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S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il)
Reynolds number: 500,000
Max Cl/Cd: 67.2 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4095-il-500000.txt
Download as CSV file: xf-s4095-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5108   0.11565   0.11358   0.0167   1.0007   0.0205
  -9.250  -0.5098   0.11176   0.10971   0.0157   1.0007   0.0209
  -9.000  -0.6470   0.10880   0.10669   0.0237   1.0007   0.0199
  -8.750  -0.6433   0.10582   0.10372   0.0235   1.0007   0.0201
  -8.500  -0.6419   0.10246   0.10037   0.0227   1.0007   0.0202
  -8.250  -0.6437   0.09873   0.09666   0.0214   1.0007   0.0204
  -8.000  -0.6409   0.09428   0.09222   0.0179   1.0007   0.0208
  -7.750  -0.6352   0.08897   0.08690   0.0128   1.0007   0.0213
  -7.500  -0.6267   0.07224   0.07004  -0.0064   1.0007   0.0230
  -7.250  -0.6117   0.07007   0.06783  -0.0073   1.0007   0.0233
  -7.000  -0.5866   0.05407   0.05134  -0.0206   1.0007   0.0262
  -6.750  -0.5660   0.05311   0.05041  -0.0211   1.0007   0.0265
  -6.500  -0.5428   0.05100   0.04823  -0.0226   1.0007   0.0272
  -6.250  -0.5062   0.03960   0.03565  -0.0301   1.0007   0.0330
  -6.000  -0.4683   0.02719   0.02200  -0.0337   1.0007   0.0228
  -5.750  -0.4342   0.02225   0.01637  -0.0351   1.0007   0.0197
  -5.500  -0.4032   0.02046   0.01431  -0.0358   1.0007   0.0198
  -5.250  -0.3726   0.01885   0.01252  -0.0364   1.0007   0.0200
  -5.000  -0.3426   0.01762   0.01126  -0.0370   1.0007   0.0204
  -4.750  -0.3125   0.01677   0.01036  -0.0376   1.0007   0.0209
  -4.500  -0.2824   0.01604   0.00960  -0.0381   1.0007   0.0214
  -4.250  -0.2522   0.01545   0.00896  -0.0386   1.0007   0.0222
  -4.000  -0.2218   0.01483   0.00831  -0.0392   1.0007   0.0232
  -3.750  -0.1915   0.01425   0.00777  -0.0398   1.0007   0.0241
  -3.500  -0.1609   0.01380   0.00731  -0.0404   1.0007   0.0253
  -3.250  -0.1303   0.01336   0.00688  -0.0410   1.0007   0.0269
  -3.000  -0.0997   0.01302   0.00656  -0.0417   1.0007   0.0295
  -2.750  -0.0689   0.01268   0.00627  -0.0423   1.0007   0.0349
  -2.500  -0.0354   0.01249   0.00633  -0.0437   0.9717   0.0814
  -2.250  -0.0088   0.01258   0.00651  -0.0431   0.9123   0.1254
  -1.750   0.0431   0.01240   0.00644  -0.0419   0.8326   0.2381
  -1.500   0.0715   0.01214   0.00640  -0.0422   0.8020   0.3419
  -1.250   0.1004   0.01172   0.00643  -0.0427   0.7743   0.5032
  -1.000   0.1269   0.01106   0.00660  -0.0425   0.7500   0.7677
  -0.750   0.1470   0.01005   0.00594  -0.0399   0.7279   0.9993
  -0.500   0.1767   0.01014   0.00586  -0.0402   0.7063   0.9993
  -0.250   0.2065   0.01023   0.00580  -0.0406   0.6864   0.9993
   0.000   0.2362   0.01033   0.00575  -0.0410   0.6677   0.9993
   0.250   0.2660   0.01042   0.00571  -0.0414   0.6497   0.9993
   0.500   0.2957   0.01053   0.00568  -0.0418   0.6325   0.9993
   0.750   0.3255   0.01063   0.00567  -0.0422   0.6154   0.9993
   1.000   0.3553   0.01072   0.00567  -0.0426   0.5990   0.9993
   1.250   0.3850   0.01082   0.00567  -0.0430   0.5830   0.9993
   1.500   0.4147   0.01093   0.00569  -0.0434   0.5669   0.9993
   2.000   0.4741   0.01116   0.00575  -0.0442   0.5335   0.9993
   2.250   0.5038   0.01128   0.00580  -0.0447   0.5166   0.9993
   2.500   0.5334   0.01141   0.00585  -0.0451   0.4991   0.9993
