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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=500,000 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: 500,000
Max Cl/Cd: 73.29 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4094-il-500000-n5.txt
Download as CSV file: xf-s4094-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6518   0.08551   0.08342   0.0086   1.0004   0.0102
  -8.500  -0.6613   0.07609   0.07400  -0.0009   1.0004   0.0102
  -8.250  -0.7026   0.03394   0.03031  -0.0296   1.0004   0.0102
  -8.000  -0.6796   0.02963   0.02545  -0.0313   1.0004   0.0103
  -7.750  -0.6535   0.02699   0.02240  -0.0323   1.0004   0.0105
  -7.500  -0.6259   0.02543   0.02056  -0.0330   1.0004   0.0107
  -7.250  -0.5984   0.02303   0.01779  -0.0339   1.0004   0.0110
  -7.000  -0.5703   0.02113   0.01564  -0.0347   1.0004   0.0113
  -6.750  -0.5416   0.01982   0.01415  -0.0353   1.0004   0.0115
  -6.500  -0.5126   0.01875   0.01296  -0.0359   1.0004   0.0118
  -6.250  -0.4834   0.01783   0.01193  -0.0364   1.0004   0.0120
  -6.000  -0.4541   0.01699   0.01099  -0.0369   1.0004   0.0123
  -5.750  -0.4246   0.01623   0.01014  -0.0373   1.0004   0.0127
  -5.500  -0.3951   0.01552   0.00934  -0.0378   1.0004   0.0130
  -5.250  -0.3654   0.01487   0.00863  -0.0383   1.0004   0.0134
  -5.000  -0.3340   0.01441   0.00809  -0.0391   0.9644   0.0137
  -4.750  -0.3071   0.01417   0.00772  -0.0386   0.9112   0.0140
  -4.500  -0.2818   0.01393   0.00730  -0.0378   0.8716   0.0144
  -4.250  -0.2547   0.01373   0.00694  -0.0374   0.8400   0.0148
  -4.000  -0.2263   0.01333   0.00638  -0.0375   0.8126   0.0155
  -3.750  -0.1974   0.01301   0.00593  -0.0376   0.7881   0.0162
  -3.500  -0.1683   0.01277   0.00556  -0.0378   0.7656   0.0169
  -3.250  -0.1390   0.01258   0.00525  -0.0380   0.7450   0.0178
  -3.000  -0.1096   0.01242   0.00497  -0.0383   0.7260   0.0188
  -2.750  -0.0801   0.01229   0.00474  -0.0386   0.7083   0.0201
  -2.500  -0.0505   0.01212   0.00450  -0.0389   0.6917   0.0244
  -2.250  -0.0208   0.01188   0.00431  -0.0393   0.6762   0.0486
  -1.750   0.0386   0.01146   0.00404  -0.0402   0.6471   0.1183
  -1.500   0.0683   0.01129   0.00394  -0.0407   0.6334   0.1576
  -1.250   0.0980   0.01111   0.00386  -0.0412   0.6202   0.2037
  -1.000   0.1277   0.01086   0.00380  -0.0417   0.6073   0.2758
  -0.750   0.1574   0.01059   0.00376  -0.0423   0.5950   0.3638
  -0.500   0.1871   0.01027   0.00375  -0.0429   0.5829   0.4725
  -0.250   0.2164   0.00993   0.00376  -0.0435   0.5706   0.5974
   0.000   0.2451   0.00964   0.00379  -0.0437   0.5582   0.7075
   0.250   0.2703   0.00926   0.00381  -0.0428   0.5461   0.8387
   0.500   0.2940   0.00861   0.00333  -0.0413   0.5338   0.9996
   0.750   0.3237   0.00871   0.00333  -0.0416   0.5206   0.9996
   1.000   0.3534   0.00881   0.00335  -0.0420   0.5065   0.9996
   1.250   0.3830   0.00893   0.00337  -0.0424   0.4920   0.9996
   1.500   0.4126   0.00905   0.00340  -0.0428   0.4768   0.9996
   1.750   0.4422   0.00918   0.00344  -0.0431   0.4601   0.9996
   2.000   0.4717   0.00933   0.00350  -0.0435   0.4433   0.9996
   2.500   0.5306   0.00966   0.00365  -0.0443   0.4091   0.9996
   2.750   0.5600   0.00983   0.00374  -0.0447   0.3915   0.9996
   3.000   0.5893   0.01002   0.00385  -0.0451   0.3745   0.9996
   3.250   0.6186   0.01021   0.00396  -0.0454   0.3578   0.9996
