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E176 (8.83%) (e176-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E176 (8.83%) (e176-il)
Reynolds number: 50,000
Max Cl/Cd: 38.69 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e176-il-50000-n5.txt
Download as CSV file: xf-e176-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E176  (8.83%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3942   0.10489   0.09825  -0.0191   1.0000   0.1067
  -8.500  -0.3906   0.10170   0.09512  -0.0207   1.0000   0.1087
  -8.250  -0.3991   0.09965   0.09321  -0.0244   1.0000   0.1133
  -7.750  -0.3931   0.08774   0.08137  -0.0316   1.0000   0.0587
  -7.500  -0.3871   0.08418   0.07787  -0.0325   1.0000   0.0575
  -7.250  -0.3834   0.08036   0.07412  -0.0351   1.0000   0.0570
  -7.000  -0.3787   0.07657   0.07039  -0.0374   1.0000   0.0557
  -6.750  -0.3745   0.07258   0.06645  -0.0401   1.0000   0.0549
  -6.500  -0.3706   0.06855   0.06241  -0.0425   1.0000   0.0540
  -6.250  -0.3678   0.06466   0.05853  -0.0443   1.0000   0.0526
  -6.000  -0.3668   0.06079   0.05464  -0.0454   1.0000   0.0514
  -5.750  -0.3673   0.05694   0.05068  -0.0460   1.0000   0.0497
  -5.250  -0.3304   0.04711   0.03986  -0.0529   0.9864   0.0462
  -5.000  -0.2971   0.04262   0.03490  -0.0571   0.9746   0.0459
  -4.750  -0.2625   0.03861   0.03031  -0.0607   0.9636   0.0457
  -4.500  -0.2256   0.03507   0.02614  -0.0639   0.9541   0.0459
  -4.250  -0.1890   0.03215   0.02259  -0.0663   0.9445   0.0463
  -4.000  -0.1543   0.02964   0.01967  -0.0681   0.9346   0.0475
  -3.750  -0.1190   0.02789   0.01770  -0.0700   0.9257   0.0517
  -3.500  -0.0841   0.02642   0.01580  -0.0712   0.9162   0.0577
  -3.250  -0.0517   0.02498   0.01412  -0.0718   0.9063   0.0620
  -3.000  -0.0173   0.02377   0.01271  -0.0728   0.8977   0.0696
  -2.750   0.0147   0.02272   0.01148  -0.0734   0.8881   0.0862
  -2.500   0.0440   0.02153   0.01063  -0.0741   0.8782   0.1528
  -2.250   0.0711   0.01988   0.01009  -0.0746   0.8697   0.3625
  -2.000   0.0881   0.01858   0.01001  -0.0715   0.8603   0.6549
  -1.750   0.1540   0.01778   0.00922  -0.0770   0.8554   1.0000
  -1.500   0.1810   0.01794   0.00894  -0.0769   0.8454   1.0000
  -1.250   0.2065   0.01815   0.00879  -0.0766   0.8352   1.0000
  -1.000   0.2333   0.01834   0.00866  -0.0765   0.8263   1.0000
  -0.750   0.2595   0.01855   0.00857  -0.0762   0.8174   1.0000
  -0.500   0.2842   0.01882   0.00860  -0.0758   0.8080   1.0000
  -0.250   0.3115   0.01902   0.00857  -0.0756   0.8005   1.0000
   0.000   0.3356   0.01933   0.00871  -0.0751   0.7912   1.0000
   0.250   0.3611   0.01961   0.00882  -0.0747   0.7831   1.0000
   0.500   0.3873   0.01989   0.00895  -0.0745   0.7752   1.0000
   0.750   0.4122   0.02024   0.00919  -0.0742   0.7668   1.0000
   1.000   0.4391   0.02051   0.00934  -0.0739   0.7599   1.0000
   1.250   0.4631   0.02092   0.00970  -0.0735   0.7512   1.0000
   1.500   0.4904   0.02117   0.00987  -0.0732   0.7449   1.0000
   1.750   0.5137   0.02165   0.01032  -0.0728   0.7359   1.0000
