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GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 377 AIRFOIL (goe377-il)
Reynolds number: 200,000
Max Cl/Cd: 77.91 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe377-il-200000.txt
Download as CSV file: xf-goe377-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 377 AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3693   0.08807   0.08471  -0.0237   1.0000   0.0299
  -7.250  -0.3755   0.08593   0.08265  -0.0228   1.0000   0.0307
  -7.000  -0.3782   0.08352   0.08030  -0.0227   1.0000   0.0311
  -6.750  -0.3808   0.08105   0.07787  -0.0229   1.0000   0.0322
  -6.500  -0.3826   0.07868   0.07554  -0.0231   1.0000   0.0329
  -6.250  -0.3821   0.07637   0.07322  -0.0242   1.0000   0.0339
  -6.000  -0.3763   0.07416   0.07099  -0.0266   1.0000   0.0347
  -5.750  -0.3635   0.07217   0.06888  -0.0298   1.0000   0.0353
  -5.500  -0.3547   0.06943   0.06607  -0.0301   1.0000   0.0355
  -5.250  -0.3545   0.06368   0.06031  -0.0302   1.0000   0.0361
  -5.000  -0.3541   0.06021   0.05690  -0.0279   1.0000   0.0370
  -4.750  -0.3487   0.05756   0.05426  -0.0264   1.0000   0.0380
  -4.500  -0.3198   0.05387   0.05047  -0.0301   0.9967   0.0398
  -4.250  -0.2827   0.04976   0.04620  -0.0353   0.9923   0.0430
  -4.000  -0.2255   0.04706   0.04289  -0.0420   0.9868   0.0481
  -3.750  -0.1989   0.04025   0.03600  -0.0458   0.9834   0.0500
  -3.500  -0.1726   0.03770   0.03342  -0.0474   0.9776   0.0535
  -3.250  -0.1313   0.03429   0.02947  -0.0507   0.9728   0.0637
  -3.000  -0.0972   0.03159   0.02676  -0.0534   0.9696   0.0679
  -2.750  -0.0660   0.02916   0.02387  -0.0542   0.9623   0.0784
  -2.500  -0.0284   0.02715   0.02155  -0.0565   0.9582   0.0920
  -2.250   0.0018   0.02519   0.01958  -0.0580   0.9526   0.1090
  -2.000   0.0355   0.02379   0.01793  -0.0594   0.9467   0.1350
  -1.750   0.0819   0.01863   0.01149  -0.0586   0.9446   0.0644
  -1.500   0.1204   0.01714   0.00975  -0.0603   0.9405   0.0650
  -1.250   0.1550   0.01626   0.00880  -0.0614   0.9336   0.0697
  -1.000   0.2025   0.01516   0.00754  -0.0648   0.9300   0.0732
  -0.750   0.2418   0.01432   0.00663  -0.0665   0.9214   0.0759
  -0.500   0.2844   0.01320   0.00562  -0.0691   0.9157   0.0834
  -0.250   0.3157   0.01268   0.00507  -0.0693   0.9056   0.0898
   0.000   0.3488   0.01200   0.00447  -0.0699   0.8970   0.1026
   0.250   0.3722   0.01039   0.00407  -0.0690   0.8871   0.4623
   0.500   0.4753   0.00899   0.00364  -0.0847   0.8859   1.0000
   0.750   0.5018   0.00892   0.00347  -0.0839   0.8713   1.0000
   1.000   0.5266   0.00889   0.00335  -0.0828   0.8551   1.0000
   1.250   0.5512   0.00886   0.00325  -0.0817   0.8378   1.0000
   1.500   0.5762   0.00884   0.00316  -0.0807   0.8198   1.0000
   1.750   0.6014   0.00884   0.00308  -0.0797   0.8008   1.0000
   2.000   0.6254   0.00888   0.00305  -0.0786   0.7795   1.0000
   2.250   0.6499   0.00895   0.00301  -0.0775   0.7574   1.0000
