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S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il)
Reynolds number: 50,000
Max Cl/Cd: 27.69 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4096-il-50000.txt
Download as CSV file: xf-s4096-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6240   0.12728   0.12061   0.0219   1.0011   0.2649
  -8.500  -0.5977   0.12185   0.11515   0.0230   1.0011   0.2749
  -8.000  -0.6315   0.11522   0.10873   0.0214   1.0011   0.2961
  -7.750  -0.6197   0.11087   0.10438   0.0223   1.0011   0.3101
  -7.500  -0.6148   0.10671   0.10026   0.0225   1.0011   0.3251
  -7.250  -0.6192   0.10278   0.09638   0.0214   1.0011   0.3419
  -7.000  -0.5998   0.09822   0.09184   0.0240   1.0011   0.3596
  -6.750  -0.5786   0.06735   0.05929  -0.0284   1.0011   0.1463
  -6.500  -0.5498   0.05975   0.05124  -0.0322   1.0011   0.1336
  -6.250  -0.5196   0.05451   0.04555  -0.0347   1.0011   0.1287
  -6.000  -0.4872   0.04916   0.03958  -0.0373   1.0011   0.1236
  -5.750  -0.4521   0.04436   0.03388  -0.0395   1.0011   0.1199
  -5.500  -0.4197   0.04092   0.02995  -0.0406   1.0011   0.1204
  -5.250  -0.3888   0.03833   0.02709  -0.0412   1.0011   0.1260
  -5.000  -0.3563   0.03586   0.02409  -0.0418   1.0011   0.1327
  -4.750  -0.3264   0.03355   0.02177  -0.0420   1.0011   0.1414
  -4.500  -0.2963   0.03152   0.01968  -0.0419   1.0011   0.1570
  -4.250  -0.2669   0.02959   0.01782  -0.0417   1.0011   0.1904
  -4.000  -0.2387   0.02720   0.01637  -0.0415   1.0011   0.3130
  -3.750  -0.2198   0.02498   0.01580  -0.0386   1.0011   0.5671
  -3.500  -0.2093   0.02374   0.01547  -0.0321   1.0011   0.7457
  -3.250  -0.1669   0.02223   0.01415  -0.0318   1.0011   0.9989
  -3.000  -0.1367   0.02177   0.01308  -0.0342   1.0011   0.9989
  -2.750  -0.1076   0.02167   0.01254  -0.0354   1.0011   0.9989
  -2.500  -0.0792   0.02169   0.01219  -0.0363   1.0011   0.9989
  -2.250  -0.0514   0.02181   0.01201  -0.0370   1.0011   0.9989
  -2.000  -0.0241   0.02201   0.01196  -0.0375   1.0011   0.9989
  -1.750   0.0026   0.02230   0.01202  -0.0380   1.0011   0.9989
  -1.500   0.0285   0.02270   0.01225  -0.0383   1.0011   0.9989
  -1.250   0.0534   0.02324   0.01264  -0.0386   1.0011   0.9989
  -1.000   0.0773   0.02392   0.01318  -0.0388   1.0011   0.9989
  -0.750   0.0999   0.02478   0.01393  -0.0389   1.0011   0.9989
  -0.500   0.1212   0.02583   0.01490  -0.0389   1.0011   0.9989
  -0.250   0.1414   0.02708   0.01606  -0.0390   1.0011   0.9989
   0.000   0.1607   0.02848   0.01739  -0.0392   1.0011   0.9989
   0.250   0.1792   0.03000   0.01885  -0.0395   1.0011   0.9989
   0.500   0.1970   0.03161   0.02042  -0.0399   1.0011   0.9989
   0.750   0.2144   0.03328   0.02206  -0.0404   1.0011   0.9989
   1.000   0.2348   0.03482   0.02358  -0.0416   0.9998   0.9989
   1.250   0.2982   0.03457   0.02328  -0.0502   0.9852   0.9989
