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S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il)
Reynolds number: 500,000
Max Cl/Cd: 59.08 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4096-il-500000.txt
Download as CSV file: xf-s4096-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4096 (designed for the E-flite UMX ASK-21 scale
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6947   0.10204   0.09991   0.0091   1.0011   0.0228
  -9.000  -0.7093   0.09478   0.09267   0.0041   1.0011   0.0230
  -8.750  -0.7150   0.08480   0.08265  -0.0053   1.0011   0.0234
  -8.500  -0.6902   0.05170   0.04885  -0.0261   1.0011   0.0267
  -8.250  -0.6737   0.04927   0.04642  -0.0265   1.0011   0.0272
  -8.000  -0.6571   0.04660   0.04366  -0.0272   1.0011   0.0279
  -7.750  -0.6391   0.04338   0.04028  -0.0282   1.0011   0.0289
  -7.500  -0.6423   0.03220   0.02677  -0.0297   1.0011   0.0209
  -7.250  -0.6125   0.03097   0.02531  -0.0303   1.0011   0.0206
  -7.000  -0.5831   0.02774   0.02174  -0.0314   1.0011   0.0208
  -6.750  -0.5534   0.02559   0.01937  -0.0322   1.0011   0.0209
  -6.500  -0.5236   0.02389   0.01751  -0.0328   1.0011   0.0210
  -6.250  -0.4939   0.02245   0.01596  -0.0335   1.0011   0.0213
  -6.000  -0.4641   0.02137   0.01481  -0.0342   1.0011   0.0217
  -5.750  -0.4342   0.02052   0.01391  -0.0348   1.0011   0.0222
  -5.500  -0.4041   0.01979   0.01314  -0.0355   1.0011   0.0227
  -5.250  -0.3739   0.01920   0.01253  -0.0362   1.0011   0.0236
  -5.000  -0.3436   0.01868   0.01197  -0.0370   1.0011   0.0246
  -4.750  -0.3131   0.01816   0.01141  -0.0377   1.0011   0.0253
  -4.500  -0.2826   0.01773   0.01095  -0.0384   1.0011   0.0259
  -4.250  -0.2517   0.01713   0.01031  -0.0393   1.0011   0.0275
  -4.000  -0.2210   0.01679   0.00997  -0.0401   1.0011   0.0294
  -3.750  -0.1903   0.01654   0.00971  -0.0409   1.0011   0.0319
  -3.500  -0.1594   0.01626   0.00946  -0.0417   1.0011   0.0394
  -3.250  -0.1283   0.01568   0.00930  -0.0429   1.0011   0.1237
  -3.000  -0.0975   0.01528   0.00931  -0.0442   1.0011   0.2194
  -2.750  -0.0666   0.01503   0.00938  -0.0453   1.0011   0.3048
  -2.500  -0.0358   0.01485   0.00948  -0.0464   1.0011   0.3778
  -2.250   0.0005   0.01486   0.00979  -0.0488   0.9756   0.4639
  -2.000   0.0316   0.01472   0.00997  -0.0496   0.9355   0.5629
  -1.750   0.0562   0.01459   0.01019  -0.0486   0.8978   0.6842
  -1.500   0.0761   0.01432   0.01046  -0.0461   0.8673   0.8596
  -1.250   0.0977   0.01355   0.00972  -0.0439   0.8381   0.9989
  -1.000   0.1270   0.01361   0.00960  -0.0443   0.8120   0.9989
  -0.750   0.1567   0.01367   0.00949  -0.0447   0.7887   0.9989
  -0.500   0.1867   0.01374   0.00940  -0.0453   0.7667   0.9989
  -0.250   0.2167   0.01381   0.00932  -0.0459   0.7466   0.9989
   0.000   0.2468   0.01387   0.00925  -0.0465   0.7280   0.9989
   0.250   0.2771   0.01394   0.00920  -0.0471   0.7102   0.9989
   0.500   0.3073   0.01400   0.00916  -0.0478   0.6933   0.9989
   0.750   0.3376   0.01407   0.00912  -0.0485   0.6772   0.9989
   1.000   0.3678   0.01415   0.00910  -0.0492   0.6615   0.9989
   1.250   0.3981   0.01422   0.00909  -0.0499   0.6464   0.9989
   1.500   0.4283   0.01430   0.00909  -0.0505   0.6315   0.9989
   1.750   0.4585   0.01438   0.00909  -0.0512   0.6168   0.9989
   2.000   0.4887   0.01447   0.00911  -0.0519   0.6020   0.9989
   2.250   0.5189   0.01456   0.00913  -0.0526   0.5872   0.9989
   2.500   0.5490   0.01465   0.00916  -0.0533   0.5720   0.9989
