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GOE 391 AIRFOIL (goe391-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 391 AIRFOIL (goe391-il)
Reynolds number: 1,000,000
Max Cl/Cd: 86.88 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe391-il-1000000-n5.txt
Download as CSV file: xf-goe391-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 391 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4158   0.10011   0.09847  -0.0201   1.0000   0.0040
  -8.500  -0.4148   0.09742   0.09580  -0.0201   1.0000   0.0039
  -8.250  -0.4154   0.09482   0.09323  -0.0198   1.0000   0.0040
  -8.000  -0.4131   0.09174   0.09016  -0.0207   0.9997   0.0047
  -7.500  -0.3916   0.08271   0.08114  -0.0298   0.9945   0.0027
  -7.250  -0.2930   0.05793   0.05646  -0.0419   0.9879   0.0029
  -7.000  -0.2841   0.05299   0.05151  -0.0471   0.9836   0.0029
  -6.750  -0.2705   0.04780   0.04631  -0.0533   0.9806   0.0031
  -6.500  -0.2514   0.04277   0.04124  -0.0595   0.9787   0.0031
  -6.250  -0.2822   0.05723   0.05553  -0.0642   0.9796   0.0027
  -6.000  -0.2505   0.05095   0.04915  -0.0720   0.9779   0.0030
  -5.750  -0.2261   0.04750   0.04563  -0.0754   0.9736   0.0032
  -5.500  -0.1972   0.04429   0.04233  -0.0792   0.9706   0.0036
  -5.250  -0.1643   0.03938   0.03726  -0.0839   0.9677   0.0039
  -5.000  -0.1385   0.03487   0.03258  -0.0859   0.9606   0.0040
  -4.500  -0.1006   0.01098   0.00662  -0.0842   0.9438   0.0041
  -4.250  -0.0743   0.00974   0.00510  -0.0839   0.9392   0.0045
  -4.000  -0.0485   0.00911   0.00431  -0.0835   0.9334   0.0049
  -3.750  -0.0216   0.00833   0.00334  -0.0833   0.9277   0.0055
  -3.500   0.0041   0.00796   0.00290  -0.0828   0.9192   0.0064
  -3.250   0.0311   0.00768   0.00254  -0.0826   0.9118   0.0075
  -3.000   0.0571   0.00730   0.00206  -0.0821   0.9038   0.0090
  -2.750   0.0840   0.00714   0.00190  -0.0819   0.8967   0.0116
  -2.500   0.1112   0.00709   0.00188  -0.0817   0.8892   0.0153
  -2.250   0.1392   0.00722   0.00201  -0.0817   0.8825   0.0199
  -2.000   0.1665   0.00727   0.00202  -0.0816   0.8742   0.0223
  -1.750   0.1939   0.00744   0.00215  -0.0814   0.8626   0.0236
  -1.500   0.2203   0.00747   0.00212  -0.0811   0.8484   0.0240
  -1.250   0.2451   0.00712   0.00168  -0.0804   0.8338   0.0252
  -1.000   0.2706   0.00688   0.00137  -0.0799   0.8224   0.0261
  -0.750   0.2965   0.00674   0.00117  -0.0795   0.8113   0.0262
  -0.500   0.3223   0.00664   0.00101  -0.0790   0.7977   0.0260
  -0.250   0.3477   0.00658   0.00086  -0.0784   0.7800   0.0259
   0.000   0.3708   0.00664   0.00074  -0.0773   0.7365   0.0258
   0.250   0.3888   0.00703   0.00070  -0.0752   0.6371   0.0259
   0.500   0.4103   0.00732   0.00070  -0.0739   0.5695   0.0263
   0.750   0.4340   0.00749   0.00067  -0.0731   0.5230   0.0280
   1.000   0.4568   0.00777   0.00071  -0.0721   0.4580   0.0316
   1.250   0.4768   0.00838   0.00086  -0.0708   0.3409   0.0352
   1.750   0.5257   0.00850   0.00106  -0.0697   0.2827   0.1742
