Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il)
Reynolds number: 200,000
Max Cl/Cd: 48.29 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4096-il-200000-n5.txt
Download as CSV file: xf-s4096-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.7035   0.10396   0.10053   0.0075   1.0011   0.0179
  -9.500  -0.7713   0.07419   0.07055  -0.0129   1.0011   0.0167
  -9.250  -0.7861   0.06224   0.05802  -0.0191   1.0011   0.0168
  -9.000  -0.7818   0.05390   0.04903  -0.0224   1.0011   0.0170
  -8.750  -0.7657   0.04812   0.04272  -0.0244   1.0011   0.0171
  -8.500  -0.7441   0.04361   0.03773  -0.0260   1.0011   0.0173
  -8.250  -0.7194   0.04020   0.03391  -0.0274   1.0011   0.0175
  -8.000  -0.6929   0.03742   0.03078  -0.0285   1.0011   0.0178
  -7.750  -0.6653   0.03505   0.02808  -0.0295   1.0011   0.0182
  -7.500  -0.6370   0.03298   0.02571  -0.0304   1.0011   0.0185
  -7.250  -0.6083   0.03127   0.02374  -0.0312   1.0011   0.0191
  -7.000  -0.5793   0.02987   0.02211  -0.0319   1.0011   0.0200
  -6.750  -0.5499   0.02844   0.02044  -0.0326   1.0011   0.0208
  -6.500  -0.5204   0.02707   0.01886  -0.0332   1.0011   0.0212
  -6.250  -0.4910   0.02587   0.01749  -0.0338   1.0011   0.0215
  -6.000  -0.4614   0.02484   0.01634  -0.0344   1.0011   0.0219
  -5.750  -0.4322   0.02364   0.01511  -0.0351   1.0011   0.0225
  -5.500  -0.4026   0.02276   0.01420  -0.0358   1.0011   0.0232
  -5.250  -0.3729   0.02206   0.01346  -0.0365   1.0011   0.0241
  -5.000  -0.3430   0.02147   0.01283  -0.0373   1.0011   0.0254
  -4.750  -0.3130   0.02096   0.01228  -0.0380   1.0011   0.0272
  -4.500  -0.2828   0.02042   0.01169  -0.0387   1.0011   0.0288
  -4.250  -0.2526   0.01994   0.01119  -0.0395   1.0011   0.0309
  -4.000  -0.2223   0.01956   0.01077  -0.0403   1.0011   0.0341
  -3.750  -0.1920   0.01916   0.01040  -0.0410   1.0011   0.0419
  -3.500  -0.1617   0.01869   0.01009  -0.0419   1.0011   0.0726
  -3.250  -0.1316   0.01818   0.00990  -0.0430   1.0011   0.1391
  -3.000  -0.1016   0.01769   0.00983  -0.0441   1.0011   0.2278
  -2.750  -0.0716   0.01737   0.00983  -0.0451   1.0011   0.3069
  -2.500  -0.0388   0.01728   0.01005  -0.0467   0.9884   0.3918
  -2.250  -0.0035   0.01691   0.01021  -0.0489   0.9578   0.5191
  -2.000   0.0284   0.01661   0.01036  -0.0497   0.9258   0.6400
  -1.750   0.0535   0.01637   0.01046  -0.0486   0.8943   0.7497
  -1.500   0.0714   0.01603   0.01036  -0.0451   0.8659   0.8780
  -1.250   0.1006   0.01518   0.00942  -0.0449   0.8368   0.9989
  -1.000   0.1292   0.01526   0.00930  -0.0449   0.8123   0.9989
  -0.750   0.1580   0.01535   0.00919  -0.0451   0.7902   0.9989
  -0.500   0.1871   0.01544   0.00911  -0.0454   0.7691   0.9989
  -0.250   0.2164   0.01554   0.00904  -0.0458   0.7495   0.9989
   0.000   0.2459   0.01565   0.00898  -0.0462   0.7312   0.9989
   0.250   0.2756   0.01576   0.00895  -0.0467   0.7134   0.9989
   0.500   0.3053   0.01587   0.00893  -0.0472   0.6962   0.9989
   0.750   0.3350   0.01598   0.00892  -0.0477   0.6796   0.9989
   1.000   0.3648   0.01610   0.00893  -0.0483   0.6636   0.9989
   1.250   0.3946   0.01623   0.00895  -0.0489   0.6479   0.9989
   1.500   0.4244   0.01636   0.00898  -0.0494   0.6324   0.9989
   1.750   0.4542   0.01649   0.00903  -0.0500   0.6169   0.9989
   2.000   0.4840   0.01663   0.00908  -0.0506   0.6013   0.9989
   2.250   0.5138   0.01678   0.00916  -0.0512   0.5856   0.9989
   2.500   0.5435   0.01694   0.00924  -0.0518   0.5696   0.9989
   2.750   0.5732   0.01710   0.00933  -0.0524   0.5535   0.9989
