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NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-206 (naca63206-il)
Reynolds number: 50,000
Max Cl/Cd: 24.23 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca63206-il-50000.txt
Download as CSV file: xf-naca63206-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-206                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5540   0.09594   0.08931   0.0090   1.0000   0.2794
  -7.500  -0.5629   0.09395   0.08745   0.0084   1.0000   0.2955
  -7.250  -0.5497   0.09001   0.08353   0.0104   1.0000   0.3215
  -7.000  -0.5441   0.08687   0.08045   0.0121   1.0000   0.3487
  -6.750  -0.5275   0.08292   0.07652   0.0146   1.0000   0.3803
  -6.500  -0.5234   0.08037   0.07404   0.0171   1.0000   0.4159
  -6.250  -0.5106   0.07718   0.07088   0.0202   1.0000   0.4565
  -6.000  -0.4862   0.07299   0.06667   0.0230   1.0000   0.5014
  -5.750  -0.4749   0.07037   0.06407   0.0266   1.0000   0.5512
  -5.000  -0.4560   0.04602   0.03857  -0.0338   1.0000   0.2001
  -4.750  -0.4183   0.03989   0.03149  -0.0375   1.0000   0.1415
  -4.500  -0.3863   0.03598   0.02666  -0.0383   1.0000   0.1191
  -4.250  -0.3591   0.03256   0.02278  -0.0382   1.0000   0.1130
  -4.000  -0.3321   0.02995   0.01970  -0.0378   1.0000   0.1156
  -3.750  -0.3041   0.02742   0.01672  -0.0371   1.0000   0.1144
  -3.500  -0.2764   0.02518   0.01400  -0.0360   1.0000   0.1137
  -3.250  -0.2498   0.02329   0.01188  -0.0345   1.0000   0.1168
  -3.000  -0.2249   0.02161   0.01008  -0.0328   1.0000   0.1237
  -2.750  -0.2014   0.02016   0.00865  -0.0314   1.0000   0.1486
  -2.500  -0.1776   0.01842   0.00712  -0.0304   1.0000   0.1849
  -2.250  -0.1312   0.01450   0.00602  -0.0261   1.0000   1.0000
  -2.000  -0.1189   0.01430   0.00544  -0.0241   1.0000   1.0000
  -1.750  -0.1027   0.01416   0.00488  -0.0228   1.0000   1.0000
  -1.500  -0.0834   0.01408   0.00448  -0.0219   1.0000   1.0000
  -1.250  -0.0626   0.01404   0.00417  -0.0212   1.0000   1.0000
  -1.000  -0.0410   0.01404   0.00393  -0.0206   1.0000   1.0000
  -0.750  -0.0189   0.01406   0.00376  -0.0202   1.0000   1.0000
  -0.500   0.0032   0.01412   0.00365  -0.0197   1.0000   1.0000
  -0.250   0.0255   0.01421   0.00356  -0.0192   1.0000   1.0000
   0.000   0.0478   0.01433   0.00357  -0.0188   1.0000   1.0000
   0.250   0.0699   0.01449   0.00363  -0.0184   1.0000   1.0000
   0.500   0.0919   0.01467   0.00376  -0.0181   1.0000   1.0000
   0.750   0.1136   0.01488   0.00394  -0.0177   1.0000   1.0000
   1.000   0.1352   0.01513   0.00419  -0.0174   1.0000   1.0000
   1.250   0.1564   0.01542   0.00451  -0.0171   1.0000   1.0000
   1.500   0.1773   0.01575   0.00487  -0.0168   1.0000   1.0000
   1.750   0.1979   0.01612   0.00530  -0.0165   1.0000   1.0000
   2.000   0.2182   0.01655   0.00580  -0.0163   1.0000   1.0000
   2.250   0.2382   0.01702   0.00638  -0.0162   1.0000   1.0000
   2.500   0.2577   0.01755   0.00704  -0.0161   1.0000   1.0000
   2.750   0.2768   0.01814   0.00787  -0.0160   1.0000   1.0000
   3.000   0.2954   0.01880   0.00870  -0.0161   1.0000   1.0000
   3.250   0.3136   0.01953   0.00963  -0.0162   1.0000   1.0000
   3.500   0.3313   0.02034   0.01067  -0.0164   1.0000   1.0000
   3.750   0.3484   0.02125   0.01183  -0.0166   1.0000   1.0000
   4.000   0.5438   0.02244   0.01083  -0.0240   0.1400   1.0000
   4.250   0.5708   0.02460   0.01287  -0.0228   0.1230   1.0000
   4.500   0.6028   0.02674   0.01520  -0.0218   0.1147   1.0000
   4.750   0.6328   0.02934   0.01792  -0.0211   0.1066   1.0000
   5.000   0.6606   0.03184   0.02068  -0.0204   0.0986   1.0000
   5.250   0.6893   0.03488   0.02433  -0.0194   0.1002   1.0000
   5.500   0.7159   0.03849   0.02868  -0.0184   0.1049   1.0000
   5.750   0.7413   0.04235   0.03308  -0.0174   0.1115   1.0000
   6.000   0.7648   0.04686   0.03850  -0.0166   0.1265   1.0000
   6.250   0.7864   0.05259   0.04515  -0.0170   0.1545   1.0000
   6.500   0.8045   0.06285   0.05667  -0.0252   0.2455   1.0000
   6.750   0.7233   0.06121   0.05569  -0.0304   0.2745   1.0000
   7.000   0.6519   0.07422   0.06859  -0.0487   0.3911   1.0000
   8.000   0.7327   0.09996   0.09370  -0.0639   0.3979   1.0000
   8.250   0.7589   0.10548   0.09927  -0.0625   0.3766   1.0000
   8.750   0.7599   0.11232   0.10611  -0.0614   0.3348   1.0000
   9.000   0.7586   0.11550   0.10924  -0.0614   0.3147   1.0000
   9.250   0.7718   0.12019   0.11394  -0.0603   0.2947   1.0000
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