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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=200,000 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: 200,000
Max Cl/Cd: 58.78 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4094-il-200000-n5.txt
Download as CSV file: xf-s4094-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5983   0.10974   0.10629   0.0157   1.0004   0.0197
  -9.250  -0.5962   0.10567   0.10224   0.0142   1.0004   0.0194
  -9.000  -0.5961   0.10112   0.09772   0.0121   1.0004   0.0191
  -8.750  -0.5976   0.09630   0.09293   0.0097   1.0004   0.0189
  -8.500  -0.6017   0.09124   0.08790   0.0069   1.0004   0.0187
  -8.250  -0.6068   0.08566   0.08236   0.0028   1.0004   0.0185
  -8.000  -0.6066   0.07834   0.07503  -0.0045   1.0004   0.0185
  -7.750  -0.6023   0.06900   0.06561  -0.0138   1.0004   0.0186
  -7.500  -0.5945   0.05733   0.05366  -0.0230   1.0004   0.0186
  -7.250  -0.5823   0.04630   0.04208  -0.0292   1.0004   0.0185
  -7.000  -0.5626   0.03804   0.03310  -0.0330   1.0004   0.0182
  -6.750  -0.5373   0.03251   0.02686  -0.0351   1.0004   0.0181
  -6.500  -0.5095   0.02881   0.02257  -0.0364   1.0004   0.0183
  -6.250  -0.4807   0.02615   0.01943  -0.0372   1.0004   0.0186
  -6.000  -0.4515   0.02411   0.01701  -0.0379   1.0004   0.0189
  -5.750  -0.4221   0.02249   0.01508  -0.0384   1.0004   0.0193
  -5.500  -0.3926   0.02122   0.01358  -0.0389   1.0004   0.0198
  -5.250  -0.3636   0.01984   0.01209  -0.0394   1.0004   0.0208
  -5.000  -0.3344   0.01891   0.01112  -0.0399   1.0004   0.0219
  -4.750  -0.3050   0.01799   0.01013  -0.0404   1.0004   0.0225
  -4.500  -0.2754   0.01715   0.00921  -0.0408   1.0004   0.0232
  -4.250  -0.2458   0.01641   0.00842  -0.0413   1.0004   0.0241
  -4.000  -0.2161   0.01577   0.00772  -0.0418   1.0004   0.0251
  -3.750  -0.1862   0.01523   0.00711  -0.0423   1.0004   0.0263
  -3.500  -0.1530   0.01479   0.00665  -0.0436   0.9711   0.0289
  -3.250  -0.1188   0.01458   0.00637  -0.0448   0.9276   0.0342
  -3.000  -0.0901   0.01428   0.00608  -0.0447   0.8903   0.0485
  -2.750  -0.0634   0.01402   0.00584  -0.0441   0.8588   0.0788
  -2.500  -0.0367   0.01381   0.00566  -0.0437   0.8314   0.1139
  -2.250  -0.0096   0.01355   0.00551  -0.0435   0.8072   0.1652
  -2.000   0.0182   0.01319   0.00538  -0.0436   0.7850   0.2432
  -1.500   0.0742   0.01248   0.00519  -0.0438   0.7459   0.4421
  -1.250   0.1017   0.01209   0.00514  -0.0438   0.7282   0.5582
  -1.000   0.1262   0.01158   0.00510  -0.0427   0.7118   0.7079
  -0.750   0.1443   0.01096   0.00486  -0.0395   0.6967   0.8848
  -0.500   0.1767   0.01053   0.00432  -0.0401   0.6805   0.9996
  -0.250   0.2060   0.01064   0.00426  -0.0403   0.6655   0.9996
   0.000   0.2353   0.01076   0.00422  -0.0406   0.6508   0.9996
   0.250   0.2646   0.01088   0.00419  -0.0408   0.6365   0.9996
   0.500   0.2939   0.01101   0.00418  -0.0411   0.6224   0.9996
   0.750   0.3232   0.01113   0.00418  -0.0413   0.6084   0.9996
   1.000   0.3525   0.01127   0.00420  -0.0416   0.5944   0.9996
   1.250   0.3818   0.01140   0.00423  -0.0419   0.5803   0.9996
   1.500   0.4111   0.01154   0.00427  -0.0422   0.5660   0.9996
   1.750   0.4403   0.01169   0.00432  -0.0424   0.5515   0.9996
   2.000   0.4695   0.01184   0.00439  -0.0427   0.5365   0.9996
   2.250   0.4987   0.01200   0.00447  -0.0430   0.5212   0.9996
