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SD7084 (9.6%) (sd7084-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD7084 (9.6%) (sd7084-il)
Reynolds number: 50,000
Max Cl/Cd: 31.27 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7084-il-50000.txt
Download as CSV file: xf-sd7084-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7084 (9.6%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3984   0.09801   0.09132  -0.0142   1.0000   0.2779
  -8.000  -0.3994   0.09528   0.08867  -0.0138   1.0000   0.2904
  -7.750  -0.3964   0.09244   0.08589  -0.0129   1.0000   0.3050
  -7.500  -0.3894   0.08947   0.08297  -0.0116   1.0000   0.3223
  -7.250  -0.3918   0.08726   0.08085  -0.0100   1.0000   0.3417
  -7.000  -0.4025   0.08562   0.07935  -0.0081   1.0000   0.3583
  -6.750  -0.3844   0.08162   0.07534  -0.0062   1.0000   0.3785
  -6.500  -0.3832   0.07913   0.07292  -0.0038   1.0000   0.3976
  -6.250  -0.4098   0.07870   0.07270   0.0005   1.0000   0.4169
  -5.250  -0.4525   0.05064   0.04350  -0.0322   1.0000   0.1564
  -5.000  -0.4385   0.04586   0.03818  -0.0322   1.0000   0.1420
  -4.750  -0.4229   0.04220   0.03432  -0.0313   1.0000   0.1363
  -4.500  -0.4042   0.03842   0.02965  -0.0306   1.0000   0.1278
  -4.250  -0.3848   0.03550   0.02637  -0.0295   1.0000   0.1259
  -4.000  -0.3637   0.03294   0.02337  -0.0285   1.0000   0.1252
  -3.750  -0.3413   0.03092   0.02073  -0.0273   1.0000   0.1284
  -3.500  -0.3200   0.02902   0.01881  -0.0263   1.0000   0.1359
  -3.250  -0.2958   0.02738   0.01674  -0.0252   1.0000   0.1418
  -3.000  -0.2719   0.02576   0.01509  -0.0241   1.0000   0.1511
  -2.750  -0.2478   0.02446   0.01374  -0.0231   1.0000   0.1735
  -2.500  -0.2228   0.02304   0.01244  -0.0221   1.0000   0.2136
  -2.250  -0.1486   0.01831   0.01118  -0.0249   1.0000   1.0000
  -2.000  -0.1368   0.01829   0.01067  -0.0231   1.0000   1.0000
  -1.750  -0.1225   0.01838   0.01035  -0.0216   1.0000   1.0000
  -1.500  -0.1069   0.01853   0.01014  -0.0203   1.0000   1.0000
  -1.250  -0.0906   0.01874   0.01001  -0.0192   1.0000   1.0000
  -1.000  -0.0739   0.01900   0.01000  -0.0181   1.0000   1.0000
  -0.750  -0.0571   0.01932   0.01007  -0.0172   1.0000   1.0000
  -0.500  -0.0403   0.01969   0.01022  -0.0164   1.0000   1.0000
  -0.250  -0.0235   0.02011   0.01042  -0.0157   1.0000   1.0000
   0.000  -0.0069   0.02059   0.01073  -0.0150   1.0000   1.0000
   0.250   0.0094   0.02113   0.01112  -0.0144   1.0000   1.0000
   0.500   0.0255   0.02174   0.01159  -0.0140   1.0000   1.0000
   0.750   0.0413   0.02241   0.01215  -0.0136   1.0000   1.0000
   1.000   0.0994   0.02389   0.01346  -0.0211   0.9820   1.0000
   1.250   0.1569   0.02515   0.01462  -0.0282   0.9599   1.0000
   1.500   0.2103   0.02618   0.01558  -0.0340   0.9374   1.0000
   1.750   0.2677   0.02706   0.01644  -0.0402   0.9155   1.0000
