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S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il)
Reynolds number: 500,000
Max Cl/Cd: 107.29 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7055-il-500000.txt
Download as CSV file: xf-s7055-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7055 (10.5%) Flat-Bottomed                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3314   0.08945   0.08733  -0.0422   1.0000   0.0212
  -8.750  -0.3325   0.08609   0.08402  -0.0435   1.0000   0.0213
  -8.500  -0.3379   0.08326   0.08125  -0.0435   1.0000   0.0213
  -8.250  -0.3288   0.07786   0.07587  -0.0499   0.9897   0.0214
  -8.000  -0.3114   0.07101   0.06902  -0.0606   0.9796   0.0214
  -7.000  -0.3128   0.03302   0.02989  -0.0852   0.9185   0.0167
  -6.750  -0.2988   0.03089   0.02755  -0.0843   0.9095   0.0171
  -6.500  -0.2977   0.02325   0.01890  -0.0811   0.8996   0.0158
  -6.250  -0.2844   0.01989   0.01512  -0.0797   0.8910   0.0168
  -6.000  -0.2624   0.01876   0.01377  -0.0788   0.8845   0.0175
  -5.750  -0.2400   0.01730   0.01206  -0.0778   0.8768   0.0181
  -5.500  -0.2167   0.01605   0.01054  -0.0769   0.8705   0.0188
  -5.250  -0.1924   0.01500   0.00930  -0.0762   0.8629   0.0198
  -5.000  -0.1673   0.01422   0.00832  -0.0754   0.8565   0.0208
  -4.750  -0.1432   0.01311   0.00704  -0.0747   0.8489   0.0223
  -4.500  -0.1180   0.01255   0.00642  -0.0741   0.8424   0.0242
  -4.250  -0.0921   0.01209   0.00589  -0.0736   0.8350   0.0263
  -4.000  -0.0657   0.01175   0.00544  -0.0731   0.8284   0.0286
  -3.750  -0.0413   0.01096   0.00460  -0.0724   0.8210   0.0330
  -3.500  -0.0142   0.01085   0.00444  -0.0721   0.8142   0.0382
  -3.250   0.0110   0.01031   0.00386  -0.0716   0.8066   0.0441
  -3.000   0.0377   0.01012   0.00359  -0.0712   0.7996   0.0489
  -2.750   0.0639   0.00981   0.00324  -0.0709   0.7915   0.0539
  -2.500   0.0905   0.00960   0.00300  -0.0705   0.7844   0.0608
  -2.250   0.1171   0.00935   0.00272  -0.0702   0.7758   0.0684
  -2.000   0.1436   0.00912   0.00246  -0.0698   0.7681   0.0802
  -1.750   0.1693   0.00873   0.00224  -0.0694   0.7593   0.1262
  -1.500   0.1933   0.00814   0.00210  -0.0689   0.7510   0.2674
  -1.250   0.2169   0.00761   0.00201  -0.0683   0.7427   0.4165
  -1.000   0.2388   0.00704   0.00197  -0.0672   0.7338   0.5841
  -0.750   0.2577   0.00648   0.00196  -0.0651   0.7257   0.7643
  -0.500   0.2863   0.00619   0.00202  -0.0646   0.7167   0.9062
  -0.250   0.3422   0.00623   0.00202  -0.0703   0.7078   0.9639
   0.000   0.4001   0.00634   0.00199  -0.0766   0.6986   0.9887
   0.250   0.4549   0.00636   0.00193  -0.0825   0.6879   1.0000
   0.500   0.4788   0.00640   0.00189  -0.0817   0.6778   1.0000
   0.750   0.5027   0.00646   0.00186  -0.0809   0.6678   1.0000
   1.000   0.5267   0.00652   0.00184  -0.0801   0.6573   1.0000
   1.250   0.5510   0.00658   0.00184  -0.0794   0.6466   1.0000
   1.500   0.5753   0.00665   0.00186  -0.0787   0.6361   1.0000
   1.750   0.5995   0.00675   0.00188  -0.0780   0.6258   1.0000
   2.000   0.6239   0.00684   0.00192  -0.0773   0.6149   1.0000
   2.250   0.6484   0.00693   0.00197  -0.0766   0.6039   1.0000
   2.500   0.6727   0.00703   0.00202  -0.0759   0.5924   1.0000
   2.750   0.6970   0.00715   0.00209  -0.0752   0.5806   1.0000
   3.000   0.7213   0.00728   0.00216  -0.0745   0.5685   1.0000
   3.250   0.7455   0.00741   0.00224  -0.0738   0.5565   1.0000
   3.500   0.7699   0.00754   0.00235  -0.0731   0.5441   1.0000
   3.750   0.7943   0.00768   0.00246  -0.0724   0.5320   1.0000
   4.000   0.8186   0.00783   0.00258  -0.0717   0.5197   1.0000
   4.250   0.8426   0.00799   0.00271  -0.0710   0.5068   1.0000
   4.500   0.8666   0.00817   0.00285  -0.0703   0.4934   1.0000
   4.750   0.8904   0.00835   0.00300  -0.0696   0.4799   1.0000
