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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=1,000,000 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: 1,000,000
Max Cl/Cd: 87.8 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4094-il-1000000.txt
Download as CSV file: xf-s4094-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4932   0.09573   0.09429   0.0052   1.0004   0.0139
  -9.250  -0.4949   0.09139   0.08996   0.0039   1.0004   0.0141
  -7.500  -0.6288   0.02907   0.02564  -0.0317   1.0004   0.0136
  -7.250  -0.6027   0.02568   0.02201  -0.0327   1.0004   0.0128
  -7.000  -0.5746   0.02302   0.01899  -0.0336   1.0004   0.0129
  -6.750  -0.5457   0.02111   0.01681  -0.0344   1.0004   0.0130
  -6.500  -0.5164   0.01958   0.01505  -0.0350   1.0004   0.0131
  -6.250  -0.4869   0.01834   0.01363  -0.0356   1.0004   0.0132
  -5.750  -0.4273   0.01526   0.01018  -0.0369   1.0004   0.0137
  -5.500  -0.3975   0.01400   0.00884  -0.0375   1.0004   0.0142
  -5.250  -0.3677   0.01325   0.00805  -0.0380   1.0004   0.0146
  -5.000  -0.3377   0.01265   0.00741  -0.0385   1.0004   0.0150
  -4.750  -0.3077   0.01212   0.00685  -0.0390   1.0004   0.0155
  -4.500  -0.2760   0.01180   0.00649  -0.0398   0.9699   0.0160
  -4.250  -0.2523   0.01172   0.00625  -0.0385   0.9123   0.0163
  -4.000  -0.2259   0.01153   0.00589  -0.0379   0.8729   0.0167
  -3.750  -0.1976   0.01133   0.00553  -0.0378   0.8408   0.0171
  -3.500  -0.1687   0.01116   0.00523  -0.0379   0.8128   0.0175
  -3.250  -0.1391   0.01081   0.00472  -0.0382   0.7879   0.0191
  -3.000  -0.1095   0.01064   0.00445  -0.0384   0.7647   0.0205
  -2.750  -0.0799   0.01052   0.00422  -0.0387   0.7438   0.0222
  -2.500  -0.0501   0.01036   0.00400  -0.0391   0.7242   0.0274
  -2.250  -0.0201   0.01005   0.00382  -0.0396   0.7061   0.0705
  -2.000   0.0096   0.00986   0.00371  -0.0400   0.6894   0.1089
  -1.750   0.0395   0.00965   0.00362  -0.0406   0.6738   0.1601
  -1.250   0.0991   0.00923   0.00349  -0.0416   0.6447   0.2862
  -1.000   0.1290   0.00901   0.00346  -0.0422   0.6314   0.3615
  -0.750   0.1588   0.00879   0.00345  -0.0428   0.6184   0.4471
  -0.500   0.1886   0.00838   0.00348  -0.0434   0.6061   0.5990
  -0.250   0.2179   0.00807   0.00352  -0.0438   0.5940   0.7268
   0.000   0.2410   0.00759   0.00356  -0.0424   0.5822   0.9054
   0.250   0.2676   0.00713   0.00315  -0.0418   0.5703   0.9996
   0.500   0.2974   0.00721   0.00315  -0.0422   0.5582   0.9996
   0.750   0.3273   0.00729   0.00315  -0.0426   0.5459   0.9996
   1.000   0.3570   0.00738   0.00316  -0.0429   0.5329   0.9996
   1.250   0.3868   0.00747   0.00318  -0.0433   0.5197   0.9996
   1.500   0.4165   0.00757   0.00320  -0.0437   0.5058   0.9996
   1.750   0.4462   0.00767   0.00323  -0.0441   0.4906   0.9996
   2.000   0.4759   0.00778   0.00327  -0.0445   0.4746   0.9996
   2.250   0.5055   0.00791   0.00332  -0.0449   0.4576   0.9996
   2.500   0.5350   0.00804   0.00338  -0.0452   0.4397   0.9996
   2.750   0.5646   0.00819   0.00345  -0.0456   0.4221   0.9996
   3.000   0.5940   0.00836   0.00352  -0.0460   0.4041   0.9996
   3.250   0.6235   0.00851   0.00361  -0.0464   0.3869   0.9996
   3.500   0.6529   0.00868   0.00371  -0.0468   0.3692   0.9996
   3.750   0.6822   0.00886   0.00382  -0.0472   0.3520   0.9996