   1.500   0.3576   0.03410   0.02279  -0.0579   0.9677   0.9989
   1.750   0.4179   0.03351   0.02221  -0.0654   0.9502   0.9989
   2.000   0.4811   0.03266   0.02141  -0.0732   0.9335   0.9989
   2.250   0.5414   0.03179   0.02060  -0.0798   0.9160   0.9989
   2.500   0.5905   0.03130   0.02019  -0.0839   0.8953   0.9989
   2.750   0.6302   0.03117   0.02013  -0.0857   0.8722   0.9989
   3.000   0.6648   0.03123   0.02025  -0.0863   0.8494   0.9989
   3.250   0.6939   0.03152   0.02059  -0.0856   0.8252   0.9989
   3.500   0.7203   0.03193   0.02105  -0.0844   0.8010   0.9989
   3.750   0.7458   0.03230   0.02145  -0.0828   0.7778   0.9989
   4.000   0.7700   0.03284   0.02208  -0.0813   0.7528   0.9989
   4.250   0.7944   0.03320   0.02244  -0.0792   0.7306   0.9989
   4.500   0.8184   0.03379   0.02310  -0.0778   0.7048   0.9989
   4.750   0.8427   0.03424   0.02360  -0.0760   0.6814   0.9989
   5.000   0.8672   0.03472   0.02412  -0.0745   0.6568   0.9989
   5.250   0.8918   0.03527   0.02473  -0.0731   0.6315   0.9989
   5.500   0.9168   0.03561   0.02503  -0.0713   0.6087   0.9989
   5.750   0.9418   0.03622   0.02576  -0.0703   0.5821   0.9989
   6.000   0.9669   0.03675   0.02633  -0.0691   0.5567   0.9989
   6.250   0.9925   0.03709   0.02662  -0.0676   0.5330   0.9989
   6.500   1.0178   0.03775   0.02740  -0.0668   0.5062   0.9989
   6.750   1.0431   0.03836   0.02805  -0.0659   0.4802   0.9989
   7.000   1.0690   0.03882   0.02845  -0.0647   0.4561   0.9989
   7.250   1.0943   0.03954   0.02922  -0.0639   0.4299   0.9989
   7.500   1.1193   0.04046   0.03023  -0.0632   0.4039   0.9989
   7.750   1.1446   0.04134   0.03108  -0.0624   0.3798   0.9989
   8.000   1.1696   0.04235   0.03208  -0.0617   0.3552   0.9989
   8.250   1.1935   0.04379   0.03367  -0.0611   0.3313   0.9989
   8.500   1.2187   0.04488   0.03465  -0.0604   0.3094   0.9989
   8.750   1.2410   0.04677   0.03679  -0.0599   0.2873   0.9989
   9.000   1.2647   0.04830   0.03833  -0.0593   0.2672   0.9989
   9.250   1.2881   0.05012   0.04016  -0.0587   0.2489   0.9989
   9.500   1.3075   0.05257   0.04295  -0.0580   0.2314   0.9989
   9.750   1.3268   0.05505   0.04567  -0.0573   0.2157   0.9989
  10.000   1.3450   0.05778   0.04863  -0.0564   0.2019   0.9989
  10.250   1.3626   0.06057   0.05160  -0.0556   0.1894   0.9989
  10.500   1.3826   0.06316   0.05423  -0.0549   0.1776   0.9989
  10.750   1.3786   0.06853   0.06042  -0.0527   0.1704   0.9989
  11.000   1.3893   0.07192   0.06400  -0.0514   0.1614   0.9989
  11.250   1.3720   0.07798   0.07067  -0.0486   0.1576   0.9989
  11.500   1.3889   0.08084   0.07351  -0.0476   0.1490   0.9989
  11.750   1.3581   0.08751   0.08065  -0.0444   0.1485   0.9989
  12.000   1.3237   0.09434   0.08776  -0.0418   0.1489   0.9989
  12.250   1.2878   0.10120   0.09478  -0.0396   0.1498   0.9989
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