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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=50,000 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: 50,000
Max Cl/Cd: 34.78 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4094-il-50000-n5.txt
Download as CSV file: xf-s4094-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5654   0.11884   0.11204   0.0106   1.0004   0.0702
  -9.000  -0.5567   0.11440   0.10757   0.0100   1.0004   0.0642
  -8.500  -0.5739   0.10192   0.09523  -0.0013   1.0004   0.0554
  -8.250  -0.5701   0.09726   0.09060  -0.0037   1.0004   0.0551
  -8.000  -0.5654   0.09237   0.08573  -0.0066   1.0004   0.0547
  -7.750  -0.5597   0.08728   0.08063  -0.0099   1.0004   0.0541
  -7.500  -0.5528   0.08192   0.07524  -0.0135   1.0004   0.0534
  -7.250  -0.5444   0.07622   0.06947  -0.0175   1.0004   0.0524
  -7.000  -0.5337   0.07018   0.06329  -0.0218   1.0004   0.0514
  -6.750  -0.5199   0.06392   0.05680  -0.0261   1.0004   0.0505
  -6.500  -0.5023   0.05767   0.05017  -0.0303   1.0004   0.0497
  -6.250  -0.4805   0.05186   0.04388  -0.0338   1.0004   0.0492
  -6.000  -0.4555   0.04674   0.03823  -0.0366   1.0004   0.0491
  -5.750  -0.4281   0.04235   0.03327  -0.0387   1.0004   0.0495
  -5.500  -0.3993   0.03878   0.02915  -0.0402   1.0004   0.0511
  -5.250  -0.3693   0.03572   0.02545  -0.0414   1.0004   0.0540
  -5.000  -0.3394   0.03306   0.02229  -0.0421   1.0004   0.0563
  -4.750  -0.3110   0.03095   0.01999  -0.0426   1.0004   0.0586
  -4.500  -0.2821   0.02910   0.01793  -0.0428   1.0004   0.0615
  -4.250  -0.2532   0.02740   0.01598  -0.0427   1.0004   0.0655
  -4.000  -0.2250   0.02598   0.01447  -0.0428   1.0004   0.0722
  -3.750  -0.1969   0.02476   0.01318  -0.0428   1.0004   0.0840
  -3.500  -0.1687   0.02355   0.01197  -0.0429   1.0004   0.1028
  -3.250  -0.1402   0.02245   0.01107  -0.0435   1.0004   0.1469
  -3.000  -0.1122   0.02129   0.01031  -0.0440   1.0004   0.2175
  -2.750  -0.0851   0.02023   0.00975  -0.0444   1.0004   0.3157
  -2.500  -0.0605   0.01924   0.00942  -0.0441   1.0004   0.4555
  -2.250  -0.0420   0.01829   0.00929  -0.0418   1.0004   0.6316
  -2.000  -0.0255   0.01742   0.00911  -0.0379   1.0004   0.8964
  -1.750  -0.0027   0.01749   0.00897  -0.0380   1.0004   0.9996
  -1.500   0.0317   0.01773   0.00884  -0.0402   0.9920   0.9996
  -1.250   0.0781   0.01778   0.00852  -0.0444   0.9719   0.9996
  -1.000   0.1222   0.01784   0.00826  -0.0481   0.9500   0.9996
  -0.750   0.1652   0.01792   0.00806  -0.0513   0.9288   0.9996
  -0.500   0.2036   0.01805   0.00795  -0.0534   0.9054   0.9996
  -0.250   0.2390   0.01822   0.00788  -0.0547   0.8832   0.9996
   0.000   0.2699   0.01844   0.00791  -0.0551   0.8596   0.9996
   0.250   0.2990   0.01869   0.00796  -0.0549   0.8383   0.9996
   0.500   0.3265   0.01895   0.00806  -0.0545   0.8164   0.9996
   0.750   0.3535   0.01923   0.00817  -0.0539   0.7965   0.9996
   1.000   0.3803   0.01951   0.00831  -0.0534   0.7769   0.9996
   1.250   0.4071   0.01980   0.00848  -0.0529   0.7575   0.9996
   1.500   0.4337   0.02008   0.00865  -0.0523   0.7389   0.9996
   1.750   0.4604   0.02037   0.00883  -0.0517   0.7211   0.9996
