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S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.29 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7055-il-1000000.txt
Download as CSV file: xf-s7055-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3420   0.09200   0.09045  -0.0390   1.0000   0.0114
  -9.250  -0.3421   0.08814   0.08662  -0.0403   1.0000   0.0114
  -9.000  -0.3584   0.08194   0.08047  -0.0425   1.0000   0.0119
  -8.750  -0.3480   0.07778   0.07631  -0.0468   0.9833   0.0120
  -8.500  -0.3282   0.07213   0.07065  -0.0555   0.9723   0.0122
  -8.250  -0.4711   0.02519   0.02219  -0.0800   0.8985   0.0081
  -8.000  -0.4762   0.01884   0.01496  -0.0773   0.8878   0.0084
  -7.750  -0.4576   0.01716   0.01303  -0.0763   0.8809   0.0088
  -7.500  -0.4348   0.01633   0.01205  -0.0757   0.8742   0.0091
  -7.250  -0.4111   0.01560   0.01118  -0.0751   0.8681   0.0094
  -7.000  -0.3875   0.01471   0.01013  -0.0745   0.8615   0.0098
  -6.750  -0.3632   0.01402   0.00927  -0.0739   0.8556   0.0102
  -6.500  -0.3387   0.01319   0.00829  -0.0734   0.8491   0.0106
  -6.250  -0.3133   0.01268   0.00765  -0.0729   0.8429   0.0111
  -6.000  -0.2864   0.01246   0.00735  -0.0727   0.8365   0.0114
  -5.750  -0.2645   0.01107   0.00575  -0.0717   0.8296   0.0126
  -5.500  -0.2385   0.01065   0.00527  -0.0713   0.8231   0.0132
  -5.250  -0.2123   0.01029   0.00483  -0.0710   0.8163   0.0140
  -5.000  -0.1858   0.00996   0.00442  -0.0706   0.8100   0.0148
  -4.750  -0.1592   0.00964   0.00404  -0.0703   0.8031   0.0155
  -4.500  -0.1336   0.00914   0.00343  -0.0698   0.7966   0.0170
  -4.250  -0.1065   0.00892   0.00321  -0.0696   0.7893   0.0191
  -4.000  -0.0792   0.00879   0.00302  -0.0694   0.7825   0.0211
  -3.750  -0.0526   0.00845   0.00268  -0.0691   0.7747   0.0256
  -3.500  -0.0248   0.00842   0.00261  -0.0690   0.7674   0.0290
  -3.250   0.0019   0.00815   0.00232  -0.0688   0.7591   0.0346
  -3.000   0.0294   0.00807   0.00220  -0.0687   0.7512   0.0378
  -2.750   0.0567   0.00796   0.00203  -0.0685   0.7427   0.0407
  -2.500   0.0838   0.00777   0.00183  -0.0683   0.7342   0.0458
  -2.250   0.1111   0.00769   0.00169  -0.0681   0.7259   0.0496
  -2.000   0.1384   0.00755   0.00155  -0.0680   0.7172   0.0579
  -1.750   0.1655   0.00741   0.00143  -0.0678   0.7088   0.0727
  -1.500   0.1921   0.00720   0.00132  -0.0675   0.7000   0.1139
  -1.250   0.2183   0.00691   0.00123  -0.0673   0.6913   0.1866
  -1.000   0.2437   0.00659   0.00117  -0.0670   0.6828   0.2877
  -0.750   0.2692   0.00628   0.00114  -0.0667   0.6734   0.3899
  -0.500   0.2938   0.00592   0.00112  -0.0662   0.6644   0.5168
  -0.250   0.3169   0.00555   0.00111  -0.0653   0.6551   0.6544
   0.000   0.3384   0.00518   0.00114  -0.0638   0.6454   0.7903
   0.250   0.3613   0.00496   0.00119  -0.0625   0.6359   0.8959
   0.500   0.4095   0.00498   0.00126  -0.0666   0.6253   0.9688
   0.750   0.4574   0.00510   0.00130  -0.0710   0.6141   0.9848
   1.000   0.5021   0.00519   0.00132  -0.0747   0.6028   0.9932
   1.250   0.5490   0.00526   0.00132  -0.0789   0.5916   0.9986
   1.500   0.5814   0.00533   0.00133  -0.0800   0.5807   1.0000
   1.750   0.6055   0.00542   0.00135  -0.0793   0.5690   1.0000
   2.000   0.6298   0.00551   0.00138  -0.0786   0.5569   1.0000
   2.250   0.6542   0.00559   0.00142  -0.0779   0.5446   1.0000
   2.500   0.6786   0.00569   0.00147  -0.0772   0.5331   1.0000
   2.750   0.7031   0.00580   0.00153  -0.0766   0.5215   1.0000
   3.000   0.7275   0.00591   0.00160  -0.0759   0.5101   1.0000
   3.250   0.7518   0.00604   0.00167  -0.0752   0.4982   1.0000
   3.500   0.7763   0.00617   0.00176  -0.0746   0.4855   1.0000
