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SA7026 (sa7026-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SA7026 (sa7026-il)
Reynolds number: 200,000
Max Cl/Cd: 87.48 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7026-il-200000.txt
Download as CSV file: xf-sa7026-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7026                                          
  
 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  -0.3777   0.10099   0.09789  -0.0337   1.0000   0.0361
  -8.000  -0.3906   0.09961   0.09658  -0.0313   1.0000   0.0361
  -7.750  -0.4085   0.09869   0.09573  -0.0288   1.0000   0.0362
  -7.500  -0.4098   0.09580   0.09287  -0.0311   0.9983   0.0363
  -7.250  -0.4024   0.08870   0.08580  -0.0330   0.9955   0.0373
  -7.000  -0.3862   0.08536   0.08242  -0.0328   0.9929   0.0386
  -6.750  -0.3672   0.08140   0.07846  -0.0370   0.9882   0.0402
  -6.500  -0.3422   0.07652   0.07355  -0.0449   0.9839   0.0422
  -6.250  -0.3234   0.07165   0.06865  -0.0523   0.9768   0.0444
  -6.000  -0.2739   0.06309   0.05969  -0.0745   0.9701   0.0485
  -5.750  -0.2636   0.05647   0.05300  -0.0779   0.9630   0.0496
  -5.500  -0.2422   0.05352   0.05013  -0.0788   0.9599   0.0514
  -5.250  -0.2104   0.04994   0.04645  -0.0833   0.9574   0.0548
  -5.000  -0.1834   0.04492   0.04067  -0.0893   0.9482   0.0624
  -4.750  -0.1564   0.04097   0.03691  -0.0915   0.9457   0.0649
  -4.500  -0.1163   0.03751   0.03285  -0.0966   0.9433   0.0765
  -4.250  -0.1012   0.03509   0.03052  -0.0955   0.9353   0.0789
  -4.000  -0.0655   0.03229   0.02737  -0.0985   0.9322   0.0917
  -3.750  -0.0160   0.02536   0.01897  -0.0990   0.9306   0.0362
  -3.500   0.0079   0.02340   0.01667  -0.0983   0.9241   0.0364
  -3.250   0.0419   0.02064   0.01358  -0.0995   0.9208   0.0348
  -3.000   0.0811   0.01889   0.01159  -0.1013   0.9186   0.0341
  -2.750   0.1201   0.01755   0.01012  -0.1031   0.9167   0.0344
  -2.500   0.1434   0.01688   0.00939  -0.1021   0.9095   0.0354
  -2.250   0.1775   0.01584   0.00831  -0.1031   0.9057   0.0398
  -2.000   0.2140   0.01472   0.00740  -0.1045   0.9030   0.0982
  -1.750   0.2338   0.01349   0.00734  -0.1037   0.8954   0.4113
  -1.500   0.2594   0.01256   0.00726  -0.1029   0.8909   0.6526
  -1.250   0.3196   0.01161   0.00691  -0.1081   0.8906   1.0000
  -1.000   0.3480   0.01158   0.00668  -0.1080   0.8846   1.0000
  -0.750   0.3756   0.01152   0.00648  -0.1078   0.8779   1.0000
  -0.500   0.4087   0.01136   0.00617  -0.1084   0.8742   1.0000
  -0.250   0.4311   0.01142   0.00613  -0.1072   0.8650   1.0000
   0.000   0.4627   0.01125   0.00583  -0.1075   0.8608   1.0000
   0.250   0.4863   0.01128   0.00579  -0.1065   0.8516   1.0000
   0.500   0.5173   0.01107   0.00548  -0.1066   0.8467   1.0000
   0.750   0.5413   0.01107   0.00543  -0.1056   0.8370   1.0000
   1.000   0.5696   0.01095   0.00524  -0.1053   0.8301   1.0000
   1.250   0.5962   0.01087   0.00511  -0.1048   0.8216   1.0000
   1.500   0.6224   0.01084   0.00504  -0.1041   0.8127   1.0000
   1.750   0.6512   0.01070   0.00484  -0.1039   0.8054   1.0000
   2.000   0.6765   0.01069   0.00482  -0.1032   0.7946   1.0000
   2.250   0.7029   0.01064   0.00476  -0.1026   0.7842   1.0000
   2.500   0.7300   0.01057   0.00465  -0.1021   0.7737   1.0000
   2.750   0.7573   0.01050   0.00454  -0.1016   0.7626   1.0000
   3.000   0.7837   0.01047   0.00452  -0.1010   0.7499   1.0000
