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S6063 7.05% (s6063-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S6063 7.05% (s6063-il)
Reynolds number: 500,000
Max Cl/Cd: 74.79 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s6063-il-500000.txt
Download as CSV file: xf-s6063-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.5221   0.05473   0.05230  -0.0322   1.0000   0.0172
  -6.750  -0.5246   0.04598   0.04326  -0.0354   1.0000   0.0176
  -6.500  -0.5169   0.04126   0.03841  -0.0365   1.0000   0.0185
  -6.250  -0.5002   0.03967   0.03679  -0.0367   1.0000   0.0196
  -6.000  -0.4825   0.03730   0.03427  -0.0369   1.0000   0.0215
  -5.750  -0.4589   0.03528   0.03194  -0.0363   1.0000   0.0249
  -5.500  -0.4378   0.03427   0.03056  -0.0353   1.0000   0.0255
  -5.250  -0.4331   0.02688   0.02284  -0.0348   1.0000   0.0277
  -5.000  -0.4163   0.02529   0.02118  -0.0335   1.0000   0.0291
  -4.750  -0.4000   0.02377   0.01950  -0.0319   1.0000   0.0314
  -4.500  -0.3787   0.02475   0.02028  -0.0297   0.9999   0.0359
  -4.250  -0.3447   0.01627   0.01077  -0.0298   0.9972   0.0179
  -4.000  -0.3102   0.01343   0.00769  -0.0309   0.9947   0.0145
  -3.750  -0.2761   0.01174   0.00578  -0.0318   0.9910   0.0135
  -3.500  -0.2402   0.01069   0.00463  -0.0335   0.9873   0.0141
  -3.250  -0.2024   0.00995   0.00381  -0.0355   0.9844   0.0153
  -3.000  -0.1672   0.00943   0.00323  -0.0371   0.9797   0.0166
  -2.750  -0.1318   0.00893   0.00262  -0.0386   0.9746   0.0187
  -2.500  -0.0965   0.00854   0.00219  -0.0400   0.9695   0.0256
  -2.250  -0.0676   0.00759   0.00187  -0.0406   0.9607   0.1805
  -2.000  -0.0397   0.00698   0.00172  -0.0408   0.9514   0.3135
  -1.750  -0.0154   0.00619   0.00164  -0.0404   0.9411   0.5118
  -1.500   0.0072   0.00567   0.00158  -0.0391   0.9299   0.6583
  -1.250   0.0271   0.00521   0.00160  -0.0369   0.9178   0.7983
  -1.000   0.0478   0.00502   0.00160  -0.0347   0.9057   0.8755
  -0.750   0.0717   0.00494   0.00157  -0.0331   0.8939   0.9272
  -0.500   0.1062   0.00491   0.00148  -0.0341   0.8828   0.9640
  -0.250   0.1465   0.00488   0.00139  -0.0366   0.8713   0.9862
   0.000   0.1874   0.00487   0.00129  -0.0393   0.8584   1.0000
   0.250   0.2112   0.00490   0.00124  -0.0383   0.8423   1.0000
   0.500   0.2355   0.00494   0.00121  -0.0375   0.8255   1.0000
   0.750   0.2601   0.00499   0.00118  -0.0367   0.8074   1.0000
   1.000   0.2852   0.00506   0.00116  -0.0359   0.7886   1.0000
   1.250   0.3107   0.00514   0.00117  -0.0353   0.7677   1.0000
   1.500   0.3363   0.00523   0.00118  -0.0347   0.7456   1.0000
   1.750   0.3621   0.00534   0.00120  -0.0342   0.7212   1.0000
   2.000   0.3880   0.00547   0.00124  -0.0337   0.6937   1.0000
   2.250   0.4139   0.00562   0.00129  -0.0332   0.6628   1.0000
   2.500   0.4390   0.00587   0.00136  -0.0325   0.6126   1.0000
   2.750   0.4637   0.00621   0.00144  -0.0319   0.5499   1.0000
   3.000   0.4890   0.00654   0.00156  -0.0315   0.4942   1.0000
   3.250   0.5137   0.00701   0.00171  -0.0310   0.4174   1.0000
   3.500   0.5378   0.00762   0.00194  -0.0306   0.3255   1.0000
   3.750   0.5617   0.00832   0.00222  -0.0303   0.2286   1.0000
   4.000   0.5848   0.00926   0.00263  -0.0299   0.1156   1.0000
   4.250   0.6077   0.01035   0.00323  -0.0293   0.0227   1.0000
   4.500   0.6338   0.01078   0.00369  -0.0289   0.0183   1.0000
   4.750   0.6596   0.01130   0.00434  -0.0285   0.0171   1.0000
   5.000   0.6851   0.01186   0.00500  -0.0280   0.0168   1.0000
   5.250   0.7103   0.01246   0.00567  -0.0275   0.0162   1.0000
   5.500   0.7350   0.01312   0.00641  -0.0270   0.0154   1.0000
   5.750   0.7589   0.01397   0.00736  -0.0263   0.0151   1.0000
   6.000   0.7823   0.01496   0.00845  -0.0255   0.0148   1.0000
   6.250   0.8054   0.01612   0.00972  -0.0247   0.0145   1.0000
   6.500   0.8283   0.01762   0.01135  -0.0237   0.0145   1.0000
   6.750   0.8512   0.01967   0.01359  -0.0226   0.0151   1.0000
   7.000   0.8726   0.02295   0.01716  -0.0214   0.0165   1.0000
   8.500   0.9627   0.04480   0.04136  -0.0124   0.0224   1.0000
   8.750   0.9696   0.04789   0.04471  -0.0112   0.0209   1.0000
   9.000   0.9754   0.05049   0.04747  -0.0103   0.0197   1.0000
   9.250   0.9779   0.05337   0.05049  -0.0094   0.0192   1.0000
   9.500   0.9838   0.05570   0.05284  -0.0088   0.0185   1.0000
   9.750   0.9747   0.05950   0.05678  -0.0078   0.0182   1.0000
  10.000   0.9567   0.06295   0.06036  -0.0061   0.0180   1.0000
  10.250   0.9375   0.06680   0.06435  -0.0064   0.0181   1.0000
  10.500   0.9149   0.07229   0.07002  -0.0098   0.0184   1.0000
  10.750   0.8430   0.10030   0.09823  -0.0327   0.0206   1.0000
  11.000   0.8349   0.10770   0.10561  -0.0370   0.0205   1.0000
  11.250   0.8314   0.11353   0.11142  -0.0402   0.0200   1.0000
  11.500   0.8304   0.11863   0.11651  -0.0427   0.0194   1.0000
  11.750   0.7003   0.12483   0.12288  -0.0428   0.0230   1.0000
  12.000   0.6962   0.13024   0.12828  -0.0455   0.0220   1.0000
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