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S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il)
Reynolds number: 100,000
Max Cl/Cd: 56.59 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s7055-il-100000-n5.txt
Download as CSV file: xf-s7055-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3320   0.09172   0.08700  -0.0409   1.0000   0.0322
  -8.500  -0.3348   0.08851   0.08387  -0.0413   1.0000   0.0311
  -8.250  -0.3417   0.08545   0.08092  -0.0414   1.0000   0.0303
  -8.000  -0.3548   0.08279   0.07839  -0.0406   1.0000   0.0298
  -7.750  -0.3764   0.08113   0.07686  -0.0379   1.0000   0.0292
  -7.500  -0.3801   0.07562   0.07140  -0.0438   0.9911   0.0281
  -7.000  -0.3510   0.05605   0.05137  -0.0662   0.9682   0.0258
  -6.500  -0.3129   0.04837   0.04333  -0.0730   0.9528   0.0281
  -6.250  -0.2922   0.04456   0.03924  -0.0755   0.9446   0.0295
  -6.000  -0.2732   0.03994   0.03417  -0.0772   0.9362   0.0302
  -5.750  -0.2513   0.03550   0.02917  -0.0784   0.9290   0.0305
  -5.500  -0.2311   0.03209   0.02520  -0.0782   0.9205   0.0312
  -5.250  -0.2046   0.02902   0.02153  -0.0786   0.9145   0.0323
  -5.000  -0.1811   0.02674   0.01872  -0.0780   0.9065   0.0339
  -4.750  -0.1526   0.02494   0.01653  -0.0783   0.9007   0.0372
  -4.500  -0.1275   0.02383   0.01524  -0.0780   0.8930   0.0404
  -4.250  -0.0983   0.02239   0.01351  -0.0780   0.8870   0.0438
  -4.000  -0.0721   0.02127   0.01214  -0.0774   0.8795   0.0484
  -3.750  -0.0445   0.02045   0.01130  -0.0774   0.8729   0.0551
  -3.500  -0.0191   0.01969   0.01040  -0.0768   0.8651   0.0625
  -3.250   0.0080   0.01897   0.00962  -0.0765   0.8584   0.0697
  -3.000   0.0322   0.01839   0.00899  -0.0757   0.8500   0.0782
  -2.750   0.0595   0.01784   0.00833  -0.0753   0.8434   0.0876
  -2.500   0.0830   0.01734   0.00783  -0.0744   0.8344   0.0988
  -2.250   0.1102   0.01676   0.00730  -0.0741   0.8282   0.1228
  -2.000   0.1328   0.01618   0.00699  -0.0732   0.8188   0.1833
  -1.750   0.1573   0.01535   0.00673  -0.0727   0.8118   0.3458
  -1.500   0.1778   0.01445   0.00665  -0.0712   0.8033   0.5663
  -1.250   0.2464   0.01351   0.00652  -0.0772   0.8000   0.9325
  -1.000   0.3151   0.01341   0.00618  -0.0854   0.7926   1.0000
  -0.750   0.3383   0.01340   0.00596  -0.0844   0.7842   1.0000
  -0.500   0.3604   0.01344   0.00585  -0.0833   0.7742   1.0000
  -0.250   0.3830   0.01350   0.00576  -0.0822   0.7644   1.0000
   0.000   0.4068   0.01352   0.00563  -0.0813   0.7557   1.0000
   0.250   0.4299   0.01358   0.00556  -0.0802   0.7458   1.0000
   0.500   0.4530   0.01365   0.00553  -0.0792   0.7357   1.0000
   0.750   0.4771   0.01370   0.00546  -0.0784   0.7266   1.0000
   1.000   0.5010   0.01377   0.00542  -0.0775   0.7169   1.0000
   1.250   0.5244   0.01388   0.00545  -0.0765   0.7065   1.0000
   1.500   0.5485   0.01397   0.00546  -0.0757   0.6967   1.0000
   1.750   0.5733   0.01404   0.00544  -0.0749   0.6873   1.0000
   2.000   0.5967   0.01418   0.00554  -0.0740   0.6761   1.0000
   2.250   0.6206   0.01430   0.00561  -0.0731   0.6653   1.0000
   2.500   0.6450   0.01442   0.00567  -0.0723   0.6548   1.0000
   2.750   0.6699   0.01453   0.00573  -0.0716   0.6445   1.0000
