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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=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: 50,000
Max Cl/Cd: 29.14 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4094-il-50000.txt
Download as CSV file: xf-s4094-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5491   0.12184   0.11524   0.0208   1.0004   0.2148
  -8.500  -0.5393   0.11737   0.11080   0.0208   1.0004   0.2222
  -8.250  -0.5541   0.11560   0.10914   0.0180   1.0004   0.2311
  -8.000  -0.5313   0.11020   0.10373   0.0195   1.0004   0.2406
  -7.750  -0.5392   0.10710   0.10073   0.0179   1.0004   0.2490
  -7.500  -0.5432   0.10438   0.09808   0.0170   1.0004   0.2607
  -7.250  -0.5252   0.09966   0.09337   0.0182   1.0004   0.2717
  -7.000  -0.5218   0.09599   0.08976   0.0178   1.0004   0.2832
  -6.750  -0.5176   0.09235   0.08618   0.0170   1.0004   0.2971
  -6.500  -0.5110   0.08869   0.08257   0.0166   1.0004   0.3127
  -6.250  -0.5031   0.08513   0.07905   0.0164   1.0004   0.3308
  -6.000  -0.5001   0.08171   0.07568   0.0151   1.0004   0.3540
  -5.750  -0.4934   0.07865   0.07266   0.0152   1.0004   0.3828
  -5.250  -0.4277   0.05932   0.05265  -0.0214   1.0004   0.2376
  -5.000  -0.3636   0.04410   0.03569  -0.0401   1.0004   0.1351
  -4.750  -0.3260   0.03896   0.02947  -0.0434   1.0004   0.1270
  -4.500  -0.2937   0.03542   0.02543  -0.0447   1.0004   0.1263
  -4.250  -0.2609   0.03239   0.02185  -0.0456   1.0004   0.1290
  -4.000  -0.2315   0.03019   0.01958  -0.0460   1.0004   0.1387
  -3.750  -0.2009   0.02791   0.01707  -0.0462   1.0004   0.1492
  -3.500  -0.1707   0.02600   0.01497  -0.0461   1.0004   0.1710
  -3.250  -0.1429   0.02413   0.01332  -0.0458   1.0004   0.2147
  -3.000  -0.1161   0.02241   0.01209  -0.0454   1.0004   0.2978
  -2.750  -0.0904   0.02040   0.01094  -0.0445   1.0004   0.4424
  -2.500  -0.0830   0.01799   0.01038  -0.0379   1.0004   0.7340
  -2.250  -0.0508   0.01700   0.00927  -0.0377   1.0004   0.9996
  -2.000  -0.0253   0.01718   0.00899  -0.0381   1.0004   0.9996
  -1.750  -0.0023   0.01748   0.00895  -0.0381   1.0004   0.9996
  -1.500   0.0191   0.01794   0.00912  -0.0380   1.0004   0.9996
  -1.250   0.0391   0.01854   0.00948  -0.0379   1.0004   0.9996
  -1.000   0.0588   0.01926   0.01000  -0.0380   1.0004   0.9996
  -0.750   0.0785   0.02009   0.01062  -0.0382   1.0004   0.9996
  -0.500   0.0979   0.02100   0.01136  -0.0386   1.0004   0.9996
  -0.250   0.1171   0.02198   0.01219  -0.0392   1.0004   0.9996
   0.000   0.1361   0.02302   0.01311  -0.0398   1.0004   0.9996
   0.250   0.1940   0.02341   0.01330  -0.0471   0.9855   0.9996
   0.500   0.2552   0.02357   0.01332  -0.0547   0.9661   0.9996
   0.750   0.3177   0.02358   0.01322  -0.0622   0.9470   0.9996
   1.000   0.3829   0.02342   0.01300  -0.0697   0.9291   0.9996
   1.250   0.4320   0.02349   0.01303  -0.0738   0.9072   0.9996
   1.500   0.4765   0.02359   0.01310  -0.0765   0.8857   0.9996
   1.750   0.5107   0.02393   0.01343  -0.0772   0.8625   0.9996
   2.000   0.5417   0.02429   0.01377  -0.0769   0.8402   0.9996
   2.250   0.5683   0.02480   0.01427  -0.0759   0.8170   0.9996
   2.500   0.5941   0.02525   0.01470  -0.0745   0.7951   0.9996
   2.750   0.6184   0.02583   0.01529  -0.0730   0.7722   0.9996
   3.000   0.6425   0.02632   0.01577  -0.0713   0.7505   0.9996
   3.250   0.6663   0.02689   0.01634  -0.0697   0.7281   0.9996
   3.500   0.6902   0.02742   0.01689  -0.0680   0.7062   0.9996
   3.750   0.7141   0.02795   0.01742  -0.0663   0.6847   0.9996
   4.000   0.7383   0.02852   0.01801  -0.0649   0.6620   0.9996
   4.250   0.7625   0.02896   0.01843  -0.0631   0.6415   0.9996
   4.500   0.7870   0.02962   0.01918  -0.0620   0.6178   0.9996
   4.750   0.8116   0.02999   0.01951  -0.0601   0.5977   0.9996
   5.000   0.8363   0.03073   0.02035  -0.0593   0.5735   0.9996
   5.250   0.8613   0.03108   0.02066  -0.0576   0.5532   0.9996
   5.500   0.8862   0.03184   0.02156  -0.0568   0.5290   0.9996
   5.750   0.9115   0.03219   0.02187  -0.0553   0.5086   0.9996
   6.000   0.9363   0.03300   0.02280  -0.0545   0.4845   0.9996
   6.250   0.9619   0.03337   0.02315  -0.0531   0.4642   0.9996
   6.500   0.9864   0.03427   0.02420  -0.0524   0.4404   0.9996
   6.750   1.0122   0.03474   0.02460  -0.0511   0.4202   0.9996
   7.000   1.0361   0.03585   0.02588  -0.0505   0.3970   0.9996
   7.250   1.0616   0.03653   0.02654  -0.0494   0.3767   0.9996
   7.500   1.0849   0.03787   0.02805  -0.0488   0.3548   0.9996
   7.750   1.1092   0.03892   0.02914  -0.0479   0.3346   0.9996
   8.000   1.1335   0.04009   0.03030  -0.0470   0.3156   0.9996
   8.250   1.1543   0.04198   0.03251  -0.0464   0.2959   0.9996
   8.500   1.1765   0.04358   0.03422  -0.0456   0.2779   0.9996
   8.750   1.1988   0.04517   0.03588  -0.0447   0.2611   0.9996
   9.000   1.2207   0.04689   0.03767  -0.0439   0.2451   0.9996
   9.250   1.2400   0.04914   0.04010  -0.0431   0.2306   0.9996
   9.500   1.2569   0.05156   0.04279  -0.0422   0.2166   0.9996
   9.750   1.2617   0.05587   0.04770  -0.0412   0.2063   0.9996
  10.000   1.2693   0.05946   0.05159  -0.0401   0.1961   0.9996
  10.250   1.2857   0.06196   0.05417  -0.0390   0.1855   0.9996
  10.500   1.2639   0.06881   0.06164  -0.0377   0.1826   0.9996
  10.750   1.2314   0.07633   0.06954  -0.0370   0.1823   0.9996
  11.000   1.1867   0.08464   0.07802  -0.0369   0.1847   0.9996
  11.250   1.1452   0.09384   0.08725  -0.0393   0.1866   0.9996
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