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Dormoy (dormoy-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Dormoy (dormoy-il)
Reynolds number: 200,000
Max Cl/Cd: 50.67 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dormoy-il-200000-n5.txt
Download as CSV file: xf-dormoy-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Dormoy                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3701   0.08845   0.08522  -0.0328   1.0000   0.0134
  -9.250  -0.3708   0.08520   0.08203  -0.0340   1.0000   0.0134
  -9.000  -0.3741   0.08210   0.07900  -0.0348   1.0000   0.0134
  -8.750  -0.3792   0.07891   0.07588  -0.0359   1.0000   0.0134
  -5.250  -0.0904   0.02170   0.01517  -0.0688   0.8784   0.0122
  -5.000  -0.0612   0.01949   0.01256  -0.0686   0.8660   0.0112
  -4.750  -0.0321   0.01788   0.01058  -0.0682   0.8532   0.0106
  -4.500  -0.0038   0.01655   0.00897  -0.0677   0.8402   0.0101
  -4.250   0.0236   0.01543   0.00764  -0.0671   0.8286   0.0102
  -4.000   0.0502   0.01473   0.00678  -0.0664   0.8166   0.0121
  -3.750   0.0758   0.01402   0.00594  -0.0656   0.8048   0.0130
  -3.500   0.1005   0.01332   0.00516  -0.0647   0.7931   0.0135
  -3.250   0.1245   0.01254   0.00421  -0.0638   0.7817   0.0147
  -3.000   0.1495   0.01207   0.00354  -0.0631   0.7688   0.0192
  -2.750   0.1751   0.01180   0.00304  -0.0623   0.7548   0.0225
  -2.500   0.1982   0.01108   0.00272  -0.0614   0.7408   0.1700
  -2.250   0.2167   0.00996   0.00258  -0.0601   0.7257   0.4510
  -2.000   0.2329   0.00910   0.00254  -0.0575   0.7107   0.6940
  -1.750   0.2951   0.00868   0.00248  -0.0638   0.6855   0.9544
  -1.500   0.3327   0.00878   0.00229  -0.0658   0.6483   0.9783
  -1.250   0.3676   0.00899   0.00212  -0.0674   0.5921   0.9939
  -1.000   0.3957   0.00917   0.00205  -0.0676   0.5580   1.0000
  -0.750   0.4175   0.00938   0.00204  -0.0665   0.5241   1.0000
  -0.500   0.4380   0.00968   0.00205  -0.0652   0.4752   1.0000
  -0.250   0.4566   0.01015   0.00213  -0.0636   0.4035   1.0000
   0.000   0.4757   0.01066   0.00227  -0.0621   0.3485   1.0000
   0.250   0.4973   0.01098   0.00241  -0.0611   0.3217   1.0000
   0.500   0.5194   0.01128   0.00256  -0.0602   0.2980   1.0000
   0.750   0.5418   0.01157   0.00273  -0.0594   0.2714   1.0000
   1.000   0.5625   0.01203   0.00289  -0.0583   0.2050   1.0000
   1.250   0.5828   0.01257   0.00316  -0.0572   0.1703   1.0000
   1.500   0.6057   0.01287   0.00343  -0.0565   0.1613   1.0000
   1.750   0.6296   0.01308   0.00367  -0.0559   0.1558   1.0000
   2.000   0.6532   0.01334   0.00393  -0.0553   0.1496   1.0000
   2.250   0.6771   0.01357   0.00419  -0.0548   0.1435   1.0000
   2.500   0.7007   0.01383   0.00451  -0.0542   0.1321   1.0000
   3.000   0.7412   0.01516   0.00556  -0.0520   0.0449   1.0000
   3.250   0.7638   0.01557   0.00586  -0.0512   0.0170   1.0000
   3.500   0.7862   0.01604   0.00651  -0.0503   0.0128   1.0000
   3.750   0.8082   0.01658   0.00724  -0.0492   0.0112   1.0000
   4.000   0.8295   0.01724   0.00809  -0.0480   0.0102   1.0000
   4.250   0.8485   0.01813   0.00921  -0.0466   0.0089   1.0000
   4.500   0.8597   0.01969   0.01100  -0.0441   0.0077   1.0000
   4.750   0.8766   0.02062   0.01205  -0.0424   0.0072   1.0000
   5.000   0.8907   0.02181   0.01338  -0.0403   0.0071   1.0000
   5.250   0.9044   0.02319   0.01485  -0.0381   0.0070   1.0000
   5.500   0.9191   0.02465   0.01639  -0.0362   0.0070   1.0000
   5.750   0.9358   0.02644   0.01827  -0.0345   0.0069   1.0000
   6.000   0.9556   0.02837   0.02030  -0.0334   0.0070   1.0000
   6.250   0.9788   0.03100   0.02305  -0.0327   0.0072   1.0000
   6.500   1.0001   0.03323   0.02550  -0.0317   0.0070   1.0000
   6.750   1.0192   0.03563   0.02815  -0.0304   0.0070   1.0000
   7.000   1.0347   0.03672   0.02951  -0.0287   0.0057   1.0000
   7.250   1.0492   0.03943   0.03251  -0.0269   0.0057   1.0000
   7.500   1.0599   0.04294   0.03643  -0.0247   0.0062   1.0000
   7.750   1.0646   0.04651   0.04030  -0.0224   0.0067   1.0000
  12.750   0.8517   0.15279   0.14943  -0.0474   0.0141   1.0000
  14.250   0.8639   0.18830   0.18483  -0.0643   0.0138   1.0000
  15.250   0.6947   0.18431   0.18137  -0.0612   0.0141   1.0000
  15.500   0.6954   0.18915   0.18618  -0.0632   0.0139   1.0000
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