   3.250   0.8097   0.01049   0.00451  -0.1003   0.7364   1.0000
   3.500   0.8358   0.01052   0.00453  -0.0997   0.7221   1.0000
   3.750   0.8612   0.01058   0.00459  -0.0990   0.7063   1.0000
   4.000   0.8863   0.01067   0.00471  -0.0983   0.6888   1.0000
   4.250   0.9115   0.01076   0.00478  -0.0976   0.6701   1.0000
   4.500   0.9364   0.01089   0.00487  -0.0968   0.6498   1.0000
   4.750   0.9606   0.01105   0.00500  -0.0959   0.6273   1.0000
   5.000   0.9844   0.01127   0.00522  -0.0950   0.6038   1.0000
   5.250   1.0078   0.01152   0.00543  -0.0940   0.5794   1.0000
   5.500   1.0305   0.01182   0.00568  -0.0929   0.5533   1.0000
   5.750   1.0524   0.01216   0.00596  -0.0917   0.5251   1.0000
   6.000   1.0732   0.01256   0.00630  -0.0904   0.4938   1.0000
   6.250   1.0932   0.01301   0.00669  -0.0890   0.4612   1.0000
   6.500   1.1126   0.01351   0.00711  -0.0875   0.4298   1.0000
   6.750   1.1315   0.01404   0.00758  -0.0860   0.3976   1.0000
   7.000   1.1477   0.01468   0.00807  -0.0841   0.3565   1.0000
   7.250   1.1615   0.01545   0.00862  -0.0819   0.3073   1.0000
   7.500   1.1748   0.01630   0.00928  -0.0797   0.2613   1.0000
   7.750   1.1883   0.01718   0.00997  -0.0776   0.2162   1.0000
   8.000   1.1996   0.01825   0.01078  -0.0753   0.1677   1.0000
   8.250   1.2095   0.01947   0.01173  -0.0729   0.1179   1.0000
   8.500   1.2059   0.02164   0.01332  -0.0685   0.0483   1.0000
   8.750   1.2041   0.02372   0.01527  -0.0640   0.0287   1.0000
   9.000   1.2118   0.02503   0.01667  -0.0612   0.0238   1.0000
   9.250   1.2123   0.02687   0.01859  -0.0578   0.0208   1.0000
   9.500   1.2191   0.02834   0.02020  -0.0552   0.0197   1.0000
   9.750   1.2251   0.02998   0.02197  -0.0526   0.0187   1.0000
  10.000   1.2313   0.03175   0.02389  -0.0502   0.0177   1.0000
  10.250   1.2387   0.03360   0.02586  -0.0481   0.0170   1.0000
  10.500   1.2480   0.03555   0.02792  -0.0462   0.0166   1.0000
  10.750   1.2596   0.03765   0.03015  -0.0446   0.0163   1.0000
  11.000   1.2732   0.03996   0.03262  -0.0431   0.0160   1.0000
  11.250   1.2875   0.04250   0.03538  -0.0418   0.0159   1.0000
  11.500   1.2997   0.04546   0.03864  -0.0403   0.0161   1.0000
  11.750   1.3071   0.04893   0.04246  -0.0385   0.0164   1.0000
  12.000   1.3059   0.05281   0.04672  -0.0364   0.0168   1.0000
  12.250   1.2975   0.05705   0.05134  -0.0344   0.0173   1.0000
  12.500   1.2849   0.06146   0.05610  -0.0327   0.0178   1.0000
  12.750   1.2698   0.06606   0.06100  -0.0316   0.0182   1.0000
  13.000   1.2526   0.07105   0.06626  -0.0312   0.0185   1.0000
  13.250   1.2342   0.07637   0.07183  -0.0316   0.0188   1.0000
  13.500   1.2143   0.08219   0.07788  -0.0328   0.0191   1.0000
  13.750   1.1945   0.08831   0.08421  -0.0349   0.0193   1.0000
  14.000   1.1742   0.09500   0.09109  -0.0379   0.0195   1.0000
  14.250   1.1528   0.10250   0.09877  -0.0420   0.0196   1.0000
  14.500   1.1320   0.11058   0.10702  -0.0469   0.0197   1.0000
  14.750   1.1111   0.11954   0.11614  -0.0527   0.0198   1.0000
  15.000   1.0902   0.12945   0.12617  -0.0595   0.0200   1.0000
  15.250   1.0688   0.14056   0.13739  -0.0670   0.0201   1.0000
  15.500   1.0481   0.15265   0.14953  -0.0747   0.0205   1.0000
  15.750   1.0377   0.16451   0.16146  -0.0812   0.0224   1.0000
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