   3.000   0.6936   0.01469   0.00587  -0.0708   0.6326   1.0000
   3.250   0.7176   0.01485   0.00601  -0.0700   0.6208   1.0000
   3.500   0.7417   0.01502   0.00616  -0.0692   0.6092   1.0000
   3.750   0.7659   0.01519   0.00634  -0.0684   0.5975   1.0000
   4.000   0.7901   0.01537   0.00650  -0.0676   0.5858   1.0000
   4.250   0.8143   0.01556   0.00666  -0.0669   0.5739   1.0000
   4.500   0.8379   0.01578   0.00689  -0.0660   0.5609   1.0000
   4.750   0.8613   0.01600   0.00715  -0.0652   0.5475   1.0000
   5.000   0.8847   0.01624   0.00740  -0.0643   0.5339   1.0000
   5.250   0.9078   0.01649   0.00768  -0.0634   0.5201   1.0000
   5.500   0.9308   0.01676   0.00797  -0.0625   0.5063   1.0000
   5.750   0.9535   0.01705   0.00829  -0.0616   0.4922   1.0000
   6.000   0.9759   0.01735   0.00866  -0.0606   0.4777   1.0000
   6.250   0.9980   0.01767   0.00901  -0.0596   0.4628   1.0000
   6.500   1.0196   0.01802   0.00938  -0.0585   0.4475   1.0000
   6.750   1.0406   0.01839   0.00979  -0.0574   0.4313   1.0000
   7.000   1.0610   0.01879   0.01025  -0.0562   0.4145   1.0000
   7.250   1.0809   0.01921   0.01076  -0.0549   0.3973   1.0000
   7.500   1.1001   0.01966   0.01125  -0.0535   0.3797   1.0000
   7.750   1.1183   0.02016   0.01176  -0.0520   0.3617   1.0000
   8.000   1.1356   0.02068   0.01235  -0.0504   0.3421   1.0000
   8.250   1.1518   0.02127   0.01296  -0.0487   0.3227   1.0000
   8.500   1.1669   0.02190   0.01366  -0.0468   0.3026   1.0000
   8.750   1.1806   0.02259   0.01438  -0.0448   0.2820   1.0000
   9.000   1.1926   0.02335   0.01515  -0.0427   0.2615   1.0000
   9.250   1.2027   0.02418   0.01600  -0.0403   0.2400   1.0000
   9.500   1.2095   0.02509   0.01689  -0.0375   0.2191   1.0000
   9.750   1.2149   0.02611   0.01790  -0.0346   0.1981   1.0000
  10.000   1.2194   0.02728   0.01905  -0.0319   0.1774   1.0000
  10.250   1.2231   0.02859   0.02033  -0.0294   0.1575   1.0000
  10.500   1.2258   0.03006   0.02183  -0.0270   0.1377   1.0000
  10.750   1.2277   0.03169   0.02345  -0.0248   0.1191   1.0000
  11.000   1.2270   0.03362   0.02532  -0.0227   0.1017   1.0000
  11.250   1.2269   0.03564   0.02732  -0.0210   0.0842   1.0000
  11.500   1.2239   0.03801   0.02961  -0.0193   0.0677   1.0000
  11.750   1.2197   0.04063   0.03215  -0.0179   0.0539   1.0000
  12.000   1.2154   0.04340   0.03490  -0.0168   0.0430   1.0000
  12.250   1.2126   0.04616   0.03777  -0.0159   0.0363   1.0000
  12.500   1.2055   0.04950   0.04112  -0.0153   0.0310   1.0000
  12.750   1.1998   0.05287   0.04465  -0.0149   0.0270   1.0000
  13.000   1.1893   0.05694   0.04879  -0.0149   0.0243   1.0000
  13.250   1.1815   0.06087   0.05285  -0.0151   0.0228   1.0000
  13.500   1.1755   0.06475   0.05692  -0.0155   0.0214   1.0000
  13.750   1.1687   0.06890   0.06123  -0.0162   0.0198   1.0000
  14.000   1.1626   0.07309   0.06557  -0.0171   0.0190   1.0000
  14.250   1.1553   0.07763   0.07023  -0.0184   0.0179   1.0000
  14.500   1.1464   0.08252   0.07524  -0.0199   0.0171   1.0000
  14.750   1.1390   0.08731   0.08013  -0.0214   0.0163   1.0000
  15.000   1.1349   0.09171   0.08472  -0.0227   0.0157   1.0000
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