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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=5


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: 57.21 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4096-il-500000-n5.txt
Download as CSV file: xf-s4096-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7263   0.12709   0.12484   0.0236   1.0011   0.0096
 -11.000  -0.9352   0.06398   0.06143  -0.0117   1.0011   0.0092
 -10.750  -0.9549   0.05308   0.04993  -0.0166   1.0011   0.0093
 -10.500  -0.9534   0.04559   0.04184  -0.0189   1.0011   0.0094
 -10.250  -0.9362   0.04184   0.03778  -0.0202   1.0011   0.0096
 -10.000  -0.9140   0.03940   0.03509  -0.0212   1.0011   0.0097
  -9.750  -0.8899   0.03736   0.03284  -0.0221   1.0011   0.0099
  -9.500  -0.8647   0.03546   0.03071  -0.0230   1.0011   0.0101
  -9.250  -0.8384   0.03373   0.02878  -0.0239   1.0011   0.0104
  -9.000  -0.8114   0.03223   0.02708  -0.0247   1.0011   0.0107
  -8.750  -0.7839   0.03082   0.02547  -0.0255   1.0011   0.0110
  -8.500  -0.7558   0.02934   0.02377  -0.0263   1.0011   0.0114
  -8.250  -0.7274   0.02786   0.02205  -0.0271   1.0011   0.0117
  -8.000  -0.6987   0.02657   0.02056  -0.0278   1.0011   0.0120
  -7.750  -0.6696   0.02547   0.01929  -0.0285   1.0011   0.0122
  -7.500  -0.6404   0.02455   0.01822  -0.0292   1.0011   0.0124
  -7.250  -0.6110   0.02373   0.01727  -0.0298   1.0011   0.0126
  -7.000  -0.5816   0.02284   0.01627  -0.0305   1.0011   0.0128
  -6.750  -0.5524   0.02167   0.01502  -0.0313   1.0011   0.0132
  -6.500  -0.5228   0.02092   0.01423  -0.0321   1.0011   0.0136
  -6.250  -0.4931   0.02035   0.01363  -0.0328   1.0011   0.0140
  -6.000  -0.4632   0.01985   0.01309  -0.0336   1.0011   0.0146
  -5.750  -0.4332   0.01933   0.01253  -0.0343   1.0011   0.0150
  -5.500  -0.4030   0.01884   0.01201  -0.0351   1.0011   0.0154
  -5.250  -0.3728   0.01841   0.01153  -0.0358   1.0011   0.0158
  -5.000  -0.3424   0.01803   0.01111  -0.0366   1.0011   0.0162
  -4.750  -0.3121   0.01769   0.01075  -0.0374   1.0011   0.0166
  -4.500  -0.2816   0.01736   0.01040  -0.0381   1.0011   0.0171
  -4.250  -0.2511   0.01702   0.01004  -0.0390   1.0011   0.0179
  -4.000  -0.2189   0.01699   0.00998  -0.0401   0.9866   0.0190
  -3.750  -0.1859   0.01697   0.00993  -0.0414   0.9464   0.0205
  -3.500  -0.1586   0.01700   0.00984  -0.0410   0.9057   0.0219
  -3.250  -0.1316   0.01696   0.00969  -0.0407   0.8712   0.0251
  -3.000  -0.1033   0.01683   0.00954  -0.0408   0.8419   0.0424
  -2.750  -0.0742   0.01664   0.00941  -0.0412   0.8157   0.0816
  -2.500  -0.0447   0.01645   0.00931  -0.0418   0.7921   0.1311
  -2.250  -0.0149   0.01621   0.00926  -0.0426   0.7700   0.2058
  -2.000   0.0150   0.01605   0.00923  -0.0434   0.7492   0.2707
  -1.750   0.0450   0.01594   0.00920  -0.0441   0.7302   0.3240
  -1.500   0.0752   0.01577   0.00921  -0.0450   0.7119   0.3959
  -1.250   0.1054   0.01556   0.00927  -0.0459   0.6947   0.4942
  -0.750   0.1647   0.01517   0.00951  -0.0472   0.6628   0.7089
  -0.500   0.1919   0.01499   0.00965  -0.0470   0.6482   0.8149
  -0.250   0.2121   0.01459   0.00949  -0.0447   0.6347   0.9423
   0.000   0.2434   0.01411   0.00892  -0.0455   0.6204   0.9989
   0.250   0.2739   0.01417   0.00889  -0.0463   0.6066   0.9989
   0.500   0.3043   0.01425   0.00886  -0.0470   0.5927   0.9989
   0.750   0.3348   0.01432   0.00884  -0.0478   0.5791   0.9989
   1.000   0.3651   0.01440   0.00883  -0.0485   0.5652   0.9989
   1.500   0.4258   0.01456   0.00883  -0.0500   0.5362   0.9989
   1.750   0.4561   0.01465   0.00884  -0.0507   0.5214   0.9989
   2.000   0.4864   0.01475   0.00886  -0.0515   0.5057   0.9989
   2.250   0.5166   0.01486   0.00890  -0.0522   0.4883   0.9989