   2.500   0.6739   0.00905   0.00303  -0.0763   0.7333   1.0000
   2.750   0.6973   0.00919   0.00307  -0.0751   0.7077   1.0000
   3.000   0.7205   0.00936   0.00315  -0.0739   0.6816   1.0000
   3.250   0.7431   0.00957   0.00324  -0.0725   0.6531   1.0000
   3.500   0.7651   0.00982   0.00339  -0.0711   0.6225   1.0000
   3.750   0.7866   0.01010   0.00354  -0.0696   0.5903   1.0000
   4.000   0.8077   0.01041   0.00372  -0.0681   0.5568   1.0000
   4.250   0.8286   0.01077   0.00394  -0.0666   0.5236   1.0000
   4.500   0.8492   0.01114   0.00419  -0.0651   0.4895   1.0000
   4.750   0.8698   0.01152   0.00450  -0.0636   0.4556   1.0000
   5.000   0.8904   0.01193   0.00479  -0.0622   0.4250   1.0000
   5.250   0.9111   0.01235   0.00512  -0.0608   0.3967   1.0000
   5.500   0.9314   0.01279   0.00546  -0.0594   0.3683   1.0000
   5.750   0.9516   0.01324   0.00582  -0.0580   0.3406   1.0000
   6.000   0.9718   0.01369   0.00623  -0.0567   0.3127   1.0000
   6.250   0.9923   0.01412   0.00663  -0.0554   0.2860   1.0000
   6.500   1.0124   0.01457   0.00704  -0.0541   0.2558   1.0000
   6.750   1.0302   0.01523   0.00750  -0.0525   0.1972   1.0000
   7.000   1.0314   0.01786   0.00904  -0.0486   0.0497   1.0000
   7.250   1.0465   0.01910   0.01037  -0.0462   0.0380   1.0000
   7.500   1.0599   0.02036   0.01176  -0.0438   0.0327   1.0000
   7.750   1.0758   0.02133   0.01284  -0.0418   0.0296   1.0000
   8.000   1.0890   0.02255   0.01414  -0.0394   0.0274   1.0000
   8.250   1.1001   0.02404   0.01569  -0.0368   0.0262   1.0000
   8.500   1.1110   0.02605   0.01774  -0.0342   0.0252   1.0000
   8.750   1.1284   0.02893   0.02069  -0.0327   0.0246   1.0000
   9.000   1.1481   0.03065   0.02257  -0.0314   0.0241   1.0000
   9.250   1.1646   0.03184   0.02402  -0.0296   0.0224   1.0000
   9.500   1.1834   0.03441   0.02684  -0.0283   0.0224   1.0000
   9.750   1.1989   0.03738   0.03013  -0.0266   0.0224   1.0000
  10.000   1.2099   0.04071   0.03381  -0.0244   0.0228   1.0000
  10.250   1.2160   0.04453   0.03797  -0.0220   0.0234   1.0000
  10.500   1.2259   0.05031   0.04400  -0.0207   0.0248   1.0000
  10.750   1.2140   0.05204   0.04650  -0.0145   0.0285   1.0000
  11.000   1.1967   0.05675   0.05157  -0.0103   0.0312   1.0000
  11.250   1.1066   0.04975   0.04495  -0.0013   0.0291   1.0000
  11.500   1.0823   0.05437   0.04983   0.0009   0.0300   1.0000
  11.750   1.0581   0.05923   0.05489   0.0019   0.0305   1.0000
  12.000   1.0336   0.06449   0.06035   0.0018   0.0308   1.0000
  12.250   1.0086   0.07018   0.06621   0.0006   0.0308   1.0000
  12.500   0.9824   0.07650   0.07269  -0.0016   0.0306   1.0000
  12.750   0.9567   0.08324   0.07959  -0.0048   0.0303   1.0000
  13.000   0.9306   0.09050   0.08699  -0.0090   0.0299   1.0000
  13.250   0.9038   0.09841   0.09503  -0.0140   0.0294   1.0000
  13.500   0.8762   0.10697   0.10369  -0.0197   0.0290   1.0000
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