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S7075 (9%) (s7075-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S7075 (9%) (s7075-il)
Reynolds number: 50,000
Max Cl/Cd: 38.83 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7075-il-50000.txt
Download as CSV file: xf-s7075-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3968   0.10380   0.09716  -0.0243   1.0000   0.2311
  -7.750  -0.3745   0.09867   0.09202  -0.0224   1.0000   0.2417
  -7.500  -0.4098   0.09970   0.09328  -0.0210   1.0000   0.2461
  -7.250  -0.3884   0.09488   0.08845  -0.0192   1.0000   0.2587
  -7.000  -0.3864   0.09191   0.08556  -0.0173   1.0000   0.2670
  -6.750  -0.4172   0.09212   0.08596  -0.0145   1.0000   0.2751
  -6.500  -0.4075   0.08865   0.08253  -0.0119   1.0000   0.2877
  -6.250  -0.4082   0.08608   0.08005  -0.0095   1.0000   0.3005
  -6.000  -0.4122   0.08382   0.07787  -0.0071   1.0000   0.3148
  -5.750  -0.4171   0.08165   0.07580  -0.0046   1.0000   0.3307
  -5.500  -0.4300   0.08004   0.07430  -0.0029   1.0000   0.3490
  -5.250  -0.4251   0.07710   0.07142   0.0005   1.0000   0.3681
  -5.000  -0.4244   0.07485   0.06922   0.0038   1.0000   0.3915
  -4.250  -0.3479   0.04691   0.03931  -0.0468   1.0000   0.1431
  -4.000  -0.3192   0.04192   0.03369  -0.0490   1.0000   0.1284
  -3.750  -0.2950   0.03844   0.02998  -0.0495   1.0000   0.1236
  -3.500  -0.2650   0.03488   0.02571  -0.0507   1.0000   0.1186
  -3.250  -0.2357   0.03218   0.02240  -0.0511   1.0000   0.1175
  -3.000  -0.2095   0.03033   0.02027  -0.0510   1.0000   0.1234
  -2.750  -0.1820   0.02853   0.01804  -0.0508   1.0000   0.1313
  -2.500  -0.1558   0.02707   0.01631  -0.0501   1.0000   0.1429
  -2.250  -0.1317   0.02567   0.01500  -0.0494   1.0000   0.1654
  -2.000  -0.1068   0.02432   0.01378  -0.0485   1.0000   0.2092
  -1.750  -0.0771   0.02192   0.01248  -0.0484   1.0000   0.3832
  -1.500  -0.0748   0.01915   0.01198  -0.0399   1.0000   1.0000
  -1.250  -0.0492   0.01940   0.01150  -0.0402   1.0000   1.0000
  -1.000  -0.0258   0.01969   0.01131  -0.0403   1.0000   1.0000
  -0.750  -0.0032   0.02003   0.01127  -0.0402   1.0000   1.0000
  -0.500   0.0188   0.02042   0.01134  -0.0401   1.0000   1.0000
  -0.250   0.0402   0.02085   0.01151  -0.0399   1.0000   1.0000
   0.000   0.0612   0.02133   0.01173  -0.0398   1.0000   1.0000
   0.250   0.0817   0.02185   0.01206  -0.0396   1.0000   1.0000
   0.500   0.1018   0.02243   0.01247  -0.0395   1.0000   1.0000
   0.750   0.1213   0.02307   0.01296  -0.0394   1.0000   1.0000
   1.000   0.1404   0.02376   0.01351  -0.0393   1.0000   1.0000
   1.250   0.1590   0.02451   0.01415  -0.0393   1.0000   1.0000
   1.500   0.1770   0.02534   0.01489  -0.0393   1.0000   1.0000
   1.750   0.1993   0.02632   0.01580  -0.0402   0.9976   1.0000
   2.000   0.2538   0.02798   0.01737  -0.0469   0.9783   1.0000
   2.250   0.3059   0.02945   0.01880  -0.0529   0.9587   1.0000
   2.500   0.3530   0.03067   0.02001  -0.0576   0.9386   1.0000
   2.750   0.3979   0.03171   0.02106  -0.0617   0.9176   1.0000
   3.000   0.4482   0.03266   0.02206  -0.0663   0.8979   1.0000
   3.250   0.4844   0.03334   0.02281  -0.0684   0.8753   1.0000
   3.500   0.5360   0.03385   0.02343  -0.0724   0.8554   1.0000
   3.750   0.5695   0.03428   0.02398  -0.0735   0.8321   1.0000
   4.000   0.6241   0.03419   0.02406  -0.0770   0.8123   1.0000
   4.250   0.6579   0.03428   0.02429  -0.0774   0.7879   1.0000
   4.500   0.7068   0.03369   0.02394  -0.0792   0.7659   1.0000
   4.750   0.7605   0.03251   0.02300  -0.0808   0.7436   1.0000
   5.000   0.8067   0.03130   0.02201  -0.0810   0.7193   1.0000
   5.250   0.8612   0.02938   0.02037  -0.0814   0.6941   1.0000
   5.500   0.9058   0.02792   0.01908  -0.0806   0.6630   1.0000
   5.750   0.9489   0.02660   0.01788  -0.0795   0.6265   1.0000
   6.000   0.9794   0.02620   0.01746  -0.0774   0.5845   1.0000
   6.250   1.0069   0.02612   0.01725  -0.0751   0.5389   1.0000
   6.500   1.0285   0.02649   0.01744  -0.0724   0.4905   1.0000
   6.750   1.0469   0.02714   0.01792  -0.0696   0.4401   1.0000
   7.000   1.0644   0.02804   0.01851  -0.0668   0.3895   1.0000
   7.250   1.0789   0.02927   0.01950  -0.0641   0.3397   1.0000
   7.500   1.0943   0.03075   0.02068  -0.0616   0.2938   1.0000
   7.750   1.1109   0.03256   0.02227  -0.0596   0.2542   1.0000
   8.000   1.1290   0.03446   0.02402  -0.0579   0.2221   1.0000
   8.250   1.1491   0.03670   0.02624  -0.0566   0.1978   1.0000
   8.500   1.1697   0.03884   0.02833  -0.0555   0.1785   1.0000
   8.750   1.1909   0.04166   0.03139  -0.0544   0.1662   1.0000
   9.000   1.2088   0.04464   0.03465  -0.0530   0.1567   1.0000
   9.250   1.2295   0.04736   0.03741  -0.0523   0.1472   1.0000
   9.500   1.2354   0.05069   0.04138  -0.0497   0.1422   1.0000
   9.750   1.2452   0.05428   0.04536  -0.0479   0.1387   1.0000
  10.000   1.2606   0.05803   0.04928  -0.0469   0.1356   1.0000
  10.250   1.2640   0.06249   0.05408  -0.0450   0.1340   1.0000
  10.500   1.2540   0.06688   0.05895  -0.0421   0.1335   1.0000
  10.750   1.2387   0.07143   0.06391  -0.0393   0.1332   1.0000
  11.000   1.2192   0.07612   0.06891  -0.0368   0.1333   1.0000
  11.250   1.1977   0.08076   0.07376  -0.0346   0.1337   1.0000
  11.500   1.1755   0.08579   0.07894  -0.0331   0.1342   1.0000
  11.750   1.0557   0.10003   0.09335  -0.0398   0.1463   1.0000
  12.000   1.0449   0.10756   0.10089  -0.0425   0.1479   1.0000
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