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GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 385 AIRFOIL (goe385-il)
Reynolds number: 1,000,000
Max Cl/Cd: 108.52 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe385-il-1000000-n5.txt
Download as CSV file: xf-goe385-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 385 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4099   0.10882   0.10724  -0.0133   1.0000   0.0053
 -10.000  -0.4077   0.10450   0.10294  -0.0153   1.0000   0.0055
  -8.750  -0.4161   0.08024   0.07853  -0.0284   0.8833   0.0068
  -7.750  -0.4011   0.04713   0.04473  -0.0623   0.8081   0.0090
  -7.500  -0.4088   0.02485   0.02125  -0.0694   0.8024   0.0115
  -7.000  -0.3717   0.01436   0.00949  -0.0692   0.7870   0.0151
  -6.750  -0.3429   0.01472   0.00986  -0.0693   0.7778   0.0155
  -6.500  -0.3140   0.01519   0.01036  -0.0694   0.7678   0.0157
  -6.250  -0.2855   0.01555   0.01073  -0.0694   0.7564   0.0159
  -6.000  -0.2574   0.01568   0.01081  -0.0695   0.7431   0.0163
  -5.750  -0.2298   0.01546   0.01049  -0.0695   0.7256   0.0167
  -5.500  -0.2027   0.01487   0.00968  -0.0695   0.7027   0.0177
  -5.250  -0.1759   0.01393   0.00846  -0.0694   0.6794   0.0190
  -5.000  -0.1482   0.01357   0.00792  -0.0694   0.6613   0.0194
  -4.750  -0.1204   0.01323   0.00744  -0.0694   0.6481   0.0198
  -4.500  -0.0930   0.01263   0.00672  -0.0695   0.6373   0.0204
  -4.250  -0.0650   0.01244   0.00644  -0.0696   0.6264   0.0208
  -4.000  -0.0368   0.01233   0.00626  -0.0697   0.6152   0.0212
  -3.750  -0.0086   0.01213   0.00598  -0.0698   0.6054   0.0216
  -3.500   0.0195   0.01179   0.00555  -0.0699   0.5964   0.0221
  -3.250   0.0477   0.01143   0.00511  -0.0700   0.5893   0.0226
  -2.750   0.1044   0.01086   0.00442  -0.0702   0.5782   0.0238
  -2.500   0.1328   0.01055   0.00405  -0.0703   0.5720   0.0243
  -2.250   0.1611   0.01029   0.00374  -0.0704   0.5664   0.0247
  -2.000   0.1896   0.01003   0.00344  -0.0705   0.5601   0.0249
  -1.750   0.2179   0.00982   0.00317  -0.0706   0.5536   0.0252
  -1.500   0.2464   0.00960   0.00292  -0.0707   0.5475   0.0254
  -1.250   0.2749   0.00942   0.00270  -0.0708   0.5404   0.0255
  -1.000   0.3034   0.00925   0.00250  -0.0710   0.5334   0.0257
  -0.750   0.3319   0.00915   0.00236  -0.0711   0.5248   0.0258
  -0.500   0.3603   0.00894   0.00210  -0.0713   0.5134   0.0263
  -0.250   0.3887   0.00876   0.00184  -0.0714   0.4994   0.0269
   0.000   0.4172   0.00865   0.00167  -0.0716   0.4872   0.0277
   0.250   0.4456   0.00861   0.00157  -0.0717   0.4729   0.0287
   0.500   0.4738   0.00864   0.00152  -0.0718   0.4546   0.0295
   0.750   0.5018   0.00872   0.00150  -0.0720   0.4319   0.0303
   1.000   0.5297   0.00882   0.00151  -0.0721   0.4085   0.0310
   1.250   0.5576   0.00893   0.00153  -0.0722   0.3874   0.0317
   1.500   0.5855   0.00903   0.00156  -0.0723   0.3698   0.0324
   1.750   0.6135   0.00913   0.00160  -0.0724   0.3548   0.0332
   2.000   0.6415   0.00924   0.00165  -0.0725   0.3419   0.0343
   2.250   0.6694   0.00934   0.00171  -0.0726   0.3305   0.0367
   2.500   0.6975   0.00940   0.00178  -0.0727   0.3207   0.0561
   3.000   0.7476   0.00764   0.00213  -0.0724   0.2992   1.0000
   3.250   0.7751   0.00784   0.00224  -0.0724   0.2858   1.0000
   3.500   0.8027   0.00801   0.00235  -0.0725   0.2752   1.0000
   3.750   0.8305   0.00816   0.00246  -0.0726   0.2683   1.0000
   4.000   0.8582   0.00831   0.00258  -0.0727   0.2613   1.0000
   4.250   0.8858   0.00846   0.00270  -0.0728   0.2551   1.0000
