.0504   0.6997   0.9996
   2.500   0.5454   0.01673   0.00820  -0.0501   0.6808   0.9996
   2.750   0.5727   0.01698   0.00839  -0.0497   0.6624   0.9996
   3.000   0.6000   0.01724   0.00855  -0.0492   0.6445   0.9996
   3.250   0.6274   0.01750   0.00874  -0.0489   0.6260   0.9996
   3.500   0.6552   0.01776   0.00899  -0.0487   0.6059   0.9996
   3.750   0.6828   0.01801   0.00918  -0.0484   0.5867   0.9996
   4.000   0.7102   0.01828   0.00936  -0.0481   0.5681   0.9996
   4.250   0.7381   0.01855   0.00963  -0.0480   0.5470   0.9996
   4.500   0.7657   0.01882   0.00987  -0.0477   0.5267   0.9996
   4.750   0.7932   0.01910   0.01007  -0.0475   0.5070   0.9996
   5.000   0.8210   0.01939   0.01038  -0.0474   0.4848   0.9996
   5.250   0.8483   0.01969   0.01062  -0.0472   0.4645   0.9996
   5.500   0.8759   0.02005   0.01100  -0.0471   0.4421   0.9996
   5.750   0.9031   0.02044   0.01130  -0.0469   0.4210   0.9996
   6.000   0.9304   0.02089   0.01177  -0.0469   0.3988   0.9996
   6.250   0.9573   0.02138   0.01221  -0.0468   0.3776   0.9996
   6.500   0.9842   0.02194   0.01277  -0.0467   0.3560   0.9996
   6.750   1.0108   0.02252   0.01332  -0.0466   0.3348   0.9996
   7.000   1.0371   0.02318   0.01396  -0.0465   0.3147   0.9996
   7.250   1.0633   0.02386   0.01469  -0.0464   0.2939   0.9996
   7.500   1.0891   0.02460   0.01537  -0.0463   0.2749   0.9996
   7.750   1.1146   0.02542   0.01621  -0.0462   0.2560   0.9996
   8.000   1.1397   0.02627   0.01716  -0.0460   0.2374   0.9996
   8.250   1.1644   0.02716   0.01806  -0.0458   0.2199   0.9996
   8.500   1.1887   0.02815   0.01904  -0.0456   0.2037   0.9996
   8.750   1.2126   0.02921   0.02009  -0.0453   0.1883   0.9996
   9.000   1.2360   0.03039   0.02132  -0.0450   0.1739   0.9996
   9.250   1.2587   0.03161   0.02262  -0.0446   0.1603   0.9996
   9.500   1.2809   0.03296   0.02412  -0.0440   0.1479   0.9996
   9.750   1.3020   0.03443   0.02578  -0.0434   0.1362   0.9996
  10.000   1.3224   0.03614   0.02764  -0.0428   0.1259   0.9996
  10.250   1.3426   0.03784   0.02939  -0.0421   0.1163   0.9996
  10.500   1.3613   0.03931   0.03077  -0.0415   0.1056   0.9996
  10.750   1.3737   0.04019   0.03196  -0.0402   0.0947   0.9996
  11.000   1.3838   0.04167   0.03371  -0.0387   0.0845   0.9996
  11.250   1.3925   0.04371   0.03593  -0.0370   0.0755   0.9996
  11.500   1.4000   0.04591   0.03809  -0.0353   0.0673   0.9996
  11.750   1.4002   0.04804   0.04052  -0.0328   0.0602   0.9996
  12.000   1.3989   0.05105   0.04367  -0.0304   0.0550   0.9996
  12.250   1.3914   0.05389   0.04682  -0.0274   0.0514   0.9996
  12.500   1.3883   0.05659   0.04957  -0.0252   0.0486   0.9996
  12.750   1.3841   0.06079   0.05388  -0.0235   0.0465   0.9996
  13.000   1.3682   0.06504   0.05851  -0.0223   0.0457   0.9996
  13.250   1.3510   0.06997   0.06379  -0.0222   0.0451   0.9996
  13.500   1.3322   0.07556   0.06968  -0.0232   0.0446   0.9996
  13.750   1.3112   0.08185   0.07627  -0.0252   0.0445   0.9996
  14.000   1.2880   0.08891   0.08360  -0.0283   0.0445   0.9996
  14.250   1.2626   0.09681   0.09174  -0.0323   0.0448   0.9996
  14.500   1.2359   0.10549   0.10061  -0.0373   0.0453   0.9996
  14.750   1.2084   0.11498   0.11028  -0.0431   0.0458   0.9996
  15.000   1.1811   0.12517   0.12060  -0.0495   0.0465   0.9996
  15.250   1.0256   0.18509   0.18046  -0.0870   0.0700   0.9996
  15.500   1.0270   0.19149   0.18686  -0.0897   0.0695   0.9996
  15.750   1.0308   0.19737   0.19273  -0.0918   0.0691   0.9996
  16.000   1.0361   0.20325   0.19862  -0.0936   0.0687   0.9996
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