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S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=200,000 Ncrit=9


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: 48.99 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4096-il-200000.txt
Download as CSV file: xf-s4096-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6728   0.09628   0.09295   0.0001   1.0011   0.0564
  -8.250  -0.6714   0.08958   0.08621  -0.0057   1.0011   0.0583
  -8.000  -0.6792   0.07379   0.06956  -0.0230   1.0011   0.0638
  -7.750  -0.6613   0.06941   0.06539  -0.0228   1.0011   0.0651
  -7.500  -0.6424   0.06691   0.06295  -0.0228   1.0011   0.0669
  -7.250  -0.6216   0.06340   0.05931  -0.0246   1.0011   0.0713
  -7.000  -0.5992   0.05673   0.05216  -0.0291   1.0011   0.0789
  -6.750  -0.5571   0.03851   0.03175  -0.0335   1.0011   0.0422
  -6.500  -0.5268   0.03529   0.02827  -0.0344   1.0011   0.0402
  -6.250  -0.4962   0.03183   0.02441  -0.0354   1.0011   0.0393
  -6.000  -0.4654   0.02963   0.02186  -0.0360   1.0011   0.0397
  -5.750  -0.4347   0.02808   0.02002  -0.0366   1.0011   0.0406
  -5.500  -0.4041   0.02636   0.01808  -0.0371   1.0011   0.0409
  -5.250  -0.3738   0.02500   0.01655  -0.0376   1.0011   0.0413
  -5.000  -0.3441   0.02317   0.01468  -0.0381   1.0011   0.0424
  -4.750  -0.3144   0.02201   0.01357  -0.0387   1.0011   0.0443
  -4.500  -0.2844   0.02128   0.01284  -0.0393   1.0011   0.0475
  -4.250  -0.2541   0.02070   0.01220  -0.0399   1.0011   0.0513
  -4.000  -0.2236   0.01979   0.01136  -0.0408   1.0011   0.0576
  -3.750  -0.1926   0.01906   0.01067  -0.0416   1.0011   0.0757
  -3.500  -0.1621   0.01760   0.01028  -0.0432   1.0011   0.2704
  -3.250  -0.1323   0.01714   0.01022  -0.0441   1.0011   0.3763
  -3.000  -0.1029   0.01673   0.01024  -0.0449   1.0011   0.4771
  -2.750  -0.0748   0.01628   0.01038  -0.0452   1.0011   0.6104
  -2.500  -0.0530   0.01581   0.01064  -0.0434   1.0011   0.7853
  -2.250  -0.0315   0.01477   0.00994  -0.0408   1.0011   0.9989
  -2.000  -0.0010   0.01496   0.00999  -0.0418   1.0011   0.9989
  -1.750   0.0291   0.01524   0.01016  -0.0429   1.0011   0.9989
  -1.500   0.0584   0.01570   0.01054  -0.0438   1.0011   0.9989
  -1.250   0.0954   0.01595   0.01068  -0.0465   0.9945   0.9989
  -1.000   0.1394   0.01561   0.01023  -0.0504   0.9747   0.9989
  -0.750   0.1792   0.01540   0.00991  -0.0532   0.9482   0.9989
  -0.500   0.2112   0.01536   0.00974  -0.0539   0.9176   0.9989
  -0.250   0.2378   0.01543   0.00967  -0.0532   0.8878   0.9989
   0.000   0.2640   0.01553   0.00963  -0.0525   0.8614   0.9989
   0.250   0.2907   0.01565   0.00959  -0.0520   0.8380   0.9989
   0.500   0.3186   0.01578   0.00958  -0.0519   0.8156   0.9989
   0.750   0.3467   0.01591   0.00957  -0.0519   0.7952   0.9989
   1.000   0.3751   0.01605   0.00958  -0.0519   0.7764   0.9989
   1.250   0.4041   0.01619   0.00960  -0.0522   0.7576   0.9989
   1.500   0.4332   0.01633   0.00964  -0.0525   0.7394   0.9989
   1.750   0.4623   0.01647   0.00969  -0.0528   0.7218   0.9989
   2.000   0.4915   0.01663   0.00975  -0.0531   0.7046   0.9989
   2.250   0.5207   0.01678   0.00981  -0.0535   0.6878   0.9989
   2.500   0.5500   0.01694   0.00989  -0.0539   0.6710   0.9989
   2.750   0.5792   0.01711   0.00998  -0.0543   0.6542   0.9989
   3.000   0.6086   0.01727   0.01008  -0.0547   0.6369   0.9989
   3.250   0.6380   0.01743   0.01020  -0.0552   0.6190   0.9989
   3.500   0.6673   0.01760   0.01032  -0.0556   0.6008   0.9989
   3.750   0.6966   0.01778   0.01044  -0.0561   0.5824   0.9989
   4.000   0.7257   0.01798   0.01058  -0.0565   0.5639   0.9989
