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S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il)
Reynolds number: 50,000
Max Cl/Cd: 27.68 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4095-il-50000.txt
Download as CSV file: xf-s4095-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.6145   0.11945   0.11308   0.0220   1.0007   0.2200
  -7.750  -0.5761   0.11212   0.10569   0.0265   1.0007   0.2304
  -7.500  -0.6095   0.11184   0.10552   0.0166   1.0007   0.2393
  -7.250  -0.5733   0.10461   0.09830   0.0251   1.0007   0.2490
  -7.000  -0.5825   0.10135   0.09511   0.0195   1.0007   0.2611
  -6.750  -0.5663   0.09718   0.09094   0.0215   1.0007   0.2752
  -6.500  -0.5567   0.09274   0.08653   0.0214   1.0007   0.2877
  -6.250  -0.5505   0.08881   0.08264   0.0194   1.0007   0.3056
  -6.000  -0.5408   0.08497   0.07882   0.0185   1.0007   0.3263
  -5.750  -0.5280   0.08118   0.07507   0.0199   1.0007   0.3501
  -5.500  -0.5151   0.07775   0.07166   0.0218   1.0007   0.3793
  -5.250  -0.5053   0.07424   0.06820   0.0236   1.0007   0.4156
  -5.000  -0.4952   0.07110   0.06512   0.0263   1.0007   0.4578
  -4.750  -0.4797   0.06758   0.06165   0.0303   1.0007   0.4912
  -4.500  -0.3052   0.04008   0.03038  -0.0416   1.0007   0.1273
  -4.250  -0.2695   0.03659   0.02626  -0.0434   1.0007   0.1282
  -4.000  -0.2369   0.03382   0.02321  -0.0444   1.0007   0.1337
  -3.750  -0.2031   0.03128   0.02017  -0.0451   1.0007   0.1404
  -3.500  -0.1711   0.02919   0.01781  -0.0455   1.0007   0.1551
  -3.250  -0.1416   0.02715   0.01593  -0.0456   1.0007   0.1805
  -3.000  -0.1124   0.02530   0.01429  -0.0455   1.0007   0.2336
  -2.750  -0.0832   0.02341   0.01276  -0.0453   1.0007   0.3234
  -2.500  -0.0583   0.02082   0.01151  -0.0441   1.0007   0.5139
  -2.250  -0.0402   0.01768   0.00961  -0.0391   1.0007   0.9993
  -2.000  -0.0098   0.01773   0.00909  -0.0398   1.0007   0.9993
  -1.750   0.0194   0.01782   0.00878  -0.0405   1.0007   0.9993
  -1.500   0.0479   0.01797   0.00864  -0.0410   1.0007   0.9993
  -1.250   0.0756   0.01819   0.00863  -0.0415   1.0007   0.9993
  -1.000   0.1023   0.01852   0.00876  -0.0420   1.0007   0.9993
  -0.750   0.1273   0.01901   0.00911  -0.0424   1.0007   0.9993
  -0.500   0.1502   0.01972   0.00970  -0.0426   1.0007   0.9993
  -0.250   0.1713   0.02068   0.01056  -0.0428   1.0007   0.9993
   0.000   0.1912   0.02186   0.01164  -0.0433   1.0007   0.9993
   0.250   0.2106   0.02321   0.01290  -0.0440   1.0007   0.9993
   0.500   0.2293   0.02469   0.01431  -0.0449   1.0007   0.9993
   0.750   0.2742   0.02533   0.01486  -0.0504   0.9904   0.9993
   1.000   0.3441   0.02491   0.01436  -0.0597   0.9691   0.9993
   1.250   0.4138   0.02432   0.01373  -0.0685   0.9474   0.9993
   1.500   0.4741   0.02391   0.01331  -0.0748   0.9232   0.9993
   1.750   0.5191   0.02392   0.01331  -0.0776   0.8957   0.9993
   2.000   0.5506   0.02431   0.01370  -0.0775   0.8661   0.9993
   2.250   0.5769   0.02487   0.01423  -0.0764   0.8373   0.9993
   2.500   0.6012   0.02544   0.01477  -0.0746   0.8105   0.9993
   2.750   0.6244   0.02602   0.01530  -0.0724   0.7852   0.9993
   3.000   0.6480   0.02669   0.01601  -0.0710   0.7578   0.9993
   3.250   0.6716   0.02731   0.01662  -0.0693   0.7321   0.9993
   3.500   0.6952   0.02791   0.01721  -0.0676   0.7072   0.9993
   3.750   0.7191   0.02851   0.01778  -0.0659   0.6831   0.9993
   4.000   0.7432   0.02910   0.01834  -0.0642   0.6594   0.9993
   4.250   0.7676   0.02969   0.01894  -0.0626   0.6360   0.9993
   4.500   0.7927   0.03035   0.01962  -0.0615   0.6116   0.9993
   4.750   0.8183   0.03107   0.02039  -0.0607   0.5864   0.9993
   5.000   0.8438   0.03175   0.02111  -0.0598   0.5619   0.9993
   5.250   0.8693   0.03241   0.02184  -0.0588   0.5381   0.9993
   5.500   0.8949   0.03306   0.02250  -0.0577   0.5148   0.9993
   5.750   0.9205   0.03370   0.02314  -0.0567   0.4921   0.9993
   6.000   0.9462   0.03435   0.02380  -0.0556   0.4698   0.9993
   6.250   0.9720   0.03511   0.02456  -0.0548   0.4475   0.9993
   6.500   0.9979   0.03615   0.02577  -0.0545   0.4235   0.9993
   6.750   1.0235   0.03715   0.02686  -0.0539   0.4007   0.9993
   7.000   1.0490   0.03817   0.02798  -0.0533   0.3789   0.9993
   7.250   1.0744   0.03924   0.02911  -0.0526   0.3578   0.9993
   7.500   1.0996   0.04041   0.03032  -0.0520   0.3374   0.9993
   7.750   1.1246   0.04169   0.03169  -0.0514   0.3179   0.9993
   8.000   1.1492   0.04313   0.03320  -0.0509   0.2990   0.9993
   8.250   1.1734   0.04475   0.03492  -0.0504   0.2810   0.9993
   8.500   1.1968   0.04657   0.03690  -0.0499   0.2638   0.9993
   8.750   1.2190   0.04864   0.03919  -0.0495   0.2475   0.9993
   9.000   1.2394   0.05110   0.04193  -0.0491   0.2325   0.9993
   9.250   1.2567   0.05413   0.04536  -0.0487   0.2188   0.9993
   9.500   1.2696   0.05789   0.04956  -0.0482   0.2071   0.9993
   9.750   1.2840   0.06119   0.05312  -0.0475   0.1964   0.9993
  10.000   1.3035   0.06356   0.05554  -0.0466   0.1855   0.9993
  10.250   1.2870   0.07103   0.06378  -0.0461   0.1812   0.9993
  10.500   0.9446   0.13957   0.13204  -0.0892   0.3243   0.9993
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