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S7075 (9%) (s7075-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S7075 (9%) (s7075-il)
Reynolds number: 200,000
Max Cl/Cd: 81.34 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7075-il-200000.txt
Download as CSV file: xf-s7075-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4162   0.09220   0.08889  -0.0360   1.0000   0.0467
  -8.000  -0.4350   0.09053   0.08730  -0.0341   1.0000   0.0468
  -7.750  -0.4500   0.08790   0.08473  -0.0347   1.0000   0.0469
  -7.500  -0.4581   0.08442   0.08127  -0.0368   1.0000   0.0470
  -7.250  -0.4651   0.08055   0.07734  -0.0388   1.0000   0.0471
  -7.000  -0.4711   0.07602   0.07294  -0.0346   1.0000   0.0482
  -6.750  -0.4701   0.07401   0.07097  -0.0317   1.0000   0.0489
  -6.500  -0.4692   0.07156   0.06853  -0.0307   1.0000   0.0498
  -6.250  -0.4673   0.06871   0.06568  -0.0307   1.0000   0.0510
  -6.000  -0.4636   0.06534   0.06227  -0.0318   1.0000   0.0525
  -5.750  -0.4567   0.06129   0.05814  -0.0342   1.0000   0.0547
  -5.500  -0.4198   0.05125   0.04751  -0.0479   0.9954   0.0608
  -5.250  -0.3939   0.04837   0.04467  -0.0499   0.9920   0.0627
  -5.000  -0.3505   0.04653   0.04202  -0.0560   0.9866   0.0726
  -4.750  -0.3267   0.03999   0.03567  -0.0592   0.9843   0.0756
  -4.500  -0.2967   0.03750   0.03308  -0.0613   0.9800   0.0805
  -4.250  -0.2541   0.02728   0.02139  -0.0638   0.9778   0.0435
  -4.000  -0.2171   0.02321   0.01644  -0.0652   0.9753   0.0383
  -3.750  -0.1779   0.02197   0.01478  -0.0669   0.9722   0.0367
  -3.500  -0.1396   0.02038   0.01294  -0.0688   0.9697   0.0365
  -3.250  -0.1102   0.01876   0.01118  -0.0691   0.9646   0.0373
  -3.000  -0.0744   0.01757   0.01000  -0.0707   0.9607   0.0396
  -2.750  -0.0342   0.01685   0.00924  -0.0731   0.9575   0.0444
  -2.500  -0.0025   0.01611   0.00854  -0.0739   0.9516   0.0546
  -2.250   0.0333   0.01489   0.00766  -0.0756   0.9468   0.1301
  -2.000   0.0720   0.01380   0.00753  -0.0785   0.9435   0.3585
  -1.750   0.0987   0.01303   0.00758  -0.0785   0.9370   0.5689
  -1.500   0.1253   0.01251   0.00773  -0.0772   0.9313   0.7647
  -1.250   0.1588   0.01226   0.00763  -0.0771   0.9279   0.8773
  -1.000   0.2134   0.01199   0.00737  -0.0818   0.9246   0.9893
  -0.750   0.2513   0.01191   0.00714  -0.0838   0.9181   1.0000
  -0.500   0.2980   0.01174   0.00684  -0.0874   0.9148   1.0000
  -0.250   0.3299   0.01165   0.00666  -0.0881   0.9067   1.0000
   0.000   0.3697   0.01144   0.00637  -0.0902   0.9014   1.0000
   0.250   0.4030   0.01128   0.00614  -0.0909   0.8938   1.0000
   0.500   0.4381   0.01105   0.00585  -0.0919   0.8868   1.0000
   0.750   0.4679   0.01090   0.00565  -0.0919   0.8777   1.0000
   1.000   0.5027   0.01062   0.00532  -0.0927   0.8707   1.0000
   1.250   0.5296   0.01046   0.00514  -0.0920   0.8593   1.0000
   1.500   0.5582   0.01027   0.00493  -0.0917   0.8483   1.0000
   1.750   0.5874   0.01006   0.00470  -0.0914   0.8368   1.0000
   2.000   0.6157   0.00988   0.00448  -0.0909   0.8236   1.0000
   2.250   0.6427   0.00974   0.00432  -0.0902   0.8076   1.0000
   2.500   0.6697   0.00964   0.00420  -0.0895   0.7897   1.0000
   2.750   0.6977   0.00955   0.00406  -0.0890   0.7706   1.0000