   3.500   0.6479   0.01042   0.00410  -0.0458   0.3411   0.9996
   3.750   0.6771   0.01063   0.00424  -0.0462   0.3248   0.9996
   4.000   0.7062   0.01085   0.00439  -0.0466   0.3089   0.9996
   4.250   0.7353   0.01107   0.00456  -0.0470   0.2934   0.9996
   4.500   0.7644   0.01131   0.00474  -0.0474   0.2775   0.9996
   4.750   0.7934   0.01155   0.00493  -0.0477   0.2620   0.9996
   5.000   0.8223   0.01181   0.00513  -0.0481   0.2465   0.9996
   5.250   0.8511   0.01208   0.00536  -0.0485   0.2318   0.9996
   5.500   0.8798   0.01236   0.00559  -0.0489   0.2170   0.9996
   5.750   0.9085   0.01264   0.00583  -0.0492   0.2045   0.9996
   6.000   0.9371   0.01294   0.00609  -0.0496   0.1906   0.9996
   6.250   0.9656   0.01326   0.00638  -0.0499   0.1777   0.9996
   6.500   0.9939   0.01359   0.00668  -0.0503   0.1652   0.9996
   6.750   1.0221   0.01395   0.00700  -0.0506   0.1517   0.9996
   7.000   1.0502   0.01433   0.00734  -0.0509   0.1383   0.9996
   7.250   1.0781   0.01473   0.00771  -0.0512   0.1256   0.9996
   7.500   1.1058   0.01515   0.00809  -0.0515   0.1129   0.9996
   7.750   1.1332   0.01561   0.00850  -0.0518   0.0995   0.9996
   8.000   1.1605   0.01609   0.00894  -0.0521   0.0868   0.9996
   8.250   1.1876   0.01657   0.00940  -0.0523   0.0768   0.9996
   8.500   1.2147   0.01703   0.00986  -0.0525   0.0683   0.9996
   8.750   1.2413   0.01755   0.01036  -0.0527   0.0595   0.9996
   9.000   1.2675   0.01812   0.01091  -0.0528   0.0505   0.9996
   9.250   1.2934   0.01874   0.01152  -0.0530   0.0424   0.9996
   9.500   1.3187   0.01940   0.01215  -0.0530   0.0342   0.9996
   9.750   1.3437   0.02008   0.01283  -0.0530   0.0271   0.9996
  10.000   1.3682   0.02081   0.01356  -0.0530   0.0209   0.9996
  10.250   1.3914   0.02172   0.01445  -0.0528   0.0130   0.9996
  10.500   1.4135   0.02274   0.01547  -0.0525   0.0084   0.9996
  10.750   1.4360   0.02359   0.01641  -0.0521   0.0071   0.9996
  11.000   1.4578   0.02448   0.01739  -0.0517   0.0064   0.9996
  11.250   1.4782   0.02549   0.01849  -0.0511   0.0058   0.9996
  11.500   1.4981   0.02646   0.01957  -0.0504   0.0054   0.9996
  11.750   1.5171   0.02743   0.02066  -0.0496   0.0051   0.9996
  12.000   1.5344   0.02849   0.02184  -0.0487   0.0049   0.9996
  12.250   1.5499   0.02965   0.02314  -0.0475   0.0047   0.9996
  12.500   1.5628   0.03094   0.02455  -0.0461   0.0045   0.9996
  12.750   1.5726   0.03238   0.02613  -0.0443   0.0044   0.9996
  13.000   1.5782   0.03403   0.02790  -0.0422   0.0042   0.9996
  13.250   1.5739   0.03604   0.03005  -0.0389   0.0042   0.9996
  13.500   1.5682   0.03866   0.03281  -0.0367   0.0041   0.9996
  13.750   1.5629   0.04187   0.03618  -0.0359   0.0040   0.9996
  14.000   1.5566   0.04574   0.04022  -0.0362   0.0040   0.9996
  14.250   1.5485   0.05022   0.04486  -0.0372   0.0039   0.9996
  14.500   1.5382   0.05530   0.05011  -0.0387   0.0039   0.9996
  14.750   1.5253   0.06096   0.05594  -0.0407   0.0038   0.9996
  15.000   1.5095   0.06718   0.06233  -0.0429   0.0038   0.9996
  15.250   1.4922   0.07381   0.06911  -0.0455   0.0038   0.9996
  15.500   1.4729   0.08087   0.07633  -0.0482   0.0038   0.9996
  15.750   1.4526   0.08826   0.08388  -0.0512   0.0038   0.9996
  16.000   1.4318   0.09587   0.09164  -0.0543   0.0038   0.9996
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