   4.000   0.7115   0.00905   0.00393  -0.0476   0.3346   0.9996
   4.500   0.7700   0.00946   0.00420  -0.0484   0.3003   0.9996
   4.750   0.7992   0.00966   0.00435  -0.0488   0.2845   0.9996
   5.000   0.8283   0.00988   0.00451  -0.0492   0.2687   0.9996
   5.250   0.8573   0.01011   0.00468  -0.0496   0.2523   0.9996
   5.500   0.8863   0.01034   0.00486  -0.0499   0.2378   0.9996
   5.750   0.9152   0.01059   0.00505  -0.0503   0.2223   0.9996
   6.000   0.9440   0.01085   0.00526  -0.0507   0.2075   0.9996
   6.250   0.9727   0.01114   0.00548  -0.0511   0.1916   0.9996
   6.500   1.0013   0.01144   0.00572  -0.0514   0.1763   0.9996
   6.750   1.0299   0.01173   0.00597  -0.0518   0.1636   0.9996
   7.000   1.0582   0.01207   0.00624  -0.0521   0.1485   0.9996
   7.250   1.0864   0.01243   0.00654  -0.0525   0.1334   0.9996
   7.500   1.1146   0.01279   0.00684  -0.0528   0.1202   0.9996
   7.750   1.1427   0.01314   0.00716  -0.0531   0.1092   0.9996
   8.000   1.1706   0.01352   0.00749  -0.0535   0.0975   0.9996
   8.250   1.1982   0.01395   0.00786  -0.0538   0.0850   0.9996
   8.500   1.2258   0.01436   0.00824  -0.0540   0.0752   0.9996
   8.750   1.2532   0.01479   0.00865  -0.0543   0.0663   0.9996
   9.000   1.2802   0.01528   0.00909  -0.0545   0.0568   0.9996
   9.250   1.3071   0.01577   0.00954  -0.0547   0.0488   0.9996
   9.500   1.3339   0.01624   0.01000  -0.0549   0.0420   0.9996
   9.750   1.3602   0.01679   0.01053  -0.0550   0.0348   0.9996
  10.000   1.3858   0.01746   0.01114  -0.0551   0.0262   0.9996
  10.250   1.4092   0.01855   0.01211  -0.0550   0.0126   0.9996
  10.500   1.4332   0.01944   0.01300  -0.0549   0.0085   0.9996
  10.750   1.4572   0.02025   0.01386  -0.0547   0.0072   0.9996
  11.000   1.4813   0.02093   0.01461  -0.0545   0.0067   0.9996
  11.250   1.5047   0.02167   0.01545  -0.0542   0.0063   0.9996
  11.500   1.5269   0.02254   0.01638  -0.0538   0.0059   0.9996
  11.750   1.5474   0.02358   0.01752  -0.0532   0.0056   0.9996
  12.000   1.5648   0.02493   0.01901  -0.0523   0.0053   0.9996
  12.250   1.5836   0.02592   0.02009  -0.0514   0.0052   0.9996
  12.500   1.6012   0.02694   0.02121  -0.0505   0.0051   0.9996
  12.750   1.6168   0.02808   0.02246  -0.0493   0.0050   0.9996
  13.000   1.6298   0.02932   0.02381  -0.0478   0.0049   0.9996
  13.250   1.6396   0.03073   0.02533  -0.0459   0.0048   0.9996
  13.500   1.6453   0.03230   0.02702  -0.0437   0.0047   0.9996
  13.750   1.6395   0.03428   0.02912  -0.0399   0.0046   0.9996
  14.000   1.6332   0.03684   0.03182  -0.0375   0.0046   0.9996
  14.250   1.6281   0.04000   0.03511  -0.0367   0.0045   0.9996
  14.500   1.6230   0.04371   0.03896  -0.0369   0.0045   0.9996
  14.750   1.6161   0.04799   0.04339  -0.0377   0.0044   0.9996
  15.000   1.6073   0.05283   0.04836  -0.0391   0.0044   0.9996
  15.250   1.5957   0.05824   0.05392  -0.0409   0.0043   0.9996
  15.500   1.5809   0.06420   0.06002  -0.0430   0.0043   0.9996
  15.750   1.5634   0.07072   0.06669  -0.0453   0.0043   0.9996
  16.000   1.5435   0.07770   0.07382  -0.0479   0.0043   0.9996
  16.250   1.5220   0.08509   0.08136  -0.0507   0.0043   0.9996
  16.500   1.4989   0.09293   0.08933  -0.0538   0.0043   0.9996
  16.750   1.4762   0.10097   0.09751  -0.0572   0.0043   0.9996
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