   3.000   0.7243   0.00954   0.00399  -0.0884   0.7474   1.0000
   3.250   0.7511   0.00958   0.00394  -0.0877   0.7224   1.0000
   3.500   0.7770   0.00971   0.00397  -0.0869   0.6945   1.0000
   3.750   0.8021   0.00991   0.00405  -0.0861   0.6645   1.0000
   4.000   0.8264   0.01016   0.00418  -0.0851   0.6335   1.0000
   4.250   0.8501   0.01046   0.00435  -0.0841   0.6012   1.0000
   4.500   0.8732   0.01079   0.00457  -0.0830   0.5680   1.0000
   4.750   0.8956   0.01116   0.00480  -0.0819   0.5326   1.0000
   5.000   0.9174   0.01156   0.00506  -0.0807   0.4961   1.0000
   5.250   0.9389   0.01200   0.00536  -0.0795   0.4592   1.0000
   5.500   0.9598   0.01248   0.00571  -0.0782   0.4220   1.0000
   5.750   0.9804   0.01299   0.00607  -0.0769   0.3824   1.0000
   6.000   1.0003   0.01356   0.00648  -0.0756   0.3419   1.0000
   6.250   1.0196   0.01419   0.00692  -0.0743   0.3009   1.0000
   6.500   1.0388   0.01487   0.00744  -0.0729   0.2620   1.0000
   6.750   1.0581   0.01556   0.00798  -0.0717   0.2243   1.0000
   7.000   1.0764   0.01637   0.00860  -0.0703   0.1878   1.0000
   7.250   1.0941   0.01725   0.00930  -0.0689   0.1524   1.0000
   7.500   1.1107   0.01826   0.01013  -0.0673   0.1229   1.0000
   7.750   1.1270   0.01931   0.01109  -0.0656   0.1012   1.0000
   8.000   1.1427   0.02039   0.01211  -0.0638   0.0868   1.0000
   8.250   1.1580   0.02153   0.01322  -0.0619   0.0770   1.0000
   8.500   1.1724   0.02274   0.01438  -0.0601   0.0698   1.0000
   8.750   1.1898   0.02377   0.01551  -0.0585   0.0649   1.0000
   9.000   1.2067   0.02483   0.01663  -0.0569   0.0610   1.0000
   9.250   1.2232   0.02658   0.01833  -0.0556   0.0576   1.0000
   9.500   1.2435   0.02796   0.01985  -0.0545   0.0556   1.0000
   9.750   1.2632   0.02919   0.02123  -0.0534   0.0534   1.0000
  10.000   1.2818   0.03045   0.02262  -0.0523   0.0510   1.0000
  10.250   1.3001   0.03180   0.02405  -0.0512   0.0491   1.0000
  10.500   1.3216   0.03373   0.02607  -0.0507   0.0475   1.0000
  10.750   1.3468   0.03781   0.03037  -0.0513   0.0459   1.0000
  11.000   1.3602   0.03954   0.03238  -0.0495   0.0454   1.0000
  11.250   1.3715   0.04160   0.03474  -0.0475   0.0448   1.0000
  11.500   1.3785   0.04366   0.03712  -0.0451   0.0439   1.0000
  11.750   1.3805   0.04566   0.03940  -0.0421   0.0429   1.0000
  12.000   1.3797   0.04771   0.04170  -0.0390   0.0419   1.0000
  12.250   1.3770   0.04995   0.04419  -0.0360   0.0410   1.0000
  12.500   1.3783   0.05152   0.04589  -0.0338   0.0395   1.0000
  12.750   1.3773   0.05316   0.04762  -0.0317   0.0382   1.0000
  13.000   1.3787   0.05594   0.05042  -0.0305   0.0366   1.0000
  13.250   1.3578   0.06147   0.05625  -0.0285   0.0359   1.0000
  13.500   1.3393   0.06487   0.05991  -0.0268   0.0356   1.0000
  13.750   1.3224   0.06814   0.06344  -0.0260   0.0352   1.0000
  14.000   1.3033   0.07252   0.06806  -0.0262   0.0349   1.0000
  14.250   1.2816   0.07801   0.07379  -0.0275   0.0347   1.0000
  14.500   1.2576   0.08452   0.08053  -0.0300   0.0348   1.0000
  14.750   1.2308   0.09234   0.08855  -0.0337   0.0351   1.0000
  15.000   1.2014   0.10162   0.09801  -0.0387   0.0356   1.0000
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