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S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il)
Reynolds number: 500,000
Max Cl/Cd: 76.51 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4094-il-500000.txt
Download as CSV file: xf-s4094-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4094 (root airfoil designed for and used on the
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5975   0.09723   0.09513   0.0094   1.0004   0.0227
  -8.500  -0.6025   0.09155   0.08948   0.0056   1.0004   0.0227
  -8.250  -0.6177   0.08289   0.08086  -0.0008   1.0004   0.0232
  -8.000  -0.6105   0.07932   0.07727  -0.0034   1.0004   0.0236
  -7.750  -0.6007   0.07524   0.07317  -0.0070   1.0004   0.0240
  -7.500  -0.5890   0.07030   0.06818  -0.0116   1.0004   0.0245
  -7.250  -0.5750   0.06446   0.06226  -0.0169   1.0004   0.0252
  -7.000  -0.5580   0.05729   0.05492  -0.0228   1.0004   0.0266
  -6.750  -0.5406   0.04192   0.03867  -0.0319   1.0004   0.0302
  -6.500  -0.5171   0.03995   0.03669  -0.0327   1.0004   0.0310
  -6.250  -0.4921   0.03786   0.03451  -0.0338   1.0004   0.0321
  -6.000  -0.4580   0.02390   0.01893  -0.0368   1.0004   0.0216
  -5.750  -0.4279   0.02146   0.01614  -0.0376   1.0004   0.0216
  -5.500  -0.3975   0.01920   0.01357  -0.0383   1.0004   0.0213
  -5.250  -0.3671   0.01750   0.01164  -0.0388   1.0004   0.0213
  -5.000  -0.3370   0.01625   0.01025  -0.0392   1.0004   0.0215
  -4.750  -0.3069   0.01526   0.00916  -0.0397   1.0004   0.0219
  -4.500  -0.2768   0.01446   0.00828  -0.0401   1.0004   0.0223
  -4.250  -0.2468   0.01379   0.00756  -0.0405   1.0004   0.0227
  -4.000  -0.2166   0.01272   0.00644  -0.0412   1.0004   0.0238
  -3.750  -0.1863   0.01217   0.00590  -0.0418   1.0004   0.0254
  -3.500  -0.1536   0.01185   0.00556  -0.0429   0.9843   0.0269
  -3.250  -0.1226   0.01176   0.00538  -0.0432   0.9325   0.0287
  -3.000  -0.0981   0.01161   0.00509  -0.0419   0.8903   0.0321
  -2.750  -0.0716   0.01141   0.00482  -0.0413   0.8570   0.0447
  -2.500  -0.0436   0.01101   0.00459  -0.0413   0.8287   0.1059
  -2.250  -0.0152   0.01080   0.00444  -0.0414   0.8034   0.1565
  -2.000   0.0136   0.01054   0.00432  -0.0417   0.7804   0.2219
  -1.750   0.0427   0.01028   0.00422  -0.0421   0.7596   0.3003
  -1.500   0.0720   0.00996   0.00416  -0.0425   0.7401   0.4014
  -1.250   0.1010   0.00953   0.00414  -0.0430   0.7223   0.5408
  -1.000   0.1286   0.00898   0.00417  -0.0430   0.7060   0.7241
  -0.750   0.1477   0.00841   0.00409  -0.0403   0.6912   0.9042
  -0.500   0.1774   0.00795   0.00358  -0.0404   0.6758   0.9996
  -0.250   0.2071   0.00805   0.00353  -0.0407   0.6614   0.9996
   0.000   0.2368   0.00814   0.00351  -0.0410   0.6473   0.9996
   0.250   0.2665   0.00824   0.00349  -0.0414   0.6337   0.9996
   0.500   0.2962   0.00833   0.00349  -0.0417   0.6204   0.9996
   0.750   0.3258   0.00843   0.00349  -0.0421   0.6071   0.9996
   1.000   0.3554   0.00854   0.00351  -0.0424   0.5940   0.9996
   1.250   0.3850   0.00865   0.00353  -0.0427   0.5807   0.9996
   1.500   0.4146   0.00876   0.00355  -0.0431   0.5671   0.9996
   1.750   0.4441   0.00888   0.00359  -0.0434   0.5532   0.9996
   2.000   0.4737   0.00899   0.00364  -0.0438   0.5388   0.9996
   2.250   0.5032   0.00911   0.00369  -0.0441   0.5240   0.9996
   2.500   0.5326   0.00924   0.00375  -0.0444   0.5084   0.9996