   2.000   0.3119   0.02765   0.01703  -0.0436   0.8916   1.0000
   2.250   0.3641   0.02807   0.01749  -0.0480   0.8692   1.0000
   2.500   0.4122   0.02829   0.01776  -0.0513   0.8461   1.0000
   2.750   0.4576   0.02836   0.01792  -0.0539   0.8228   1.0000
   3.000   0.5143   0.02794   0.01763  -0.0575   0.8021   1.0000
   3.250   0.5517   0.02776   0.01756  -0.0580   0.7781   1.0000
   3.500   0.6033   0.02691   0.01683  -0.0596   0.7582   1.0000
   3.750   0.6347   0.02672   0.01671  -0.0588   0.7332   1.0000
   4.000   0.6688   0.02637   0.01644  -0.0580   0.7089   1.0000
   4.250   0.7067   0.02581   0.01596  -0.0573   0.6857   1.0000
   4.500   0.7356   0.02574   0.01593  -0.0559   0.6599   1.0000
   4.750   0.7617   0.02592   0.01614  -0.0543   0.6335   1.0000
   5.000   0.7876   0.02619   0.01647  -0.0528   0.6077   1.0000
   5.250   0.8142   0.02651   0.01678  -0.0513   0.5832   1.0000
   5.500   0.8402   0.02691   0.01717  -0.0499   0.5589   1.0000
   5.750   0.8615   0.02771   0.01803  -0.0484   0.5346   1.0000
   6.000   0.8861   0.02834   0.01872  -0.0470   0.5121   1.0000
   6.250   0.9081   0.02920   0.01965  -0.0456   0.4898   1.0000
   6.500   0.9309   0.03007   0.02057  -0.0442   0.4687   1.0000
   6.750   0.9518   0.03106   0.02167  -0.0428   0.4475   1.0000
   7.000   0.9758   0.03194   0.02257  -0.0415   0.4276   1.0000
   7.250   0.9934   0.03322   0.02408  -0.0398   0.4069   1.0000
   7.500   1.0172   0.03413   0.02502  -0.0385   0.3870   1.0000
   7.750   1.0339   0.03550   0.02659  -0.0368   0.3667   1.0000
   8.000   1.0549   0.03653   0.02770  -0.0352   0.3456   1.0000
   8.250   1.0721   0.03784   0.02916  -0.0333   0.3244   1.0000
   8.500   1.0960   0.03846   0.02973  -0.0318   0.3000   1.0000
   8.750   1.1078   0.03975   0.03125  -0.0293   0.2756   1.0000
   9.000   1.1231   0.04053   0.03203  -0.0269   0.2473   1.0000
   9.250   1.1392   0.04092   0.03217  -0.0244   0.2147   1.0000
   9.500   1.1439   0.04213   0.03343  -0.0211   0.1842   1.0000
   9.750   1.1481   0.04358   0.03481  -0.0178   0.1557   1.0000
  10.000   1.1551   0.04536   0.03636  -0.0151   0.1320   1.0000
  10.250   1.1569   0.04797   0.03915  -0.0123   0.1168   1.0000
  10.500   1.1631   0.05087   0.04211  -0.0101   0.1052   1.0000
  10.750   1.1618   0.05395   0.04557  -0.0075   0.0979   1.0000
  11.000   1.1629   0.05755   0.04932  -0.0055   0.0925   1.0000
  11.250   1.1492   0.06148   0.05367  -0.0027   0.0912   1.0000
  11.500   1.1312   0.06542   0.05793  -0.0001   0.0907   1.0000
  11.750   1.1086   0.06982   0.06259   0.0015   0.0906   1.0000
  12.000   1.0844   0.07476   0.06776   0.0017   0.0911   1.0000
  12.250   1.0586   0.08050   0.07368   0.0005   0.0920   1.0000
  12.500   1.0339   0.08697   0.08023  -0.0020   0.0929   1.0000
  12.750   1.0114   0.09409   0.08743  -0.0053   0.0938   1.0000
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