   2.000   0.5406   0.02193   0.01058  -0.0725   0.7296   1.0000
   2.250   0.5639   0.02243   0.01109  -0.0721   0.7208   1.0000
   2.500   0.5896   0.02280   0.01146  -0.0717   0.7137   1.0000
   2.750   0.6139   0.02324   0.01194  -0.0712   0.7055   1.0000
   3.000   0.6382   0.02370   0.01248  -0.0708   0.6975   1.0000
   3.250   0.6637   0.02407   0.01290  -0.0703   0.6900   1.0000
   3.500   0.6866   0.02461   0.01353  -0.0698   0.6808   1.0000
   3.750   0.7140   0.02483   0.01381  -0.0692   0.6741   1.0000
   4.000   0.7358   0.02542   0.01453  -0.0685   0.6635   1.0000
   4.250   0.7593   0.02587   0.01515  -0.0678   0.6537   1.0000
   4.500   0.7869   0.02598   0.01537  -0.0671   0.6457   1.0000
   4.750   0.8089   0.02647   0.01601  -0.0662   0.6339   1.0000
   5.000   0.8317   0.02685   0.01656  -0.0652   0.6219   1.0000
   5.250   0.8552   0.02711   0.01706  -0.0641   0.6094   1.0000
   5.500   0.8791   0.02728   0.01741  -0.0630   0.5961   1.0000
   5.750   0.9029   0.02737   0.01770  -0.0617   0.5817   1.0000
   6.000   0.9268   0.02736   0.01790  -0.0603   0.5660   1.0000
   6.250   0.9516   0.02716   0.01791  -0.0587   0.5489   1.0000
   6.500   0.9724   0.02720   0.01825  -0.0570   0.5278   1.0000
   6.750   0.9954   0.02691   0.01817  -0.0551   0.5046   1.0000
   7.000   1.0148   0.02689   0.01837  -0.0531   0.4760   1.0000
   7.250   1.0325   0.02697   0.01866  -0.0509   0.4402   1.0000
   7.500   1.0489   0.02711   0.01886  -0.0484   0.3941   1.0000
   7.750   1.0606   0.02772   0.01930  -0.0457   0.3310   1.0000
   8.000   1.0650   0.02917   0.02028  -0.0427   0.2625   1.0000
   8.250   1.0630   0.03139   0.02209  -0.0400   0.2030   1.0000
   8.500   1.0572   0.03396   0.02421  -0.0374   0.1505   1.0000
   8.750   1.0496   0.03664   0.02647  -0.0351   0.1092   1.0000
   9.000   1.0448   0.03945   0.02901  -0.0333   0.0806   1.0000
   9.250   1.0428   0.04226   0.03174  -0.0318   0.0640   1.0000
   9.500   1.0421   0.04511   0.03457  -0.0305   0.0551   1.0000
   9.750   1.0444   0.04777   0.03731  -0.0293   0.0489   1.0000
  10.000   1.0491   0.05035   0.03997  -0.0279   0.0447   1.0000
  10.250   1.0582   0.05262   0.04245  -0.0267   0.0403   1.0000
  10.500   1.0647   0.05511   0.04498  -0.0258   0.0369   1.0000
  10.750   1.0786   0.05735   0.04745  -0.0244   0.0341   1.0000
  11.000   1.0951   0.05974   0.05019  -0.0230   0.0320   1.0000
  11.250   1.1078   0.06272   0.05351  -0.0219   0.0307   1.0000
  11.500   1.1142   0.06615   0.05733  -0.0212   0.0300   1.0000
  11.750   1.1147   0.07005   0.06154  -0.0210   0.0294   1.0000
  12.000   1.1107   0.07436   0.06615  -0.0214   0.0292   1.0000
  12.250   1.1024   0.07915   0.07123  -0.0223   0.0290   1.0000
  12.500   1.0905   0.08451   0.07686  -0.0238   0.0289   1.0000
  12.750   1.0755   0.09049   0.08310  -0.0262   0.0290   1.0000
  13.000   1.0580   0.09724   0.09008  -0.0295   0.0292   1.0000
  13.250   1.0374   0.10499   0.09804  -0.0338   0.0295   1.0000
  13.500   1.0155   0.11388   0.10711  -0.0393   0.0300   1.0000
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