   2.750   0.5621   0.00937   0.00383  -0.0448   0.4920   0.9996
   3.000   0.5915   0.00951   0.00391  -0.0451   0.4744   0.9996
   3.250   0.6208   0.00967   0.00400  -0.0455   0.4561   0.9996
   3.500   0.6501   0.00986   0.00411  -0.0458   0.4375   0.9996
   3.750   0.6793   0.01006   0.00423  -0.0462   0.4188   0.9996
   4.000   0.7085   0.01026   0.00437  -0.0466   0.3998   0.9996
   4.250   0.7376   0.01048   0.00452  -0.0469   0.3807   0.9996
   4.500   0.7666   0.01072   0.00470  -0.0473   0.3622   0.9996
   4.750   0.7956   0.01097   0.00488  -0.0477   0.3436   0.9996
   5.000   0.8245   0.01122   0.00507  -0.0480   0.3251   0.9996
   5.250   0.8533   0.01149   0.00529  -0.0484   0.3067   0.9996
   5.500   0.8821   0.01177   0.00552  -0.0488   0.2895   0.9996
   5.750   0.9108   0.01208   0.00576  -0.0491   0.2720   0.9996
   6.000   0.9394   0.01237   0.00602  -0.0495   0.2553   0.9996
   6.250   0.9679   0.01269   0.00630  -0.0498   0.2385   0.9996
   6.500   0.9963   0.01303   0.00659  -0.0502   0.2218   0.9996
   6.750   1.0245   0.01339   0.00690  -0.0505   0.2053   0.9996
   7.000   1.0526   0.01378   0.00725  -0.0508   0.1890   0.9996
   7.250   1.0806   0.01418   0.00760  -0.0511   0.1743   0.9996
   7.500   1.1084   0.01459   0.00798  -0.0514   0.1604   0.9996
   7.750   1.1361   0.01503   0.00839  -0.0517   0.1461   0.9996
   8.000   1.1635   0.01548   0.00881  -0.0520   0.1315   0.9996
   8.250   1.1907   0.01596   0.00924  -0.0522   0.1179   0.9996
   8.500   1.2177   0.01647   0.00972  -0.0525   0.1053   0.9996
   8.750   1.2444   0.01698   0.01022  -0.0527   0.0936   0.9996
   9.000   1.2711   0.01749   0.01072  -0.0528   0.0833   0.9996
   9.250   1.2973   0.01804   0.01126  -0.0530   0.0733   0.9996
   9.500   1.3232   0.01862   0.01183  -0.0531   0.0641   0.9996
   9.750   1.3486   0.01926   0.01246  -0.0531   0.0560   0.9996
  10.000   1.3737   0.01991   0.01311  -0.0531   0.0485   0.9996
  10.250   1.3986   0.02053   0.01376  -0.0531   0.0415   0.9996
  10.500   1.4222   0.02136   0.01456  -0.0529   0.0322   0.9996
  10.750   1.4427   0.02266   0.01577  -0.0525   0.0190   0.9996
  11.000   1.4623   0.02400   0.01713  -0.0518   0.0138   0.9996
  11.250   1.4823   0.02512   0.01837  -0.0511   0.0121   0.9996
  11.500   1.5013   0.02625   0.01959  -0.0504   0.0110   0.9996
  11.750   1.5154   0.02785   0.02130  -0.0491   0.0100   0.9996
  12.000   1.5308   0.02910   0.02268  -0.0479   0.0095   0.9996
  12.250   1.5438   0.03046   0.02418  -0.0464   0.0092   0.9996
  12.500   1.5531   0.03200   0.02585  -0.0445   0.0088   0.9996
  12.750   1.5583   0.03373   0.02771  -0.0423   0.0086   0.9996
  13.000   1.5543   0.03575   0.02987  -0.0390   0.0084   0.9996
  13.250   1.5475   0.03840   0.03266  -0.0366   0.0083   0.9996
  13.500   1.5417   0.04165   0.03607  -0.0357   0.0081   0.9996
  13.750   1.5353   0.04553   0.04010  -0.0359   0.0080   0.9996
  14.000   1.5274   0.04996   0.04469  -0.0368   0.0079   0.9996
  14.250   1.5176   0.05493   0.04981  -0.0382   0.0078   0.9996
  14.500   1.5057   0.06035   0.05538  -0.0399   0.0078   0.9996
  14.750   1.4919   0.06615   0.06133  -0.0419   0.0077   0.9996
  15.000   1.4770   0.07221   0.06754  -0.0440   0.0077   0.9996
  15.250   1.4610   0.07850   0.07396  -0.0462   0.0077   0.9996
  15.500   1.4446   0.08496   0.08056  -0.0485   0.0076   0.9996
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