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S6063 7.05% (s6063-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S6063 7.05% (s6063-il)
Reynolds number: 1,000,000
Max Cl/Cd: 81.25 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s6063-il-1000000.txt
Download as CSV file: xf-s6063-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6063 7.05%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -5.250  -0.3965   0.00655   0.00299  -0.0380   0.9919   0.0129
  -5.000  -0.3661   0.00541   0.00167  -0.0392   0.9867   0.0140
  -4.750  -0.3364   0.00448   0.00054  -0.0399   0.9804   0.0153
  -4.500  -0.3048   0.00495   0.00096  -0.0401   0.9713   0.0172
  -4.000  -0.2637   0.01004   0.00505  -0.0393   0.9732   0.0088
  -3.750  -0.2358   0.00910   0.00396  -0.0391   0.9642   0.0084
  -3.500  -0.2093   0.00850   0.00327  -0.0386   0.9548   0.0089
  -3.250  -0.1840   0.00809   0.00278  -0.0379   0.9442   0.0098
  -3.000  -0.1584   0.00776   0.00238  -0.0372   0.9333   0.0105
  -2.750  -0.1325   0.00751   0.00205  -0.0366   0.9226   0.0110
  -2.500  -0.1064   0.00727   0.00172  -0.0361   0.9119   0.0119
  -2.250  -0.0800   0.00708   0.00144  -0.0355   0.9011   0.0137
  -2.000  -0.0534   0.00674   0.00120  -0.0351   0.8896   0.0474
  -1.750  -0.0277   0.00615   0.00102  -0.0349   0.8780   0.1720
  -1.500  -0.0017   0.00569   0.00091  -0.0347   0.8660   0.2869
  -1.250   0.0240   0.00520   0.00082  -0.0345   0.8534   0.4244
  -1.000   0.0493   0.00467   0.00078  -0.0342   0.8403   0.5858
  -0.750   0.0744   0.00430   0.00076  -0.0336   0.8267   0.7090
  -0.500   0.0995   0.00408   0.00075  -0.0328   0.8123   0.7943
  -0.250   0.1245   0.00395   0.00075  -0.0320   0.7970   0.8507
   0.000   0.1487   0.00388   0.00075  -0.0308   0.7804   0.9006
   0.250   0.1732   0.00386   0.00075  -0.0297   0.7625   0.9431
   0.500   0.2056   0.00389   0.00073  -0.0305   0.7423   0.9728
   1.000   0.2788   0.00404   0.00069  -0.0343   0.6944   1.0000
   1.250   0.3046   0.00415   0.00071  -0.0339   0.6690   1.0000
   1.500   0.3306   0.00429   0.00074  -0.0335   0.6401   1.0000
   1.750   0.3567   0.00445   0.00077  -0.0331   0.6073   1.0000
   2.000   0.3824   0.00471   0.00083  -0.0327   0.5537   1.0000
   2.250   0.4079   0.00504   0.00091  -0.0323   0.4897   1.0000
   2.500   0.4339   0.00534   0.00101  -0.0321   0.4373   1.0000
   2.750   0.4597   0.00569   0.00113  -0.0318   0.3755   1.0000
   3.000   0.4844   0.00629   0.00131  -0.0315   0.2778   1.0000
   3.250   0.5095   0.00683   0.00152  -0.0313   0.1989   1.0000
   3.500   0.5336   0.00762   0.00185  -0.0310   0.0947   1.0000
   3.750   0.5579   0.00843   0.00227  -0.0306   0.0160   1.0000
   4.000   0.5848   0.00871   0.00257  -0.0303   0.0126   1.0000
   4.250   0.6115   0.00903   0.00298  -0.0300   0.0116   1.0000
   4.500   0.6378   0.00944   0.00346  -0.0297   0.0112   1.0000
   4.750   0.6642   0.00979   0.00387  -0.0294   0.0109   1.0000
   5.000   0.6902   0.01023   0.00436  -0.0291   0.0107   1.0000
   5.250   0.7160   0.01073   0.00493  -0.0287   0.0105   1.0000
   5.500   0.7413   0.01131   0.00558  -0.0283   0.0103   1.0000
   5.750   0.7662   0.01195   0.00631  -0.0278   0.0100   1.0000
   6.000   0.7906   0.01273   0.00716  -0.0272   0.0096   1.0000
   6.250   0.8144   0.01367   0.00819  -0.0265   0.0092   1.0000
   6.500   0.8373   0.01495   0.00958  -0.0256   0.0093   1.0000
   6.750   0.8593   0.01684   0.01164  -0.0245   0.0098   1.0000
   7.250   0.9055   0.02195   0.01730  -0.0219   0.0138   1.0000
   7.500   0.9277   0.02337   0.01884  -0.0213   0.0131   1.0000
   7.750   0.9488   0.02498   0.02057  -0.0207   0.0125   1.0000
   8.000   0.9651   0.02788   0.02367  -0.0198   0.0117   1.0000
   8.250   0.9598   0.03645   0.03295  -0.0172   0.0111   1.0000
   8.500   0.9701   0.03929   0.03609  -0.0158   0.0111   1.0000
   8.750   0.9976   0.03784   0.03475  -0.0151   0.0102   1.0000
   9.000   1.0123   0.03961   0.03671  -0.0139   0.0090   1.0000
   9.250   1.0171   0.04280   0.04014  -0.0125   0.0087   1.0000
   9.500   1.0204   0.04546   0.04298  -0.0112   0.0083   1.0000
   9.750   1.0167   0.04870   0.04641  -0.0097   0.0081   1.0000
  10.000   1.0051   0.05180   0.04967  -0.0075   0.0080   1.0000
  10.250   0.9851   0.05522   0.05324  -0.0057   0.0080   1.0000
  10.500   0.9564   0.06110   0.05931  -0.0071   0.0082   1.0000
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