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S7075 (9%) (s7075-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S7075 (9%) (s7075-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.95 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7075-il-1000000.txt
Download as CSV file: xf-s7075-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7075 (9%)                                      
  
 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  -0.3917   0.09403   0.09240  -0.0360   1.0000   0.0113
  -9.250  -0.4016   0.09192   0.09032  -0.0338   1.0000   0.0113
  -9.000  -0.4082   0.08482   0.08325  -0.0384   0.9988   0.0116
  -8.750  -0.3949   0.08190   0.08034  -0.0417   0.9971   0.0119
  -8.500  -0.3816   0.07793   0.07637  -0.0464   0.9949   0.0121
  -8.250  -0.3697   0.07388   0.07233  -0.0512   0.9916   0.0124
  -8.000  -0.3571   0.06887   0.06731  -0.0581   0.9872   0.0128
  -7.750  -0.3363   0.06149   0.05993  -0.0713   0.9838   0.0135
  -7.500  -0.3160   0.05104   0.04936  -0.0874   0.9780   0.0135
  -7.250  -0.2924   0.03830   0.03618  -0.0994   0.9721   0.0152
  -7.000  -0.2792   0.03355   0.03106  -0.1018   0.9645   0.0153
  -6.250  -0.2483   0.01634   0.01209  -0.1005   0.9439   0.0116
  -6.000  -0.2235   0.01538   0.01097  -0.1000   0.9401   0.0114
  -5.750  -0.1998   0.01394   0.00932  -0.0994   0.9359   0.0114
  -5.500  -0.1768   0.01205   0.00720  -0.0987   0.9319   0.0117
  -5.250  -0.1516   0.01115   0.00619  -0.0982   0.9286   0.0119
  -5.000  -0.1259   0.01049   0.00546  -0.0979   0.9250   0.0123
  -4.750  -0.0998   0.00997   0.00490  -0.0975   0.9210   0.0126
  -4.500  -0.0734   0.00950   0.00437  -0.0971   0.9170   0.0128
  -4.250  -0.0467   0.00909   0.00389  -0.0968   0.9133   0.0131
  -4.000  -0.0200   0.00873   0.00349  -0.0966   0.9092   0.0135
  -3.750   0.0071   0.00842   0.00314  -0.0963   0.9050   0.0141
  -3.500   0.0343   0.00812   0.00278  -0.0961   0.9011   0.0146
  -3.250   0.0618   0.00786   0.00247  -0.0959   0.8971   0.0151
  -3.000   0.0891   0.00754   0.00210  -0.0956   0.8922   0.0170
  -2.750   0.1166   0.00733   0.00188  -0.0954   0.8874   0.0202
  -2.500   0.1439   0.00697   0.00165  -0.0952   0.8829   0.0531
  -2.250   0.1711   0.00669   0.00151  -0.0951   0.8772   0.0959
  -2.000   0.1983   0.00640   0.00138  -0.0950   0.8716   0.1495
  -1.750   0.2254   0.00611   0.00129  -0.0949   0.8655   0.2179
  -1.500   0.2523   0.00578   0.00121  -0.0948   0.8585   0.3053
  -1.250   0.2795   0.00554   0.00115  -0.0947   0.8515   0.3751
  -1.000   0.3064   0.00523   0.00110  -0.0946   0.8435   0.4724
  -0.750   0.3327   0.00487   0.00108  -0.0943   0.8347   0.5939
  -0.500   0.3586   0.00459   0.00108  -0.0938   0.8251   0.7035
  -0.250   0.3843   0.00445   0.00111  -0.0932   0.8136   0.7780
   0.000   0.4107   0.00443   0.00113  -0.0926   0.8000   0.8161
   0.250   0.4371   0.00446   0.00113  -0.0921   0.7832   0.8372
   0.500   0.4634   0.00451   0.00112  -0.0916   0.7616   0.8532
   0.750   0.4890   0.00459   0.00112  -0.0909   0.7377   0.8674
   1.000   0.5141   0.00468   0.00114  -0.0901   0.7129   0.8816
   1.250   0.5391   0.00478   0.00117  -0.0894   0.6875   0.8950
   1.500   0.5635   0.00488   0.00121  -0.0885   0.6624   0.9102
   1.750   0.5871   0.00496   0.00126  -0.0874   0.6365   0.9329
   2.000   0.6188   0.00508   0.00131  -0.0882   0.6075   0.9719
   2.250   0.6491   0.00528   0.00137  -0.0888   0.5775   1.0000
   2.500   0.6750   0.00549   0.00147  -0.0884   0.5501   1.0000
   2.750   0.7008   0.00571   0.00157  -0.0881   0.5220   1.0000
   3.000   0.7266   0.00595   0.00167  -0.0877   0.4931   1.0000
   3.250   0.7520   0.00620   0.00179  -0.0873   0.4617   1.0000
   3.500   0.7772   0.00649   0.00194  -0.0868   0.4277   1.0000
   3.750   0.8027   0.00675   0.00208  -0.0864   0.3992   1.0000
   4.000   0.8278   0.00705   0.00224  -0.0860   0.3669   1.0000
   4.250   0.8523   0.00741   0.00243  -0.0855   0.3312   1.0000
