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S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il)
Reynolds number: 100,000
Max Cl/Cd: 39.59 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4096-il-100000.txt
Download as CSV file: xf-s4096-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6321   0.11843   0.11366   0.0118   1.0011   0.1134
  -8.750  -0.6669   0.11226   0.10758   0.0027   1.0011   0.1168
  -8.500  -0.6709   0.10555   0.10089  -0.0013   1.0011   0.1188
  -8.250  -0.6509   0.10308   0.09843   0.0040   1.0011   0.1220
  -8.000  -0.6470   0.09840   0.09374   0.0013   1.0011   0.1271
  -7.750  -0.5469   0.08636   0.08197  -0.0109   1.0011   0.1441
  -7.500  -0.6359   0.08726   0.08251  -0.0066   1.0011   0.1383
  -7.250  -0.5464   0.07637   0.07195  -0.0132   1.0011   0.1552
  -7.000  -0.5484   0.07005   0.06553  -0.0171   1.0011   0.1649
  -6.750  -0.5921   0.07247   0.06744  -0.0165   1.0011   0.1677
  -6.500  -0.5371   0.04710   0.03967  -0.0352   1.0011   0.0784
  -6.250  -0.5050   0.04231   0.03432  -0.0365   1.0011   0.0719
  -6.000  -0.4723   0.03778   0.02913  -0.0378   1.0011   0.0680
  -5.750  -0.4395   0.03441   0.02509  -0.0386   1.0011   0.0664
  -5.500  -0.4084   0.03203   0.02240  -0.0391   1.0011   0.0670
  -5.250  -0.3782   0.03034   0.02055  -0.0397   1.0011   0.0705
  -5.000  -0.3474   0.02870   0.01868  -0.0400   1.0011   0.0736
  -4.750  -0.3167   0.02724   0.01701  -0.0402   1.0011   0.0761
  -4.500  -0.2877   0.02547   0.01541  -0.0405   1.0011   0.0814
  -4.250  -0.2580   0.02430   0.01424  -0.0409   1.0011   0.0911
  -4.000  -0.2282   0.02306   0.01319  -0.0414   1.0011   0.1144
  -3.750  -0.1991   0.02064   0.01215  -0.0425   1.0011   0.3276
  -3.500  -0.1725   0.01980   0.01202  -0.0425   1.0011   0.4851
  -3.250  -0.1498   0.01905   0.01206  -0.0409   1.0011   0.6541
  -2.750  -0.1007   0.01729   0.01093  -0.0369   1.0011   0.9989
  -2.500  -0.0705   0.01735   0.01070  -0.0380   1.0011   0.9989
  -2.250  -0.0410   0.01749   0.01062  -0.0390   1.0011   0.9989
  -2.000  -0.0120   0.01771   0.01065  -0.0398   1.0011   0.9989
  -1.750   0.0163   0.01803   0.01081  -0.0405   1.0011   0.9989
  -1.500   0.0436   0.01849   0.01116  -0.0411   1.0011   0.9989
  -1.250   0.0694   0.01917   0.01174  -0.0415   1.0011   0.9989
  -1.000   0.0933   0.02013   0.01261  -0.0418   1.0011   0.9989
  -0.750   0.1147   0.02147   0.01388  -0.0420   1.0011   0.9989
  -0.500   0.1454   0.02234   0.01466  -0.0443   0.9976   0.9989
  -0.250   0.1987   0.02166   0.01387  -0.0504   0.9869   0.9989
   0.000   0.2518   0.02090   0.01302  -0.0563   0.9750   0.9989
   0.250   0.3015   0.02028   0.01232  -0.0614   0.9599   0.9989
   0.500   0.3455   0.01986   0.01184  -0.0649   0.9405   0.9989
   0.750   0.3822   0.01970   0.01162  -0.0666   0.9176   0.9989
   1.000   0.4122   0.01976   0.01161  -0.0667   0.8939   0.9989
   1.250   0.4387   0.01993   0.01171  -0.0659   0.8707   0.9989
   1.500   0.4645   0.02015   0.01186  -0.0649   0.8487   0.9989
   1.750   0.4902   0.02038   0.01202  -0.0641   0.8271   0.9989
   2.000   0.5158   0.02062   0.01217  -0.0631   0.8074   0.9989
   2.250   0.5423   0.02087   0.01236  -0.0626   0.7868   0.9989
   2.500   0.5691   0.02111   0.01255  -0.0621   0.7667   0.9989
   2.750   0.5958   0.02136   0.01271  -0.0615   0.7476   0.9989
   3.000   0.6229   0.02161   0.01290  -0.0611   0.7282   0.9989
