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GOE 746 AIRFOIL (goe746-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 746 AIRFOIL (goe746-il)
Reynolds number: 500,000
Max Cl/Cd: 102.39 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe746-il-500000-n5.txt
Download as CSV file: xf-goe746-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 746 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4207   0.09942   0.09594   0.0186   0.5456   0.0087
  -8.500  -0.4186   0.09571   0.09223   0.0168   0.5428   0.0087
  -8.250  -0.4193   0.09163   0.08817   0.0149   0.5401   0.0089
  -8.000  -0.4152   0.08900   0.08555   0.0136   0.5367   0.0090
  -7.750  -0.4053   0.08768   0.08421   0.0128   0.5329   0.0095
  -7.500  -0.4092   0.08434   0.08088   0.0113   0.5304   0.0094
  -7.250  -0.4039   0.08132   0.07784   0.0092   0.5279   0.0097
  -7.000  -0.3966   0.07793   0.07444   0.0068   0.5255   0.0101
  -6.750  -0.3885   0.07394   0.07043   0.0040   0.5231   0.0106
  -6.500  -0.3791   0.06934   0.06578   0.0009   0.5207   0.0109
  -6.250  -0.3705   0.06220   0.05854  -0.0036   0.5189   0.0115
  -6.000  -0.3541   0.05847   0.05472  -0.0057   0.5160   0.0119
  -5.750  -0.3347   0.05636   0.05253  -0.0069   0.5129   0.0122
  -5.500  -0.3144   0.05403   0.05012  -0.0080   0.5103   0.0129
  -5.250  -0.2943   0.05004   0.04600  -0.0097   0.5081   0.0137
  -5.000  -0.2754   0.04077   0.03636  -0.0120   0.5067   0.0152
  -4.750  -0.2524   0.03936   0.03487  -0.0122   0.5038   0.0155
  -4.500  -0.2288   0.03814   0.03354  -0.0124   0.5008   0.0161
  -4.000  -0.1854   0.02677   0.02125  -0.0110   0.4966   0.0196
  -3.750  -0.1605   0.02625   0.02067  -0.0109   0.4940   0.0200
  -3.500  -0.1353   0.02554   0.01988  -0.0108   0.4913   0.0206
  -3.250  -0.1106   0.02384   0.01796  -0.0102   0.4887   0.0214
  -3.000  -0.0858   0.02164   0.01542  -0.0094   0.4862   0.0223
  -2.750  -0.0600   0.01975   0.01316  -0.0085   0.4837   0.0237
  -2.500  -0.0334   0.01863   0.01173  -0.0079   0.4812   0.0243
  -2.250  -0.0065   0.01786   0.01074  -0.0074   0.4787   0.0247
  -2.000   0.0193   0.01614   0.00878  -0.0069   0.4762   0.0251
  -1.750   0.0462   0.01529   0.00783  -0.0067   0.4736   0.0257
  -1.500   0.0735   0.01476   0.00721  -0.0066   0.4709   0.0264
  -1.250   0.1010   0.01416   0.00649  -0.0063   0.4683   0.0267
  -1.000   0.1287   0.01363   0.00585  -0.0061   0.4657   0.0270
  -0.750   0.1565   0.01314   0.00531  -0.0060   0.4633   0.0275
  -0.500   0.1843   0.01272   0.00484  -0.0058   0.4607   0.0279
  -0.250   0.2120   0.01235   0.00442  -0.0056   0.4579   0.0283
   0.000   0.2395   0.01202   0.00405  -0.0054   0.4551   0.0287
   0.250   0.2670   0.01174   0.00373  -0.0052   0.4525   0.0290
   0.500   0.2944   0.01152   0.00348  -0.0051   0.4501   0.0296
   0.750   0.3219   0.01131   0.00327  -0.0049   0.4473   0.0303
   1.000   0.3492   0.01109   0.00306  -0.0047   0.4443   0.0305
   1.250   0.3764   0.01090   0.00286  -0.0045   0.4413   0.0307
   1.500   0.4037   0.01076   0.00269  -0.0043   0.4384   0.0310
   1.750   0.4309   0.01065   0.00256  -0.0041   0.4354   0.0313
   2.000   0.4585   0.01054   0.00247  -0.0040   0.4313   0.0317
   2.250   0.4858   0.01043   0.00237  -0.0038   0.4265   0.0323