   5.000   0.9141   0.00854   0.00316  -0.0688   0.4657   1.0000
   5.250   0.9377   0.00874   0.00334  -0.0681   0.4515   1.0000
   5.500   0.9612   0.00896   0.00354  -0.0673   0.4372   1.0000
   5.750   0.9845   0.00919   0.00374  -0.0665   0.4219   1.0000
   6.000   1.0076   0.00943   0.00395  -0.0657   0.4057   1.0000
   6.250   1.0305   0.00970   0.00418  -0.0649   0.3892   1.0000
   6.500   1.0529   0.00999   0.00444  -0.0640   0.3721   1.0000
   6.750   1.0753   0.01029   0.00471  -0.0631   0.3554   1.0000
   7.000   1.0975   0.01059   0.00499  -0.0622   0.3372   1.0000
   7.250   1.1188   0.01096   0.00530  -0.0612   0.3171   1.0000
   7.500   1.1393   0.01136   0.00564  -0.0601   0.2938   1.0000
   7.750   1.1589   0.01183   0.00603  -0.0588   0.2701   1.0000
   8.000   1.1773   0.01237   0.00645  -0.0574   0.2430   1.0000
   8.250   1.1948   0.01296   0.00691  -0.0559   0.2144   1.0000
   8.500   1.2112   0.01359   0.00742  -0.0543   0.1864   1.0000
   8.750   1.2265   0.01428   0.00797  -0.0525   0.1596   1.0000
   9.000   1.2398   0.01506   0.00861  -0.0504   0.1300   1.0000
   9.250   1.2524   0.01583   0.00926  -0.0482   0.1071   1.0000
   9.500   1.2628   0.01656   0.00990  -0.0456   0.0875   1.0000
   9.750   1.2707   0.01739   0.01064  -0.0426   0.0700   1.0000
  10.000   1.2783   0.01828   0.01145  -0.0398   0.0532   1.0000
  10.250   1.2835   0.01936   0.01243  -0.0368   0.0372   1.0000
  10.500   1.2835   0.02082   0.01378  -0.0334   0.0200   1.0000
  10.750   1.2859   0.02225   0.01523  -0.0305   0.0136   1.0000
  11.000   1.2913   0.02356   0.01658  -0.0282   0.0115   1.0000
  11.250   1.2931   0.02519   0.01834  -0.0256   0.0099   1.0000
  11.500   1.2994   0.02655   0.01980  -0.0238   0.0092   1.0000
  11.750   1.3041   0.02810   0.02145  -0.0220   0.0086   1.0000
  12.000   1.3075   0.02981   0.02326  -0.0204   0.0083   1.0000
  12.250   1.3100   0.03168   0.02521  -0.0189   0.0078   1.0000
  12.500   1.3091   0.03394   0.02757  -0.0174   0.0076   1.0000
  12.750   1.2996   0.03712   0.03088  -0.0159   0.0071   1.0000
  13.000   1.3027   0.03923   0.03310  -0.0152   0.0070   1.0000
  13.250   1.3014   0.04189   0.03587  -0.0144   0.0069   1.0000
  13.500   1.3007   0.04456   0.03866  -0.0139   0.0068   1.0000
  13.750   1.3001   0.04732   0.04152  -0.0136   0.0067   1.0000
  14.000   1.2964   0.05056   0.04488  -0.0134   0.0066   1.0000
  14.250   1.2943   0.05371   0.04816  -0.0134   0.0064   1.0000
  14.500   1.2913   0.05708   0.05165  -0.0136   0.0063   1.0000
  14.750   1.2867   0.06076   0.05545  -0.0139   0.0063   1.0000
  15.000   1.2844   0.06425   0.05905  -0.0144   0.0062   1.0000
  15.250   1.2816   0.06794   0.06286  -0.0151   0.0060   1.0000
  15.500   1.2772   0.07191   0.06695  -0.0159   0.0059   1.0000
  15.750   1.2728   0.07595   0.07111  -0.0168   0.0059   1.0000
  16.000   1.2691   0.08008   0.07535  -0.0181   0.0057   1.0000
  16.250   1.2642   0.08444   0.07982  -0.0194   0.0056   1.0000
  16.500   1.2580   0.08900   0.08454  -0.0206   0.0057   1.0000
  16.750   1.2526   0.09372   0.08937  -0.0225   0.0055   1.0000
  17.000   1.2457   0.09867   0.09447  -0.0242   0.0056   1.0000
  17.250   1.2392   0.10378   0.09969  -0.0264   0.0055   1.0000
  17.500   1.2309   0.10925   0.10532  -0.0287   0.0055   1.0000
  17.750   1.2231   0.11479   0.11097  -0.0313   0.0054   1.0000
  18.000   1.2140   0.12073   0.11707  -0.0341   0.0055   1.0000
  18.250   1.2035   0.12712   0.12362  -0.0373   0.0055   1.0000
  18.500   1.1943   0.13337   0.13000  -0.0408   0.0054   1.0000
  18.750   1.1834   0.14018   0.13696  -0.0446   0.0054   1.0000
  19.000   1.1689   0.14804   0.14500  -0.0491   0.0055   1.0000
  19.250   1.1508   0.15717   0.15434  -0.0544   0.0057   1.0000
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