   3.250   0.6505   0.02186   0.01313  -0.0609   0.7076   0.9989
   3.500   0.6779   0.02210   0.01331  -0.0606   0.6878   0.9989
   3.750   0.7053   0.02236   0.01349  -0.0603   0.6686   0.9989
   4.000   0.7333   0.02262   0.01376  -0.0603   0.6468   0.9989
   4.250   0.7610   0.02287   0.01396  -0.0601   0.6262   0.9989
   4.500   0.7889   0.02314   0.01418  -0.0600   0.6050   0.9989
   4.750   0.8168   0.02340   0.01444  -0.0600   0.5826   0.9989
   5.000   0.8445   0.02368   0.01465  -0.0599   0.5610   0.9989
   5.250   0.8725   0.02396   0.01493  -0.0599   0.5373   0.9989
   5.500   0.9002   0.02426   0.01520  -0.0599   0.5143   0.9989
   5.750   0.9280   0.02457   0.01548  -0.0599   0.4901   0.9989
   6.000   0.9557   0.02492   0.01582  -0.0600   0.4653   0.9989
   6.250   0.9830   0.02532   0.01613  -0.0600   0.4414   0.9989
   6.500   1.0104   0.02578   0.01659  -0.0601   0.4157   0.9989
   6.750   1.0376   0.02631   0.01709  -0.0602   0.3904   0.9989
   7.000   1.0644   0.02692   0.01760  -0.0603   0.3666   0.9989
   7.250   1.0911   0.02756   0.01825  -0.0604   0.3415   0.9989
   7.500   1.1176   0.02828   0.01896  -0.0605   0.3177   0.9989
   7.750   1.1436   0.02905   0.01964  -0.0606   0.2951   0.9989
   8.000   1.1695   0.02989   0.02052  -0.0607   0.2722   0.9989
   8.250   1.1948   0.03078   0.02135  -0.0607   0.2513   0.9989
   8.500   1.2199   0.03177   0.02238  -0.0607   0.2306   0.9989
   8.750   1.2445   0.03278   0.02339  -0.0606   0.2111   0.9989
   9.000   1.2686   0.03391   0.02447  -0.0605   0.1938   0.9989
   9.250   1.2923   0.03519   0.02573  -0.0604   0.1775   0.9989
   9.500   1.3155   0.03651   0.02713  -0.0601   0.1623   0.9989
   9.750   1.3383   0.03795   0.02861  -0.0598   0.1487   0.9989
  10.000   1.3610   0.03952   0.03014  -0.0595   0.1367   0.9989
  10.250   1.3821   0.04098   0.03182  -0.0589   0.1253   0.9989
  10.500   1.4027   0.04285   0.03394  -0.0583   0.1154   0.9989
  10.750   1.4225   0.04476   0.03592  -0.0577   0.1063   0.9989
  11.000   1.4420   0.04656   0.03758  -0.0573   0.0969   0.9989
  11.250   1.4544   0.04786   0.03929  -0.0556   0.0878   0.9989
  11.500   1.4660   0.04986   0.04151  -0.0541   0.0794   0.9989
  11.750   1.4790   0.05196   0.04351  -0.0530   0.0718   0.9989
  12.000   1.4832   0.05424   0.04625  -0.0504   0.0651   0.9989
  12.250   1.4894   0.05715   0.04921  -0.0484   0.0595   0.9989
  12.500   1.4861   0.05998   0.05242  -0.0452   0.0549   0.9989
  12.750   1.4939   0.06312   0.05537  -0.0438   0.0505   0.9989
  13.000   1.4778   0.06674   0.05947  -0.0394   0.0491   0.9989
  13.250   1.4588   0.07085   0.06396  -0.0353   0.0480   0.9989
  13.500   1.4408   0.07548   0.06893  -0.0328   0.0469   0.9989
  13.750   1.4227   0.08057   0.07432  -0.0315   0.0461   0.9989
  14.000   1.4038   0.08616   0.08020  -0.0312   0.0455   0.9989
  14.250   1.3830   0.09241   0.08673  -0.0321   0.0450   0.9989
  14.500   1.3574   0.09984   0.09446  -0.0343   0.0450   0.9989
  14.750   1.3247   0.10909   0.10404  -0.0385   0.0456   0.9989
  15.000   1.2876   0.12019   0.11546  -0.0450   0.0467   0.9989
  15.250   1.2501   0.13277   0.12828  -0.0533   0.0480   0.9989
  15.500   1.2150   0.14634   0.14197  -0.0625   0.0494   0.9989
  15.750   1.1848   0.16034   0.15602  -0.0717   0.0504   0.9989
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