   2.500   0.5279   0.01216   0.00456  -0.0433   0.5052   0.9996
   2.750   0.5570   0.01233   0.00467  -0.0436   0.4884   0.9996
   3.000   0.5861   0.01252   0.00478  -0.0438   0.4713   0.9996
   3.250   0.6151   0.01272   0.00490  -0.0441   0.4536   0.9996
   3.500   0.6441   0.01293   0.00506  -0.0444   0.4351   0.9996
   3.750   0.6729   0.01316   0.00522  -0.0447   0.4163   0.9996
   4.000   0.7017   0.01341   0.00540  -0.0450   0.3980   0.9996
   4.250   0.7304   0.01368   0.00561  -0.0453   0.3798   0.9996
   4.500   0.7591   0.01395   0.00585  -0.0456   0.3613   0.9996
   4.750   0.7877   0.01425   0.00609  -0.0460   0.3433   0.9996
   5.000   0.8162   0.01457   0.00636  -0.0463   0.3255   0.9996
   5.250   0.8446   0.01489   0.00666  -0.0466   0.3083   0.9996
   5.500   0.8729   0.01523   0.00697  -0.0469   0.2907   0.9996
   5.750   0.9012   0.01559   0.00730  -0.0472   0.2736   0.9996
   6.000   0.9292   0.01597   0.00765  -0.0475   0.2568   0.9996
   6.250   0.9571   0.01637   0.00804  -0.0477   0.2406   0.9996
   6.500   0.9849   0.01679   0.00845  -0.0480   0.2250   0.9996
   6.750   1.0125   0.01723   0.00887  -0.0483   0.2101   0.9996
   7.000   1.0399   0.01769   0.00933  -0.0485   0.1953   0.9996
   7.250   1.0671   0.01817   0.00983  -0.0487   0.1810   0.9996
   7.500   1.0941   0.01868   0.01034  -0.0489   0.1670   0.9996
   7.750   1.1208   0.01921   0.01089  -0.0491   0.1533   0.9996
   8.250   1.1734   0.02036   0.01209  -0.0494   0.1283   0.9996
   8.500   1.1993   0.02096   0.01274  -0.0494   0.1172   0.9996
   8.750   1.2248   0.02160   0.01343  -0.0495   0.1070   0.9996
   9.000   1.2498   0.02230   0.01416  -0.0495   0.0970   0.9996
   9.250   1.2741   0.02306   0.01494  -0.0494   0.0864   0.9996
   9.500   1.2978   0.02387   0.01576  -0.0493   0.0752   0.9996
   9.750   1.3210   0.02469   0.01661  -0.0492   0.0650   0.9996
  10.000   1.3439   0.02551   0.01749  -0.0489   0.0563   0.9996
  10.250   1.3658   0.02642   0.01846  -0.0486   0.0488   0.9996
  10.500   1.3865   0.02743   0.01951  -0.0481   0.0421   0.9996
  10.750   1.4066   0.02844   0.02063  -0.0476   0.0356   0.9996
  11.000   1.4248   0.02962   0.02188  -0.0468   0.0289   0.9996
  11.250   1.4403   0.03102   0.02333  -0.0458   0.0222   0.9996
  11.500   1.4529   0.03259   0.02498  -0.0445   0.0172   0.9996
  11.750   1.4623   0.03434   0.02681  -0.0428   0.0143   0.9996
  12.000   1.4699   0.03606   0.02870  -0.0410   0.0128   0.9996
  12.250   1.4729   0.03803   0.03082  -0.0388   0.0118   0.9996
  12.500   1.4671   0.04036   0.03330  -0.0358   0.0113   0.9996
  12.750   1.4604   0.04330   0.03640  -0.0340   0.0108   0.9996
  13.000   1.4557   0.04658   0.03988  -0.0334   0.0105   0.9996
  13.250   1.4498   0.05039   0.04392  -0.0337   0.0102   0.9996
  13.500   1.4426   0.05472   0.04845  -0.0346   0.0100   0.9996
  13.750   1.4337   0.05955   0.05347  -0.0360   0.0098   0.9996
  14.000   1.4227   0.06485   0.05896  -0.0378   0.0096   0.9996
  14.250   1.4099   0.07062   0.06491  -0.0400   0.0095   0.9996
  14.500   1.3952   0.07682   0.07130  -0.0424   0.0094   0.9996
  14.750   1.3790   0.08344   0.07809  -0.0451   0.0094   0.9996
  15.000   1.3616   0.09042   0.08524  -0.0481   0.0093   0.9996
  15.250   1.3433   0.09769   0.09268  -0.0513   0.0093   0.9996
  15.500   1.3252   0.10523   0.10038  -0.0547   0.0093   0.9996
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