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S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il)
Reynolds number: 500,000
Max Cl/Cd: 99.11 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s7055-il-500000-n5.txt
Download as CSV file: xf-s7055-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3550   0.09342   0.09121  -0.0380   1.0000   0.0076
  -9.500  -0.3577   0.08912   0.08695  -0.0395   1.0000   0.0075
  -8.500  -0.4827   0.02964   0.02639  -0.0806   0.8957   0.0077
  -8.000  -0.4679   0.02165   0.01724  -0.0778   0.8764   0.0084
  -7.750  -0.4492   0.01990   0.01513  -0.0768   0.8692   0.0087
  -7.500  -0.4277   0.01865   0.01359  -0.0761   0.8621   0.0090
  -7.250  -0.4062   0.01736   0.01201  -0.0752   0.8557   0.0095
  -7.000  -0.3835   0.01636   0.01086  -0.0747   0.8488   0.0101
  -6.750  -0.3593   0.01571   0.01007  -0.0741   0.8428   0.0106
  -6.500  -0.3347   0.01500   0.00921  -0.0737   0.8363   0.0110
  -6.250  -0.3100   0.01432   0.00838  -0.0731   0.8300   0.0114
  -6.000  -0.2849   0.01369   0.00761  -0.0727   0.8235   0.0119
  -5.750  -0.2597   0.01312   0.00689  -0.0722   0.8169   0.0124
  -5.500  -0.2342   0.01259   0.00623  -0.0717   0.8104   0.0128
  -5.250  -0.2086   0.01212   0.00566  -0.0713   0.8032   0.0134
  -5.000  -0.1831   0.01164   0.00511  -0.0709   0.7961   0.0147
  -4.750  -0.1569   0.01131   0.00471  -0.0705   0.7883   0.0158
  -4.500  -0.1305   0.01099   0.00431  -0.0702   0.7809   0.0171
  -4.250  -0.1041   0.01070   0.00393  -0.0698   0.7732   0.0186
  -4.000  -0.0776   0.01041   0.00363  -0.0695   0.7655   0.0219
  -3.750  -0.0508   0.01024   0.00338  -0.0693   0.7580   0.0252
  -3.500  -0.0240   0.01001   0.00313  -0.0690   0.7499   0.0292
  -3.250   0.0029   0.00988   0.00294  -0.0688   0.7422   0.0333
  -3.000   0.0301   0.00977   0.00277  -0.0686   0.7336   0.0360
  -2.750   0.0568   0.00957   0.00254  -0.0684   0.7255   0.0408
  -2.500   0.0837   0.00945   0.00237  -0.0682   0.7168   0.0453
  -2.250   0.1108   0.00932   0.00219  -0.0680   0.7080   0.0507
  -2.000   0.1376   0.00919   0.00204  -0.0677   0.6991   0.0587
  -1.750   0.1645   0.00906   0.00190  -0.0675   0.6898   0.0706
  -1.500   0.1913   0.00892   0.00179  -0.0673   0.6805   0.0913
  -1.250   0.2177   0.00875   0.00168  -0.0670   0.6715   0.1274
  -1.000   0.2439   0.00853   0.00160  -0.0668   0.6621   0.1828
  -0.750   0.2697   0.00828   0.00155  -0.0665   0.6531   0.2609
  -0.500   0.2951   0.00803   0.00151  -0.0662   0.6439   0.3481
  -0.250   0.3198   0.00771   0.00149  -0.0657   0.6344   0.4562
   0.000   0.3420   0.00725   0.00149  -0.0647   0.6252   0.6144
   0.250   0.3594   0.00667   0.00157  -0.0622   0.6162   0.8202
   0.500   0.4078   0.00655   0.00166  -0.0662   0.6049   0.9484
   0.750   0.4579   0.00665   0.00167  -0.0710   0.5929   0.9789
   1.000   0.4950   0.00674   0.00168  -0.0731   0.5812   0.9883
   1.250   0.5293   0.00684   0.00169  -0.0745   0.5696   0.9945
   1.500   0.5651   0.00693   0.00170  -0.0764   0.5578   0.9993
   1.750   0.5917   0.00704   0.00174  -0.0762   0.5466   1.0000
   2.000   0.6161   0.00714   0.00179  -0.0755   0.5357   1.0000
   2.250   0.6403   0.00725   0.00184  -0.0748   0.5246   1.0000
   2.500   0.6645   0.00738   0.00191  -0.0741   0.5131   1.0000
   2.750   0.6885   0.00752   0.00200  -0.0734   0.4998   1.0000
   3.000   0.7126   0.00767   0.00208  -0.0727   0.4867   1.0000
   3.250   0.7366   0.00782   0.00218  -0.0720   0.4743   1.0000
   3.500   0.7607   0.00798   0.00229  -0.0713   0.4618   1.0000