   2.000   0.4873   0.02067   0.00906  -0.0512   0.7026   0.9996
   2.250   0.5144   0.02098   0.00930  -0.0509   0.6841   0.9996
   2.500   0.5413   0.02128   0.00954  -0.0504   0.6660   0.9996
   2.750   0.5683   0.02159   0.00981  -0.0500   0.6483   0.9996
   3.000   0.5953   0.02190   0.01007  -0.0495   0.6305   0.9996
   3.250   0.6225   0.02223   0.01039  -0.0493   0.6114   0.9996
   3.500   0.6496   0.02256   0.01074  -0.0490   0.5927   0.9996
   3.750   0.6765   0.02288   0.01104  -0.0486   0.5744   0.9996
   4.000   0.7035   0.02323   0.01138  -0.0482   0.5557   0.9996
   4.250   0.7305   0.02359   0.01178  -0.0480   0.5357   0.9996
   4.500   0.7574   0.02395   0.01218  -0.0477   0.5165   0.9996
   4.750   0.7843   0.02433   0.01256  -0.0474   0.4972   0.9996
   5.000   0.8112   0.02475   0.01304  -0.0472   0.4764   0.9996
   5.250   0.8378   0.02515   0.01345  -0.0469   0.4568   0.9996
   5.500   0.8643   0.02562   0.01400  -0.0467   0.4364   0.9996
   5.750   0.8906   0.02611   0.01453  -0.0464   0.4159   0.9996
   6.250   0.9425   0.02724   0.01574  -0.0459   0.3758   0.9996
   6.500   0.9680   0.02787   0.01644  -0.0456   0.3562   0.9996
   6.750   0.9932   0.02856   0.01716  -0.0453   0.3373   0.9996
   7.000   1.0181   0.02932   0.01804  -0.0451   0.3173   0.9996
   7.250   1.0426   0.03013   0.01891  -0.0447   0.2989   0.9996
   7.500   1.0665   0.03096   0.01981  -0.0444   0.2813   0.9996
   7.750   1.0901   0.03192   0.02090  -0.0441   0.2634   0.9996
   8.000   1.1130   0.03293   0.02204  -0.0437   0.2460   0.9996
   8.250   1.1354   0.03401   0.02324  -0.0432   0.2299   0.9996
   8.500   1.1570   0.03515   0.02453  -0.0427   0.2144   0.9996
   8.750   1.1779   0.03640   0.02590  -0.0422   0.2001   0.9996
   9.000   1.1978   0.03772   0.02736  -0.0416   0.1863   0.9996
   9.250   1.2169   0.03915   0.02895  -0.0409   0.1735   0.9996
   9.500   1.2348   0.04067   0.03063  -0.0401   0.1616   0.9996
   9.750   1.2516   0.04225   0.03233  -0.0392   0.1508   0.9996
  10.000   1.2676   0.04387   0.03409  -0.0382   0.1410   0.9996
  10.250   1.2804   0.04587   0.03641  -0.0371   0.1310   0.9996
  10.500   1.2926   0.04790   0.03863  -0.0359   0.1229   0.9996
  10.750   1.3032   0.04987   0.04074  -0.0346   0.1153   0.9996
  11.000   1.3085   0.05244   0.04364  -0.0331   0.1081   0.9996
  11.250   1.3148   0.05454   0.04583  -0.0315   0.1020   0.9996
  11.500   1.3134   0.05766   0.04929  -0.0297   0.0969   0.9996
  11.750   1.3066   0.06066   0.05255  -0.0276   0.0924   0.9996
  12.000   1.3066   0.06285   0.05466  -0.0260   0.0877   0.9996
  12.250   1.2882   0.06764   0.05988  -0.0252   0.0851   0.9996
  12.500   1.2709   0.07290   0.06547  -0.0257   0.0828   0.9996
  12.750   1.2543   0.07843   0.07124  -0.0271   0.0805   0.9996
  13.000   1.2579   0.08065   0.07335  -0.0270   0.0755   0.9996
  13.250   1.2331   0.08822   0.08124  -0.0302   0.0748   0.9996
  13.500   1.2061   0.09683   0.09006  -0.0344   0.0746   0.9996
  13.750   1.1767   0.10664   0.10007  -0.0397   0.0749   0.9996
  14.000   1.1449   0.11784   0.11141  -0.0461   0.0755   0.9996
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