   2.250   0.6035   0.00757   0.00156  -0.0762   0.1537   1.0000
   2.500   0.6271   0.00777   0.00169  -0.0753   0.1359   1.0000
   2.750   0.6486   0.00819   0.00187  -0.0742   0.0816   1.0000
   3.000   0.6707   0.00857   0.00207  -0.0731   0.0429   1.0000
   3.250   0.6945   0.00877   0.00225  -0.0723   0.0361   1.0000
   3.500   0.7188   0.00893   0.00240  -0.0716   0.0330   1.0000
   3.750   0.7431   0.00910   0.00258  -0.0709   0.0313   1.0000
   4.000   0.7670   0.00931   0.00280  -0.0702   0.0290   1.0000
   4.250   0.7910   0.00953   0.00304  -0.0694   0.0278   1.0000
   4.500   0.8148   0.00977   0.00330  -0.0686   0.0264   1.0000
   4.750   0.8380   0.01009   0.00367  -0.0678   0.0241   1.0000
   5.250   0.8868   0.01042   0.00405  -0.0666   0.0229   1.0000
   5.500   0.9115   0.01057   0.00421  -0.0661   0.0215   1.0000
   5.750   0.9357   0.01077   0.00442  -0.0655   0.0171   1.0000
   6.000   0.9582   0.01117   0.00471  -0.0646   0.0087   1.0000
   6.250   0.9811   0.01154   0.00512  -0.0637   0.0063   1.0000
   6.500   1.0032   0.01202   0.00565  -0.0627   0.0049   1.0000
   6.750   1.0259   0.01240   0.00610  -0.0618   0.0043   1.0000
   7.000   1.0483   0.01284   0.00659  -0.0609   0.0038   1.0000
   7.250   1.0695   0.01342   0.00723  -0.0598   0.0032   1.0000
   7.500   1.0903   0.01407   0.00797  -0.0586   0.0030   1.0000
   7.750   1.1117   0.01462   0.00861  -0.0575   0.0027   1.0000
   8.000   1.1333   0.01511   0.00917  -0.0566   0.0025   1.0000
   8.250   1.1543   0.01569   0.00982  -0.0555   0.0022   1.0000
   8.500   1.1743   0.01640   0.01066  -0.0543   0.0021   1.0000
   8.750   1.1937   0.01717   0.01152  -0.0530   0.0019   1.0000
   9.000   1.2111   0.01821   0.01269  -0.0514   0.0018   1.0000
   9.250   1.2270   0.01943   0.01409  -0.0495   0.0017   1.0000
   9.500   1.2455   0.02026   0.01504  -0.0482   0.0016   1.0000
   9.750   1.2618   0.02139   0.01635  -0.0465   0.0016   1.0000
  10.000   1.2772   0.02260   0.01774  -0.0447   0.0014   1.0000
  10.250   1.2914   0.02389   0.01922  -0.0427   0.0014   1.0000
  10.500   1.3036   0.02538   0.02092  -0.0406   0.0013   1.0000
  10.750   1.3125   0.02718   0.02296  -0.0380   0.0013   1.0000
  11.000   1.3198   0.02899   0.02500  -0.0353   0.0012   1.0000
  11.250   1.3223   0.03093   0.02717  -0.0319   0.0012   1.0000
  11.500   1.3273   0.03216   0.02854  -0.0288   0.0011   1.0000
  11.750   1.3134   0.03529   0.03200  -0.0237   0.0011   1.0000
  12.000   1.3113   0.03715   0.03402  -0.0205   0.0010   1.0000
  12.250   1.2953   0.04048   0.03763  -0.0166   0.0011   1.0000
  12.500   1.2887   0.04294   0.04024  -0.0142   0.0010   1.0000
  12.750   1.2516   0.04913   0.04679  -0.0115   0.0011   1.0000
  13.000   1.2266   0.05468   0.05257  -0.0114   0.0011   1.0000
  13.250   1.2237   0.05775   0.05571  -0.0121   0.0010   1.0000
  13.500   1.1885   0.06698   0.06517  -0.0167   0.0011   1.0000
  13.750   1.1642   0.07652   0.07487  -0.0232   0.0010   1.0000
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