   3.750   0.8007   0.00631   0.00185  -0.0739   0.4724   1.0000
   4.000   0.8251   0.00645   0.00195  -0.0733   0.4590   1.0000
   4.250   0.8493   0.00661   0.00207  -0.0726   0.4454   1.0000
   4.500   0.8736   0.00677   0.00219  -0.0720   0.4320   1.0000
   4.750   0.8977   0.00695   0.00232  -0.0713   0.4183   1.0000
   5.000   0.9218   0.00713   0.00246  -0.0707   0.4042   1.0000
   5.250   0.9458   0.00732   0.00261  -0.0700   0.3894   1.0000
   5.500   0.9693   0.00755   0.00279  -0.0692   0.3728   1.0000
   6.000   1.0160   0.00802   0.00315  -0.0677   0.3404   1.0000
   6.250   1.0394   0.00826   0.00335  -0.0670   0.3248   1.0000
   6.500   1.0623   0.00853   0.00357  -0.0662   0.3067   1.0000
   6.750   1.0844   0.00887   0.00382  -0.0653   0.2862   1.0000
   7.000   1.1052   0.00929   0.00411  -0.0642   0.2583   1.0000
   7.250   1.1254   0.00976   0.00444  -0.0630   0.2291   1.0000
   7.500   1.1453   0.01023   0.00480  -0.0618   0.2023   1.0000
   7.750   1.1642   0.01078   0.00519  -0.0604   0.1733   1.0000
   8.000   1.1833   0.01130   0.00559  -0.0591   0.1492   1.0000
   8.250   1.2019   0.01183   0.00601  -0.0577   0.1261   1.0000
   8.500   1.2187   0.01247   0.00651  -0.0561   0.1013   1.0000
   8.750   1.2355   0.01307   0.00701  -0.0545   0.0821   1.0000
   9.000   1.2513   0.01371   0.00755  -0.0527   0.0635   1.0000
   9.250   1.2662   0.01437   0.00812  -0.0508   0.0484   1.0000
   9.500   1.2805   0.01501   0.00870  -0.0488   0.0356   1.0000
   9.750   1.2889   0.01578   0.00938  -0.0457   0.0227   1.0000
  10.000   1.2918   0.01679   0.01031  -0.0418   0.0099   1.0000
  10.250   1.3005   0.01760   0.01113  -0.0390   0.0069   1.0000
  10.500   1.3114   0.01833   0.01190  -0.0367   0.0057   1.0000
  10.750   1.3221   0.01911   0.01275  -0.0346   0.0052   1.0000
  11.000   1.3301   0.02010   0.01383  -0.0322   0.0048   1.0000
  11.250   1.3406   0.02099   0.01478  -0.0302   0.0046   1.0000
  11.500   1.3509   0.02191   0.01578  -0.0284   0.0044   1.0000
  11.750   1.3588   0.02304   0.01699  -0.0265   0.0043   1.0000
  12.000   1.3665   0.02424   0.01827  -0.0247   0.0042   1.0000
  12.250   1.3741   0.02549   0.01960  -0.0231   0.0040   1.0000
  12.500   1.3801   0.02692   0.02112  -0.0214   0.0040   1.0000
  12.750   1.3863   0.02839   0.02265  -0.0200   0.0038   1.0000
  13.000   1.3912   0.03003   0.02437  -0.0187   0.0037   1.0000
  13.250   1.3934   0.03198   0.02643  -0.0174   0.0036   1.0000
  13.500   1.3952   0.03404   0.02858  -0.0163   0.0035   1.0000
  13.750   1.3960   0.03629   0.03092  -0.0153   0.0034   1.0000
  14.000   1.3920   0.03912   0.03387  -0.0145   0.0034   1.0000
  14.250   1.3827   0.04263   0.03751  -0.0138   0.0033   1.0000
  14.500   1.3793   0.04567   0.04066  -0.0135   0.0033   1.0000
  14.750   1.3741   0.04908   0.04419  -0.0134   0.0033   1.0000
  15.000   1.3652   0.05306   0.04829  -0.0136   0.0032   1.0000
  15.250   1.3528   0.05766   0.05304  -0.0141   0.0030   1.0000
  15.500   1.3456   0.06177   0.05726  -0.0147   0.0030   1.0000
  15.750   1.3390   0.06590   0.06151  -0.0156   0.0030   1.0000
  16.000   1.3389   0.06933   0.06503  -0.0165   0.0029   1.0000
  16.250   1.3324   0.07372   0.06953  -0.0177   0.0029   1.0000
  16.500   1.3179   0.07930   0.07524  -0.0192   0.0030   1.0000
  16.750   1.3146   0.08352   0.07957  -0.0207   0.0029   1.0000
  17.000   1.3035   0.08892   0.08508  -0.0225   0.0030   1.0000
  17.250   1.2968   0.09387   0.09014  -0.0244   0.0029   1.0000
  17.500   1.2860   0.09949   0.09587  -0.0266   0.0029   1.0000
  17.750   1.2771   0.10503   0.10153  -0.0290   0.0028   1.0000
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