   3.000   0.6028   0.01727   0.00944  -0.0530   0.5367   0.9989
   3.250   0.6325   0.01744   0.00956  -0.0536   0.5191   0.9989
   3.500   0.6621   0.01762   0.00968  -0.0542   0.5005   0.9989
   3.750   0.6916   0.01782   0.00984  -0.0548   0.4811   0.9989
   4.000   0.7210   0.01805   0.00999  -0.0554   0.4612   0.9989
   4.250   0.7504   0.01828   0.01016  -0.0560   0.4402   0.9989
   4.500   0.7796   0.01855   0.01036  -0.0565   0.4188   0.9989
   4.750   0.8088   0.01883   0.01059  -0.0571   0.3981   0.9989
   5.000   0.8378   0.01913   0.01083  -0.0577   0.3773   0.9989
   5.250   0.8668   0.01947   0.01109  -0.0583   0.3567   0.9989
   5.500   0.8957   0.01979   0.01140  -0.0589   0.3362   0.9989
   5.750   0.9244   0.02016   0.01171  -0.0595   0.3158   0.9989
   6.000   0.9531   0.02054   0.01204  -0.0601   0.2964   0.9989
   6.250   0.9816   0.02093   0.01240  -0.0606   0.2766   0.9989
   6.500   1.0099   0.02136   0.01280  -0.0612   0.2579   0.9989
   6.750   1.0381   0.02181   0.01321  -0.0617   0.2402   0.9989
   7.000   1.0663   0.02226   0.01364  -0.0623   0.2227   0.9989
   7.250   1.0942   0.02274   0.01412  -0.0628   0.2053   0.9989
   7.500   1.1218   0.02325   0.01461  -0.0633   0.1888   0.9989
   7.750   1.1492   0.02380   0.01514  -0.0637   0.1725   0.9989
   8.000   1.1764   0.02439   0.01571  -0.0642   0.1570   0.9989
   8.250   1.2032   0.02499   0.01632  -0.0646   0.1425   0.9989
   8.500   1.2299   0.02561   0.01694  -0.0649   0.1295   0.9989
   8.750   1.2564   0.02624   0.01761  -0.0652   0.1180   0.9989
   9.000   1.2825   0.02691   0.01832  -0.0655   0.1073   0.9989
   9.250   1.3082   0.02763   0.01909  -0.0657   0.0973   0.9989
   9.500   1.3332   0.02843   0.01991  -0.0659   0.0880   0.9989
   9.750   1.3579   0.02923   0.02075  -0.0660   0.0787   0.9989
  10.000   1.3822   0.03005   0.02161  -0.0660   0.0693   0.9989
  10.250   1.4057   0.03094   0.02253  -0.0660   0.0603   0.9989
  10.500   1.4283   0.03192   0.02353  -0.0659   0.0525   0.9989
  10.750   1.4504   0.03290   0.02456  -0.0657   0.0456   0.9989
  11.000   1.4721   0.03388   0.02564  -0.0654   0.0407   0.9989
  11.250   1.4918   0.03506   0.02688  -0.0648   0.0358   0.9989
  11.500   1.5116   0.03615   0.02809  -0.0643   0.0310   0.9989
  11.750   1.5286   0.03751   0.02952  -0.0634   0.0263   0.9989
  12.000   1.5431   0.03906   0.03115  -0.0622   0.0218   0.9989
  12.250   1.5560   0.04064   0.03287  -0.0608   0.0181   0.9989
  12.500   1.5643   0.04257   0.03491  -0.0588   0.0157   0.9989
  12.750   1.5689   0.04464   0.03714  -0.0563   0.0140   0.9989
  13.000   1.5628   0.04720   0.03984  -0.0524   0.0131   0.9989
  13.250   1.5527   0.05030   0.04310  -0.0487   0.0125   0.9989
  13.500   1.5452   0.05371   0.04671  -0.0464   0.0120   0.9989
  13.750   1.5374   0.05758   0.05078  -0.0450   0.0115   0.9989
  14.000   1.5291   0.06189   0.05528  -0.0445   0.0111   0.9989
  14.250   1.5196   0.06668   0.06025  -0.0446   0.0108   0.9989
  14.500   1.5087   0.07194   0.06570  -0.0453   0.0105   0.9989
  14.750   1.4961   0.07768   0.07163  -0.0465   0.0103   0.9989
  15.000   1.4814   0.08391   0.07805  -0.0482   0.0101   0.9989
  15.250   1.4653   0.09056   0.08488  -0.0503   0.0100   0.9989
  15.500   1.4480   0.09761   0.09211  -0.0528   0.0099   0.9989
  15.750   1.4302   0.10495   0.09963  -0.0558   0.0099   0.9989
<< Back to S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il)

Polar data table (+)

Polar graphs


<< Back to S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il)