   2.500   0.5131   0.01036   0.00225  -0.0037   0.4222   0.0336
   2.750   0.5407   0.01033   0.00222  -0.0036   0.4187   0.0349
   3.000   0.5684   0.01031   0.00222  -0.0035   0.4148   0.0362
   3.250   0.5959   0.01030   0.00223  -0.0035   0.4108   0.0389
   3.750   0.6505   0.01026   0.00232  -0.0033   0.4035   0.1012
   4.250   0.7589   0.00869   0.00279  -0.0150   0.3926   0.9916
   4.500   0.8160   0.00875   0.00286  -0.0215   0.3871   0.9996
   4.750   0.8445   0.00884   0.00294  -0.0217   0.3818   1.0000
   5.000   0.8703   0.00896   0.00304  -0.0215   0.3767   1.0000
   5.250   0.8963   0.00906   0.00317  -0.0212   0.3697   1.0000
   5.500   0.9219   0.00921   0.00329  -0.0209   0.3624   1.0000
   5.750   0.9477   0.00934   0.00344  -0.0206   0.3557   1.0000
   6.000   0.9731   0.00952   0.00361  -0.0204   0.3457   1.0000
   6.250   0.9983   0.00975   0.00380  -0.0201   0.3307   1.0000
   6.500   1.0232   0.01001   0.00402  -0.0198   0.3157   1.0000
   6.750   1.0477   0.01036   0.00431  -0.0196   0.2955   1.0000
   7.000   1.0714   0.01082   0.00468  -0.0193   0.2726   1.0000
   7.250   1.0938   0.01152   0.00521  -0.0191   0.2401   1.0000
   7.500   1.1160   0.01216   0.00574  -0.0188   0.2161   1.0000
   7.750   1.1370   0.01296   0.00640  -0.0184   0.1864   1.0000
   8.000   1.1542   0.01425   0.00740  -0.0179   0.1361   1.0000
   8.250   1.1557   0.01733   0.00988  -0.0168   0.0270   1.0000
   8.500   1.1726   0.01822   0.01078  -0.0160   0.0181   1.0000
   8.750   1.1902   0.01894   0.01157  -0.0153   0.0158   1.0000
   9.000   1.2056   0.01983   0.01251  -0.0145   0.0139   1.0000
   9.250   1.2180   0.02093   0.01373  -0.0135   0.0125   1.0000
   9.500   1.2302   0.02211   0.01500  -0.0131   0.0120   1.0000
   9.750   1.2348   0.02372   0.01670  -0.0124   0.0114   1.0000
  10.000   1.2345   0.02547   0.01852  -0.0109   0.0110   1.0000
  10.250   1.2367   0.02734   0.02046  -0.0101   0.0105   1.0000
  10.500   1.2392   0.02937   0.02256  -0.0096   0.0100   1.0000
  10.750   1.2406   0.03160   0.02485  -0.0092   0.0094   1.0000
  11.000   1.2393   0.03419   0.02752  -0.0089   0.0092   1.0000
  11.250   1.2338   0.03727   0.03071  -0.0088   0.0087   1.0000
  11.500   1.2342   0.03977   0.03329  -0.0087   0.0085   1.0000
  11.750   1.2333   0.04245   0.03606  -0.0086   0.0084   1.0000
  12.000   1.2332   0.04508   0.03876  -0.0086   0.0081   1.0000
  12.250   1.2311   0.04794   0.04171  -0.0087   0.0079   1.0000
  12.500   1.2273   0.05109   0.04494  -0.0089   0.0076   1.0000
  12.750   1.2238   0.05430   0.04824  -0.0092   0.0076   1.0000
  13.000   1.2228   0.05734   0.05135  -0.0095   0.0072   1.0000
  13.250   1.2222   0.06034   0.05442  -0.0099   0.0071   1.0000
  13.500   1.2196   0.06369   0.05784  -0.0105   0.0069   1.0000
  13.750   1.2185   0.06692   0.06115  -0.0110   0.0066   1.0000
  14.000   1.2154   0.07042   0.06471  -0.0117   0.0064   1.0000
  14.250   1.2108   0.07424   0.06861  -0.0125   0.0064   1.0000
  14.500   1.2070   0.07796   0.07239  -0.0133   0.0062   1.0000
  14.750   1.1979   0.08245   0.07696  -0.0142   0.0060   1.0000
  15.000   1.1962   0.08597   0.08055  -0.0150   0.0060   1.0000
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