   2.500   0.5467   0.01497   0.00893  -0.0529   0.4705   0.9989
   2.750   0.5768   0.01510   0.00898  -0.0537   0.4516   0.9989
   3.250   0.6367   0.01541   0.00911  -0.0551   0.4127   0.9989
   3.500   0.6666   0.01558   0.00920  -0.0558   0.3927   0.9989
   3.750   0.6964   0.01577   0.00931  -0.0566   0.3736   0.9989
   4.000   0.7262   0.01595   0.00942  -0.0573   0.3554   0.9989
   4.250   0.7560   0.01615   0.00954  -0.0580   0.3367   0.9989
   4.500   0.7856   0.01636   0.00968  -0.0587   0.3182   0.9989
   4.750   0.8152   0.01660   0.00984  -0.0594   0.2998   0.9989
   5.000   0.8447   0.01683   0.01001  -0.0601   0.2820   0.9989
   5.250   0.8741   0.01707   0.01019  -0.0608   0.2643   0.9989
   5.500   0.9034   0.01734   0.01040  -0.0615   0.2468   0.9989
   5.750   0.9327   0.01760   0.01061  -0.0621   0.2313   0.9989
   6.000   0.9619   0.01789   0.01085  -0.0628   0.2154   0.9989
   6.250   0.9909   0.01820   0.01111  -0.0635   0.1997   0.9989
   6.500   1.0199   0.01852   0.01138  -0.0641   0.1850   0.9989
   7.000   1.0773   0.01924   0.01198  -0.0653   0.1535   0.9989
   7.250   1.1058   0.01962   0.01232  -0.0659   0.1393   0.9989
   7.500   1.1343   0.01999   0.01266  -0.0665   0.1278   0.9989
   7.750   1.1625   0.02039   0.01303  -0.0671   0.1159   0.9989
   8.000   1.1905   0.02083   0.01342  -0.0676   0.1033   0.9989
   8.250   1.2183   0.02130   0.01386  -0.0681   0.0909   0.9989
   8.500   1.2459   0.02179   0.01431  -0.0686   0.0792   0.9989
   8.750   1.2734   0.02226   0.01477  -0.0691   0.0704   0.9989
   9.000   1.3007   0.02277   0.01526  -0.0695   0.0623   0.9989
   9.250   1.3275   0.02335   0.01581  -0.0699   0.0534   0.9989
   9.500   1.3540   0.02393   0.01638  -0.0702   0.0457   0.9989
   9.750   1.3805   0.02449   0.01695  -0.0705   0.0395   0.9989
  10.000   1.4064   0.02514   0.01759  -0.0708   0.0334   0.9989
  10.250   1.4320   0.02581   0.01826  -0.0710   0.0285   0.9989
  10.500   1.4575   0.02644   0.01894  -0.0712   0.0246   0.9989
  10.750   1.4822   0.02718   0.01969  -0.0713   0.0205   0.9989
  11.000   1.5061   0.02802   0.02054  -0.0713   0.0153   0.9989
  11.250   1.5286   0.02902   0.02154  -0.0711   0.0102   0.9989
  11.500   1.5505   0.03006   0.02262  -0.0708   0.0078   0.9989
  11.750   1.5721   0.03105   0.02369  -0.0704   0.0067   0.9989
  12.000   1.5930   0.03205   0.02479  -0.0700   0.0060   0.9989
  12.250   1.6124   0.03318   0.02600  -0.0693   0.0055   0.9989
  12.500   1.6301   0.03443   0.02736  -0.0684   0.0052   0.9989
  12.750   1.6475   0.03560   0.02864  -0.0674   0.0050   0.9989
  13.000   1.6628   0.03689   0.03006  -0.0662   0.0048   0.9989
  13.250   1.6754   0.03834   0.03163  -0.0646   0.0046   0.9989
  13.500   1.6843   0.03997   0.03342  -0.0625   0.0045   0.9989
  13.750   1.6868   0.04191   0.03549  -0.0595   0.0044   0.9989
  14.000   1.6755   0.04458   0.03830  -0.0546   0.0043   0.9989
  14.250   1.6680   0.04761   0.04149  -0.0515   0.0042   0.9989
  14.500   1.6615   0.05105   0.04509  -0.0496   0.0042   0.9989
  14.750   1.6548   0.05494   0.04914  -0.0486   0.0041   0.9989
  15.000   1.6468   0.05933   0.05369  -0.0482   0.0040   0.9989
  15.250   1.6373   0.06422   0.05874  -0.0485   0.0040   0.9989
  15.500   1.6259   0.06965   0.06433  -0.0494   0.0040   0.9989
  15.750   1.6122   0.07561   0.07046  -0.0506   0.0039   0.9989
  16.000   1.5963   0.08207   0.07710  -0.0524   0.0039   0.9989
  16.250   1.5781   0.08902   0.08421  -0.0544   0.0039   0.9989
  16.500   1.5584   0.09640   0.09176  -0.0569   0.0039   0.9989
  16.750   1.5378   0.10417   0.09970  -0.0599   0.0038   0.9989
  17.000   1.5170   0.11229   0.10799  -0.0632   0.0038   0.9989
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