   2.750   0.5791   0.01475   0.00920  -0.0540   0.5563   0.9989
   3.000   0.6092   0.01485   0.00924  -0.0547   0.5401   0.9989
   3.250   0.6392   0.01497   0.00930  -0.0554   0.5227   0.9989
   3.500   0.6691   0.01510   0.00936  -0.0560   0.5046   0.9989
   3.750   0.6990   0.01524   0.00943  -0.0567   0.4856   0.9989
   4.000   0.7289   0.01538   0.00952  -0.0574   0.4652   0.9989
   4.250   0.7586   0.01556   0.00962  -0.0581   0.4439   0.9989
   4.500   0.7883   0.01575   0.00973  -0.0588   0.4225   0.9989
   4.750   0.8179   0.01596   0.00986  -0.0595   0.4004   0.9989
   5.000   0.8474   0.01618   0.01001  -0.0601   0.3790   0.9989
   5.250   0.8768   0.01642   0.01017  -0.0608   0.3572   0.9989
   5.500   0.9061   0.01668   0.01036  -0.0615   0.3369   0.9989
   5.750   0.9355   0.01694   0.01056  -0.0621   0.3159   0.9989
   6.000   0.9646   0.01723   0.01078  -0.0628   0.2959   0.9989
   6.250   0.9937   0.01753   0.01102  -0.0634   0.2761   0.9989
   6.500   1.0227   0.01784   0.01127  -0.0641   0.2567   0.9989
   6.750   1.0514   0.01821   0.01156  -0.0647   0.2368   0.9989
   7.000   1.0802   0.01856   0.01186  -0.0653   0.2176   0.9989
   7.250   1.1088   0.01894   0.01218  -0.0659   0.1992   0.9989
   7.500   1.1372   0.01934   0.01252  -0.0665   0.1823   0.9989
   7.750   1.1655   0.01975   0.01288  -0.0671   0.1669   0.9989
   8.000   1.1935   0.02020   0.01329  -0.0676   0.1517   0.9989
   8.500   1.2491   0.02116   0.01415  -0.0686   0.1222   0.9989
   8.750   1.2766   0.02167   0.01462  -0.0691   0.1085   0.9989
   9.000   1.3037   0.02221   0.01512  -0.0695   0.0957   0.9989
   9.250   1.3306   0.02279   0.01566  -0.0699   0.0841   0.9989
   9.500   1.3574   0.02336   0.01621  -0.0703   0.0741   0.9989
   9.750   1.3839   0.02392   0.01677  -0.0706   0.0651   0.9989
  10.000   1.4101   0.02453   0.01740  -0.0709   0.0576   0.9989
  10.250   1.4356   0.02526   0.01810  -0.0711   0.0503   0.9989
  10.500   1.4615   0.02583   0.01871  -0.0713   0.0453   0.9989
  10.750   1.4864   0.02656   0.01946  -0.0714   0.0399   0.9989
  11.000   1.5109   0.02731   0.02021  -0.0715   0.0342   0.9989
  11.250   1.5348   0.02810   0.02103  -0.0715   0.0282   0.9989
  11.500   1.5559   0.02933   0.02223  -0.0711   0.0200   0.9989
  11.750   1.5760   0.03064   0.02356  -0.0705   0.0150   0.9989
  12.000   1.5956   0.03188   0.02485  -0.0699   0.0127   0.9989
  12.250   1.6138   0.03321   0.02628  -0.0690   0.0114   0.9989
  12.500   1.6317   0.03444   0.02762  -0.0681   0.0106   0.9989
  12.750   1.6464   0.03592   0.02922  -0.0668   0.0099   0.9989
  13.000   1.6545   0.03796   0.03138  -0.0646   0.0094   0.9989
  13.250   1.6594   0.04004   0.03360  -0.0620   0.0091   0.9989
  13.500   1.6605   0.04210   0.03582  -0.0588   0.0089   0.9989
  13.750   1.6474   0.04495   0.03882  -0.0537   0.0087   0.9989
  14.000   1.6383   0.04823   0.04226  -0.0506   0.0086   0.9989
  14.250   1.6301   0.05199   0.04618  -0.0488   0.0085   0.9989
  14.500   1.6217   0.05622   0.05057  -0.0479   0.0083   0.9989
  14.750   1.6125   0.06092   0.05544  -0.0478   0.0082   0.9989
  15.000   1.6019   0.06609   0.06076  -0.0483   0.0081   0.9989
  15.250   1.5901   0.07165   0.06649  -0.0492   0.0080   0.9989
  15.500   1.5766   0.07763   0.07262  -0.0505   0.0080   0.9989
  15.750   1.5617   0.08392   0.07908  -0.0522   0.0079   0.9989
  16.000   1.5454   0.09051   0.08582  -0.0541   0.0079   0.9989
  16.250   1.5286   0.09732   0.09278  -0.0563   0.0078   0.9989
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