   4.500   0.9134   0.00862   0.00284  -0.0729   0.2483   1.0000
   4.750   0.9406   0.00881   0.00298  -0.0729   0.2402   1.0000
   5.000   0.9679   0.00898   0.00313  -0.0730   0.2320   1.0000
   5.250   0.9951   0.00917   0.00330  -0.0730   0.2251   1.0000
   5.500   1.0216   0.00944   0.00350  -0.0730   0.2116   1.0000
   5.750   1.0473   0.00980   0.00374  -0.0728   0.1887   1.0000
   6.000   1.0682   0.01073   0.00431  -0.0721   0.1258   1.0000
   6.250   1.0934   0.01112   0.00463  -0.0719   0.1125   1.0000
   6.500   1.1188   0.01146   0.00494  -0.0717   0.1040   1.0000
   6.750   1.1446   0.01174   0.00520  -0.0716   0.0960   1.0000
   7.000   1.1668   0.01243   0.00570  -0.0710   0.0639   1.0000
   7.250   1.1905   0.01291   0.00613  -0.0706   0.0506   1.0000
   7.500   1.2145   0.01334   0.00653  -0.0702   0.0416   1.0000
   7.750   1.2348   0.01416   0.00720  -0.0693   0.0169   1.0000
   8.000   1.2581   0.01461   0.00767  -0.0688   0.0131   1.0000
   8.250   1.2816   0.01503   0.00811  -0.0683   0.0110   1.0000
   8.500   1.3050   0.01543   0.00854  -0.0679   0.0100   1.0000
   8.750   1.3274   0.01589   0.00903  -0.0673   0.0089   1.0000
   9.000   1.3490   0.01642   0.00959  -0.0665   0.0079   1.0000
   9.250   1.3712   0.01686   0.01008  -0.0659   0.0075   1.0000
   9.500   1.3925   0.01735   0.01061  -0.0652   0.0070   1.0000
   9.750   1.4129   0.01787   0.01117  -0.0643   0.0065   1.0000
  10.000   1.4323   0.01846   0.01178  -0.0633   0.0060   1.0000
  10.250   1.4495   0.01916   0.01254  -0.0620   0.0055   1.0000
  10.500   1.4678   0.01973   0.01317  -0.0609   0.0053   1.0000
  10.750   1.4842   0.02036   0.01385  -0.0594   0.0051   1.0000
  11.000   1.4972   0.02103   0.01458  -0.0574   0.0048   1.0000
  11.250   1.5090   0.02178   0.01539  -0.0554   0.0046   1.0000
  11.500   1.5202   0.02262   0.01629  -0.0534   0.0044   1.0000
  11.750   1.5305   0.02357   0.01730  -0.0516   0.0043   1.0000
  12.000   1.5395   0.02467   0.01846  -0.0497   0.0041   1.0000
  12.250   1.5463   0.02601   0.01989  -0.0479   0.0039   1.0000
  12.500   1.5500   0.02770   0.02168  -0.0461   0.0038   1.0000
  12.750   1.5573   0.02921   0.02328  -0.0449   0.0037   1.0000
  13.000   1.5634   0.03093   0.02509  -0.0438   0.0036   1.0000
  13.250   1.5682   0.03287   0.02711  -0.0429   0.0036   1.0000
  13.500   1.5720   0.03498   0.02932  -0.0422   0.0035   1.0000
  13.750   1.5750   0.03727   0.03171  -0.0416   0.0034   1.0000
  14.000   1.5768   0.03978   0.03432  -0.0412   0.0033   1.0000
  14.250   1.5772   0.04256   0.03719  -0.0411   0.0032   1.0000
  14.500   1.5770   0.04552   0.04024  -0.0411   0.0031   1.0000
  14.750   1.5749   0.04878   0.04361  -0.0413   0.0031   1.0000
  15.000   1.5722   0.05217   0.04710  -0.0416   0.0030   1.0000
  15.250   1.5671   0.05590   0.05094  -0.0420   0.0029   1.0000
  15.500   1.5610   0.05985   0.05500  -0.0425   0.0029   1.0000
  15.750   1.5536   0.06405   0.05930  -0.0432   0.0028   1.0000
  16.000   1.5442   0.06870   0.06406  -0.0442   0.0028   1.0000
  16.250   1.5346   0.07349   0.06895  -0.0453   0.0028   1.0000
  16.500   1.5229   0.07868   0.07425  -0.0467   0.0027   1.0000
  16.750   1.5114   0.08400   0.07969  -0.0482   0.0027   1.0000
  17.000   1.4984   0.08968   0.08548  -0.0499   0.0027   1.0000
  17.250   1.4849   0.09550   0.09141  -0.0517   0.0027   1.0000
  17.500   1.4716   0.10139   0.09741  -0.0537   0.0026   1.0000
  17.750   1.4576   0.10750   0.10363  -0.0559   0.0026   1.0000
  18.000   1.4440   0.11358   0.10981  -0.0581   0.0026   1.0000
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