   4.500   0.8770   0.00775   0.00263  -0.0850   0.2977   1.0000
   4.750   0.9016   0.00810   0.00283  -0.0845   0.2668   1.0000
   5.000   0.9259   0.00848   0.00306  -0.0839   0.2349   1.0000
   5.250   0.9504   0.00884   0.00330  -0.0834   0.2081   1.0000
   5.500   0.9748   0.00920   0.00355  -0.0829   0.1833   1.0000
   5.750   0.9989   0.00958   0.00381  -0.0823   0.1599   1.0000
   6.000   1.0227   0.00999   0.00410  -0.0817   0.1361   1.0000
   6.250   1.0465   0.01040   0.00441  -0.0811   0.1144   1.0000
   6.500   1.0699   0.01084   0.00474  -0.0805   0.0952   1.0000
   6.750   1.0936   0.01124   0.00507  -0.0799   0.0798   1.0000
   7.000   1.1170   0.01165   0.00541  -0.0792   0.0662   1.0000
   7.250   1.1401   0.01209   0.00579  -0.0785   0.0546   1.0000
   7.500   1.1629   0.01255   0.00621  -0.0777   0.0450   1.0000
   7.750   1.1856   0.01300   0.00662  -0.0769   0.0386   1.0000
   8.000   1.2086   0.01342   0.00705  -0.0762   0.0346   1.0000
   8.250   1.2316   0.01381   0.00746  -0.0754   0.0320   1.0000
   8.500   1.2531   0.01433   0.00799  -0.0745   0.0291   1.0000
   8.750   1.2747   0.01483   0.00852  -0.0735   0.0269   1.0000
   9.000   1.2976   0.01516   0.00889  -0.0728   0.0258   1.0000
   9.250   1.3196   0.01557   0.00933  -0.0720   0.0247   1.0000
   9.500   1.3407   0.01603   0.00982  -0.0710   0.0235   1.0000
   9.750   1.3607   0.01657   0.01039  -0.0698   0.0223   1.0000
  10.000   1.3778   0.01732   0.01121  -0.0682   0.0209   1.0000
  10.250   1.3947   0.01802   0.01199  -0.0666   0.0202   1.0000
  10.500   1.4143   0.01846   0.01248  -0.0654   0.0199   1.0000
  10.750   1.4329   0.01886   0.01293  -0.0640   0.0194   1.0000
  11.000   1.4511   0.01922   0.01333  -0.0626   0.0186   1.0000
  11.250   1.4678   0.01967   0.01382  -0.0609   0.0179   1.0000
  11.500   1.4839   0.02014   0.01432  -0.0592   0.0172   1.0000
  11.750   1.4984   0.02073   0.01493  -0.0574   0.0163   1.0000
  12.000   1.5090   0.02157   0.01583  -0.0550   0.0154   1.0000
  12.250   1.5205   0.02236   0.01669  -0.0528   0.0148   1.0000
  12.500   1.5397   0.02265   0.01702  -0.0518   0.0143   1.0000
  12.750   1.5560   0.02313   0.01754  -0.0505   0.0135   1.0000
  13.000   1.5711   0.02371   0.01815  -0.0490   0.0126   1.0000
  13.250   1.5843   0.02443   0.01889  -0.0474   0.0114   1.0000
  13.500   1.5966   0.02522   0.01973  -0.0457   0.0102   1.0000
  13.750   1.6067   0.02621   0.02069  -0.0439   0.0076   1.0000
  14.000   1.6132   0.02747   0.02200  -0.0419   0.0058   1.0000
  14.250   1.6171   0.02900   0.02359  -0.0397   0.0047   1.0000
  14.500   1.6210   0.03057   0.02524  -0.0377   0.0042   1.0000
  14.750   1.6219   0.03248   0.02725  -0.0357   0.0037   1.0000
  15.000   1.6248   0.03428   0.02915  -0.0340   0.0035   1.0000
  15.250   1.6267   0.03625   0.03123  -0.0326   0.0035   1.0000
  15.500   1.6270   0.03847   0.03358  -0.0313   0.0033   1.0000
  15.750   1.6260   0.04093   0.03616  -0.0303   0.0033   1.0000
  16.000   1.6245   0.04359   0.03895  -0.0295   0.0032   1.0000
  16.250   1.6205   0.04669   0.04217  -0.0291   0.0031   1.0000
  16.500   1.6145   0.05021   0.04583  -0.0292   0.0030   1.0000
  16.750   1.6079   0.05407   0.04982  -0.0296   0.0030   1.0000
  17.000   1.5995   0.05840   0.05429  -0.0305   0.0029   1.0000
  17.250   1.5888   0.06337   0.05940  -0.0320   0.0029   1.0000
  17.500   1.5757   0.06901   0.06520  -0.0342   0.0029   1.0000
  17.750   1.5598   0.07543   0.07177  -0.0369   0.0028   1.0000
  18.000   1.5446   0.08206   0.07855  -0.0401   0.0029   1.0000
  18.250   1.5246   0.08989   0.08654  -0.0441   0.0029   1.0000
  18.500   1.5032   0.09828   0.09509  -0.0486   0.0029   1.0000
  18.750   1.4783   0.10770   0.10468  -0.0538   0.0029   1.0000
  19.000   1.4522   0.11767   0.11482  -0.0595   0.0029   1.0000
  19.250   1.4242   0.12834   0.12565  -0.0657   0.0029   1.0000
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