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S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il)
Reynolds number: 200,000
Max Cl/Cd: 53.48 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4095-il-200000-n5.txt
Download as CSV file: xf-s4095-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4095 (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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4845   0.11218   0.10891   0.0109   1.0007   0.0244
  -9.250  -0.4864   0.10760   0.10435   0.0098   1.0007   0.0230
  -8.750  -0.6365   0.10368   0.10030   0.0189   1.0007   0.0196
  -8.500  -0.6389   0.09953   0.09618   0.0175   1.0007   0.0193
  -8.250  -0.6405   0.09462   0.09129   0.0144   1.0007   0.0191
  -8.000  -0.6379   0.08883   0.08551   0.0094   1.0007   0.0188
  -7.750  -0.6314   0.08208   0.07872   0.0029   1.0007   0.0185
  -7.500  -0.6201   0.07377   0.07032  -0.0052   1.0007   0.0185
  -7.250  -0.6026   0.06318   0.05950  -0.0146   1.0007   0.0188
  -7.000  -0.5798   0.05200   0.04788  -0.0224   1.0007   0.0187
  -6.750  -0.5524   0.04198   0.03717  -0.0283   1.0007   0.0182
  -6.500  -0.5212   0.03485   0.02921  -0.0321   1.0007   0.0180
  -6.250  -0.4897   0.03054   0.02423  -0.0341   1.0007   0.0181
  -6.000  -0.4585   0.02763   0.02081  -0.0355   1.0007   0.0184
  -5.750  -0.4275   0.02546   0.01821  -0.0364   1.0007   0.0188
  -5.500  -0.3969   0.02376   0.01621  -0.0372   1.0007   0.0192
  -5.250  -0.3666   0.02246   0.01466  -0.0378   1.0007   0.0197
  -5.000  -0.3367   0.02109   0.01319  -0.0385   1.0007   0.0208
  -4.750  -0.3069   0.02018   0.01223  -0.0391   1.0007   0.0219
  -4.500  -0.2769   0.01926   0.01123  -0.0397   1.0007   0.0225
  -4.250  -0.2468   0.01844   0.01035  -0.0403   1.0007   0.0233
  -4.000  -0.2166   0.01773   0.00958  -0.0408   1.0007   0.0242
  -3.750  -0.1863   0.01713   0.00891  -0.0414   1.0007   0.0254
  -3.500  -0.1559   0.01656   0.00829  -0.0420   1.0007   0.0270
  -3.250  -0.1256   0.01608   0.00782  -0.0426   1.0007   0.0300
  -3.000  -0.0953   0.01565   0.00743  -0.0433   1.0007   0.0373
  -2.750  -0.0648   0.01519   0.00707  -0.0440   1.0007   0.0577
  -2.500  -0.0301   0.01518   0.00717  -0.0456   0.9527   0.0924
  -2.250   0.0012   0.01513   0.00722  -0.0463   0.9035   0.1350
  -2.000   0.0278   0.01499   0.00723  -0.0458   0.8632   0.1967
  -1.750   0.0542   0.01471   0.00720  -0.0455   0.8296   0.2887
  -1.500   0.0811   0.01444   0.00716  -0.0452   0.8002   0.3868
  -1.250   0.1082   0.01406   0.00715  -0.0451   0.7738   0.5217
  -0.750   0.1518   0.01217   0.00623  -0.0409   0.7284   0.9993
  -0.500   0.1808   0.01231   0.00614  -0.0410   0.7073   0.9993
  -0.250   0.2101   0.01244   0.00607  -0.0412   0.6873   0.9993
   0.000   0.2394   0.01257   0.00603  -0.0415   0.6681   0.9993
   0.250   0.2687   0.01271   0.00600  -0.0417   0.6499   0.9993
   0.500   0.2981   0.01286   0.00598  -0.0420   0.6323   0.9993
   0.750   0.3276   0.01300   0.00598  -0.0423   0.6151   0.9993
   1.000   0.3570   0.01314   0.00600  -0.0427   0.5980   0.9993
   1.250   0.3865   0.01329   0.00602  -0.0430   0.5810   0.9993
   1.500   0.4159   0.01344   0.00607  -0.0434   0.5640   0.9993
   1.750   0.4453   0.01360   0.00612  -0.0437   0.5470   0.9993
   2.000   0.4747   0.01377   0.00619  -0.0441   0.5301   0.9993
   2.250   0.5041   0.01394   0.00626  -0.0444   0.5127   0.9993