   3.750   0.7849   0.00814   0.00242  -0.0706   0.4496   1.0000
   4.000   0.8089   0.00831   0.00255  -0.0699   0.4371   1.0000
   4.250   0.8327   0.00849   0.00270  -0.0692   0.4244   1.0000
   4.500   0.8564   0.00869   0.00285  -0.0685   0.4109   1.0000
   4.750   0.8799   0.00890   0.00303  -0.0677   0.3963   1.0000
   5.000   0.9033   0.00912   0.00321  -0.0669   0.3819   1.0000
   5.250   0.9267   0.00935   0.00340  -0.0662   0.3673   1.0000
   5.500   0.9498   0.00960   0.00361  -0.0654   0.3525   1.0000
   5.750   0.9727   0.00987   0.00385  -0.0646   0.3369   1.0000
   6.250   1.0176   0.01047   0.00435  -0.0628   0.3021   1.0000
   6.500   1.0397   0.01080   0.00463  -0.0619   0.2842   1.0000
   6.750   1.0612   0.01116   0.00493  -0.0610   0.2660   1.0000
   7.000   1.0826   0.01153   0.00527  -0.0600   0.2487   1.0000
   7.250   1.1034   0.01194   0.00561  -0.0589   0.2292   1.0000
   7.500   1.1223   0.01246   0.00603  -0.0576   0.2033   1.0000
   7.750   1.1396   0.01309   0.00650  -0.0561   0.1735   1.0000
   8.000   1.1546   0.01384   0.00705  -0.0543   0.1402   1.0000
   8.250   1.1693   0.01459   0.00765  -0.0524   0.1101   1.0000
   8.500   1.1841   0.01530   0.00824  -0.0505   0.0884   1.0000
   8.750   1.1971   0.01607   0.00888  -0.0484   0.0662   1.0000
   9.000   1.2094   0.01676   0.00951  -0.0461   0.0512   1.0000
   9.250   1.2184   0.01753   0.01020  -0.0432   0.0361   1.0000
   9.500   1.2289   0.01824   0.01089  -0.0407   0.0274   1.0000
   9.750   1.2373   0.01911   0.01172  -0.0381   0.0179   1.0000
  10.000   1.2462   0.02001   0.01261  -0.0356   0.0115   1.0000
  10.250   1.2553   0.02094   0.01357  -0.0334   0.0074   1.0000
  10.500   1.2635   0.02196   0.01463  -0.0312   0.0053   1.0000
  10.750   1.2738   0.02290   0.01565  -0.0293   0.0047   1.0000
  11.000   1.2838   0.02390   0.01673  -0.0276   0.0043   1.0000
  11.250   1.2935   0.02495   0.01786  -0.0259   0.0041   1.0000
  11.500   1.3015   0.02617   0.01915  -0.0243   0.0037   1.0000
  11.750   1.3087   0.02750   0.02058  -0.0227   0.0036   1.0000
  12.000   1.3135   0.02908   0.02225  -0.0211   0.0032   1.0000
  12.250   1.3207   0.03051   0.02377  -0.0198   0.0031   1.0000
  12.500   1.3259   0.03217   0.02556  -0.0185   0.0030   1.0000
  12.750   1.3294   0.03405   0.02755  -0.0173   0.0029   1.0000
  13.000   1.3324   0.03606   0.02968  -0.0163   0.0028   1.0000
  13.250   1.3349   0.03819   0.03191  -0.0155   0.0028   1.0000
  13.500   1.3368   0.04045   0.03428  -0.0148   0.0027   1.0000
  13.750   1.3372   0.04297   0.03691  -0.0142   0.0026   1.0000
  14.000   1.3374   0.04557   0.03962  -0.0139   0.0026   1.0000
  14.250   1.3348   0.04862   0.04279  -0.0138   0.0025   1.0000
  14.500   1.3321   0.05182   0.04612  -0.0139   0.0025   1.0000
  14.750   1.3299   0.05507   0.04948  -0.0141   0.0024   1.0000
  15.000   1.3258   0.05871   0.05324  -0.0147   0.0024   1.0000
  15.250   1.3212   0.06254   0.05719  -0.0154   0.0023   1.0000
  15.500   1.3145   0.06677   0.06156  -0.0164   0.0024   1.0000
  15.750   1.3079   0.07116   0.06607  -0.0176   0.0023   1.0000
  16.000   1.3016   0.07565   0.07067  -0.0190   0.0023   1.0000
  16.250   1.2944   0.08038   0.07552  -0.0205   0.0023   1.0000
  16.500   1.2853   0.08556   0.08083  -0.0224   0.0022   1.0000
  16.750   1.2766   0.09081   0.08620  -0.0244   0.0022   1.0000
  17.000   1.2667   0.09639   0.09193  -0.0267   0.0022   1.0000
  17.250   1.2558   0.10227   0.09793  -0.0292   0.0021   1.0000
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