   2.750   0.5629   0.01155   0.00591  -0.0455   0.4808   0.9993
   3.000   0.5925   0.01170   0.00598  -0.0460   0.4621   0.9993
   3.250   0.6220   0.01187   0.00607  -0.0464   0.4431   0.9993
   3.500   0.6514   0.01205   0.00617  -0.0468   0.4241   0.9993
   3.750   0.6808   0.01224   0.00628  -0.0473   0.4051   0.9993
   4.000   0.7102   0.01244   0.00641  -0.0477   0.3860   0.9993
   4.250   0.7395   0.01265   0.00656  -0.0482   0.3672   0.9993
   4.500   0.7688   0.01287   0.00671  -0.0486   0.3485   0.9993
   4.750   0.7980   0.01310   0.00688  -0.0491   0.3300   0.9993
   5.000   0.8271   0.01334   0.00707  -0.0495   0.3119   0.9993
   5.250   0.8562   0.01360   0.00727  -0.0500   0.2941   0.9993
   5.500   0.8852   0.01387   0.00748  -0.0504   0.2768   0.9993
   5.750   0.9142   0.01415   0.00771  -0.0509   0.2597   0.9993
   6.000   0.9430   0.01444   0.00796  -0.0513   0.2431   0.9993
   6.250   0.9718   0.01475   0.00822  -0.0518   0.2267   0.9993
   6.500   1.0005   0.01508   0.00851  -0.0522   0.2107   0.9993
   6.750   1.0291   0.01542   0.00881  -0.0526   0.1947   0.9993
   7.000   1.0575   0.01579   0.00913  -0.0531   0.1795   0.9993
   7.250   1.0859   0.01617   0.00948  -0.0535   0.1653   0.9993
   7.500   1.1141   0.01658   0.00985  -0.0539   0.1519   0.9993
   8.000   1.1700   0.01745   0.01065  -0.0547   0.1245   0.9993
   8.250   1.1977   0.01793   0.01109  -0.0551   0.1112   0.9993
   8.500   1.2253   0.01843   0.01156  -0.0554   0.1001   0.9993
   8.750   1.2527   0.01892   0.01205  -0.0558   0.0892   0.9993
   9.000   1.2798   0.01948   0.01257  -0.0561   0.0790   0.9993
   9.250   1.3067   0.02003   0.01311  -0.0564   0.0689   0.9993
   9.500   1.3334   0.02061   0.01368  -0.0567   0.0601   0.9993
   9.750   1.3597   0.02123   0.01430  -0.0570   0.0527   0.9993
  10.000   1.3859   0.02183   0.01493  -0.0572   0.0454   0.9993
  10.250   1.4116   0.02253   0.01562  -0.0573   0.0372   0.9993
  10.500   1.4358   0.02354   0.01657  -0.0574   0.0245   0.9993
  10.750   1.4581   0.02495   0.01793  -0.0573   0.0145   0.9993
  11.000   1.4809   0.02611   0.01916  -0.0571   0.0119   0.9993
  11.250   1.5025   0.02738   0.02051  -0.0568   0.0106   0.9993
  11.500   1.5239   0.02851   0.02177  -0.0565   0.0098   0.9993
  11.750   1.5432   0.02987   0.02324  -0.0559   0.0092   0.9993
  12.000   1.5583   0.03168   0.02517  -0.0550   0.0088   0.9993
  12.250   1.5744   0.03312   0.02677  -0.0540   0.0085   0.9993
  12.500   1.5878   0.03472   0.02851  -0.0528   0.0082   0.9993
  12.750   1.5979   0.03648   0.03041  -0.0513   0.0079   0.9993
  13.000   1.6037   0.03846   0.03252  -0.0494   0.0077   0.9993
  13.250   1.6011   0.04083   0.03503  -0.0465   0.0075   0.9993
  13.500   1.5865   0.04414   0.03848  -0.0432   0.0074   0.9993
  13.750   1.5750   0.04835   0.04285  -0.0425   0.0073   0.9993
  14.000   1.5635   0.05340   0.04806  -0.0434   0.0072   0.9993
  14.250   1.5508   0.05912   0.05394  -0.0451   0.0072   0.9993
  14.500   1.5365   0.06530   0.06027  -0.0472   0.0071   0.9993
  14.750   1.5211   0.07175   0.06687  -0.0495   0.0071   0.9993
  15.000   1.5050   0.07834   0.07361  -0.0519   0.0071   0.9993
  15.250   1.4882   0.08508   0.08050  -0.0543   0.0071   0.9993
  15.500   1.4713   0.09191   0.08745  -0.0569   0.0071   0.9993
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