   2.500   0.5335   0.01411   0.00636  -0.0448   0.4947   0.9993
   2.750   0.5628   0.01430   0.00647  -0.0452   0.4763   0.9993
   3.000   0.5921   0.01450   0.00658  -0.0456   0.4578   0.9993
   3.250   0.6213   0.01471   0.00672  -0.0460   0.4394   0.9993
   3.500   0.6505   0.01493   0.00688  -0.0464   0.4200   0.9993
   3.750   0.6797   0.01517   0.00705  -0.0468   0.4012   0.9993
   4.000   0.7087   0.01544   0.00723  -0.0472   0.3827   0.9993
   4.250   0.7378   0.01570   0.00744  -0.0476   0.3645   0.9993
   4.500   0.7667   0.01597   0.00768  -0.0480   0.3462   0.9993
   4.750   0.7956   0.01627   0.00793  -0.0484   0.3283   0.9993
   5.000   0.8244   0.01659   0.00819  -0.0488   0.3107   0.9993
   5.250   0.8532   0.01691   0.00850  -0.0492   0.2935   0.9993
   5.500   0.8819   0.01725   0.00881  -0.0496   0.2762   0.9993
   5.750   0.9105   0.01761   0.00914  -0.0500   0.2594   0.9993
   6.000   0.9390   0.01798   0.00949  -0.0504   0.2432   0.9993
   6.250   0.9673   0.01839   0.00989  -0.0508   0.2272   0.9993
   6.500   0.9956   0.01880   0.01030  -0.0512   0.2124   0.9993
   6.750   1.0237   0.01924   0.01073  -0.0516   0.1977   0.9993
   7.000   1.0516   0.01970   0.01119  -0.0520   0.1833   0.9993
   7.250   1.0794   0.02019   0.01170  -0.0524   0.1696   0.9993
   7.500   1.1070   0.02070   0.01222  -0.0527   0.1560   0.9993
   7.750   1.1345   0.02123   0.01277  -0.0530   0.1431   0.9993
   8.000   1.1617   0.02179   0.01335  -0.0534   0.1310   0.9993
   8.250   1.1887   0.02238   0.01399  -0.0536   0.1199   0.9993
   8.500   1.2154   0.02301   0.01466  -0.0539   0.1095   0.9993
   8.750   1.2416   0.02371   0.01537  -0.0541   0.0997   0.9993
   9.000   1.2677   0.02438   0.01611  -0.0544   0.0896   0.9993
   9.250   1.2934   0.02510   0.01687  -0.0545   0.0794   0.9993
   9.500   1.3186   0.02587   0.01769  -0.0547   0.0691   0.9993
   9.750   1.3433   0.02671   0.01855  -0.0548   0.0600   0.9993
  10.000   1.3672   0.02762   0.01949  -0.0549   0.0519   0.9993
  10.250   1.3910   0.02850   0.02044  -0.0548   0.0444   0.9993
  10.500   1.4140   0.02945   0.02149  -0.0547   0.0383   0.9993
  10.750   1.4357   0.03056   0.02269  -0.0545   0.0318   0.9993
  11.000   1.4558   0.03186   0.02404  -0.0541   0.0247   0.9993
  11.250   1.4738   0.03337   0.02561  -0.0535   0.0185   0.9993
  11.750   1.5043   0.03668   0.02919  -0.0517   0.0128   0.9993
  12.000   1.5156   0.03854   0.03120  -0.0504   0.0116   0.9993
  12.250   1.5222   0.04071   0.03353  -0.0487   0.0109   0.9993
  12.500   1.5261   0.04291   0.03597  -0.0467   0.0104   0.9993
  12.750   1.5214   0.04550   0.03876  -0.0440   0.0101   0.9993
  13.000   1.5103   0.04883   0.04229  -0.0415   0.0098   0.9993
  13.250   1.5005   0.05290   0.04657  -0.0410   0.0097   0.9993
  13.500   1.4905   0.05767   0.05155  -0.0418   0.0095   0.9993
  13.750   1.4792   0.06310   0.05718  -0.0434   0.0093   0.9993
  14.000   1.4660   0.06912   0.06341  -0.0456   0.0092   0.9993
  14.250   1.4507   0.07569   0.07018  -0.0482   0.0092   0.9993
  14.500   1.4336   0.08273   0.07741  -0.0511   0.0091   0.9993
  14.750   1.4148   0.09018   0.08504  -0.0543   0.0091   0.9993
  15.000   1.3949   0.09801   0.09304  -0.0578   0.0091   0.9993
  15.250   1.3747   0.10603   0.10123  -0.0614   0.0091   0.9993
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