   4.250   0.7550   0.01817   0.01074  -0.0570   0.5438   0.9989
   4.500   0.7842   0.01836   0.01090  -0.0574   0.5230   0.9989
   4.750   0.8132   0.01860   0.01107  -0.0579   0.5025   0.9989
   5.000   0.8423   0.01882   0.01127  -0.0584   0.4794   0.9989
   5.250   0.8711   0.01911   0.01147  -0.0588   0.4573   0.9989
   5.500   0.9000   0.01939   0.01173  -0.0593   0.4331   0.9989
   5.750   0.9286   0.01973   0.01200  -0.0598   0.4098   0.9989
   6.000   0.9571   0.02010   0.01231  -0.0603   0.3859   0.9989
   6.250   0.9855   0.02050   0.01267  -0.0608   0.3626   0.9989
   6.500   1.0136   0.02095   0.01304  -0.0612   0.3397   0.9989
   6.750   1.0418   0.02139   0.01346  -0.0617   0.3168   0.9989
   7.000   1.0695   0.02190   0.01389  -0.0622   0.2950   0.9989
   7.250   1.0974   0.02240   0.01439  -0.0626   0.2729   0.9989
   7.500   1.1248   0.02297   0.01490  -0.0630   0.2520   0.9989
   7.750   1.1521   0.02354   0.01545  -0.0635   0.2313   0.9989
   8.000   1.1791   0.02416   0.01605  -0.0638   0.2115   0.9989
   8.250   1.2055   0.02487   0.01670  -0.0642   0.1932   0.9989
   8.500   1.2319   0.02557   0.01740  -0.0645   0.1757   0.9989
   8.750   1.2579   0.02632   0.01815  -0.0647   0.1593   0.9989
   9.000   1.2834   0.02713   0.01899  -0.0649   0.1444   0.9989
   9.250   1.3084   0.02801   0.01988  -0.0649   0.1305   0.9989
   9.500   1.3326   0.02898   0.02085  -0.0649   0.1180   0.9989
   9.750   1.3560   0.03005   0.02192  -0.0648   0.1068   0.9989
  10.000   1.3785   0.03115   0.02300  -0.0646   0.0961   0.9989
  10.250   1.4016   0.03203   0.02395  -0.0646   0.0856   0.9989
  10.500   1.4248   0.03285   0.02488  -0.0645   0.0761   0.9989
  10.750   1.4454   0.03404   0.02613  -0.0640   0.0686   0.9989
  11.000   1.4638   0.03540   0.02749  -0.0633   0.0616   0.9989
  11.250   1.4842   0.03645   0.02873  -0.0627   0.0552   0.9989
  11.500   1.4989   0.03812   0.03046  -0.0615   0.0490   0.9989
  11.750   1.5129   0.03967   0.03209  -0.0603   0.0422   0.9989
  12.000   1.5235   0.04153   0.03410  -0.0585   0.0357   0.9989
  12.250   1.5245   0.04415   0.03679  -0.0555   0.0314   0.9989
  12.500   1.5258   0.04639   0.03918  -0.0525   0.0284   0.9989
  12.750   1.5136   0.04942   0.04231  -0.0480   0.0271   0.9989
  13.000   1.4982   0.05351   0.04647  -0.0444   0.0259   0.9989
  13.250   1.4940   0.05687   0.05008  -0.0426   0.0248   0.9989
  13.500   1.4887   0.06061   0.05402  -0.0413   0.0237   0.9989
  13.750   1.4832   0.06456   0.05813  -0.0406   0.0228   0.9989
  14.000   1.4775   0.06869   0.06240  -0.0403   0.0221   0.9989
  14.250   1.4713   0.07298   0.06680  -0.0403   0.0215   0.9989
  14.500   1.4640   0.07746   0.07138  -0.0403   0.0210   0.9989
  14.750   1.4551   0.08216   0.07621  -0.0399   0.0205   0.9989
  15.000   1.4462   0.08714   0.08138  -0.0404   0.0202   0.9989
  15.250   1.4370   0.09236   0.08683  -0.0416   0.0199   0.9989
  15.500   1.4266   0.09789   0.09259  -0.0432   0.0197   0.9989
  15.750   1.4151   0.10376   0.09868  -0.0453   0.0195   0.9989
  16.000   1.4026   0.11002   0.10516  -0.0479   0.0192   0.9989
  16.250   1.3897   0.11673   0.11208  -0.0510   0.0191   0.9989
  16.500   1.3760   0.12390   0.11948  -0.0549   0.0189   0.9989
  16.750   1.3610   0.13167   0.12746  -0.0593   0.0189   0.9989
  17.000   1.3447   0.14014   0.13615  -0.0646   0.0188   0.9989
  17.250   1.3263   0.14959   0.14582  -0.0708   0.0189   0.9989
  17.500   1.3053   0.16034   0.15680  -0.0782   0.0191   0.9989
  17.750   1.2805   0.17293   0.16959  -0.0871   0.0194   0.9989
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