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GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.32 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe314-il-1000000-n5.txt
Download as CSV file: xf-goe314-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 314 (HANSA-BRANDENBURG) 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  -0.3480   0.08992   0.08829  -0.0231   0.9999   0.0127
  -8.500  -0.3369   0.08592   0.08429  -0.0270   0.9928   0.0131
  -8.250  -0.3389   0.07990   0.07827  -0.0320   0.9781   0.0144
  -8.000  -0.3108   0.07619   0.07453  -0.0394   0.9568   0.0145
  -7.750  -0.2625   0.07137   0.06965  -0.0520   0.9404   0.0148
  -7.500  -0.2087   0.06592   0.06399  -0.0666   0.8966   0.0154
  -7.250  -0.1980   0.06303   0.06087  -0.0691   0.8478   0.0158
  -7.000  -0.2007   0.05554   0.05320  -0.0746   0.8237   0.0174
  -6.750  -0.1874   0.05307   0.05062  -0.0759   0.8065   0.0176
  -6.500  -0.1718   0.05074   0.04820  -0.0771   0.7923   0.0178
  -6.250  -0.1543   0.04892   0.04629  -0.0778   0.7768   0.0179
  -6.000  -0.1361   0.04684   0.04412  -0.0787   0.7643   0.0182
  -5.750  -0.1174   0.04451   0.04168  -0.0797   0.7515   0.0184
  -5.500  -0.0978   0.04228   0.03934  -0.0804   0.7376   0.0189
  -5.250  -0.0777   0.03955   0.03646  -0.0813   0.7233   0.0195
  -5.000  -0.0577   0.03593   0.03264  -0.0821   0.7077   0.0200
  -4.750  -0.0398   0.02889   0.02519  -0.0827   0.6948   0.0211
  -4.500  -0.0190   0.02655   0.02262  -0.0824   0.6761   0.0215
  -4.250   0.0035   0.02505   0.02094  -0.0820   0.6543   0.0217
  -4.000   0.0262   0.02367   0.01935  -0.0814   0.6284   0.0220
  -3.750   0.0490   0.02238   0.01783  -0.0807   0.5990   0.0223
  -3.500   0.0718   0.02064   0.01583  -0.0800   0.5736   0.0226
  -3.250   0.0864   0.01274   0.00690  -0.0777   0.5587   0.0246
  -3.000   0.1107   0.01180   0.00566  -0.0770   0.5340   0.0250
  -2.750   0.1362   0.01136   0.00502  -0.0765   0.5134   0.0253
  -2.500   0.1622   0.01103   0.00455  -0.0760   0.4962   0.0254
  -2.250   0.1878   0.01053   0.00389  -0.0755   0.4812   0.0258
  -2.000   0.2136   0.01016   0.00340  -0.0750   0.4671   0.0262
  -1.750   0.2400   0.00995   0.00312  -0.0745   0.4545   0.0265
  -1.500   0.2665   0.00980   0.00290  -0.0741   0.4445   0.0268
  -1.250   0.2930   0.00968   0.00272  -0.0737   0.4337   0.0271
  -1.000   0.3193   0.00958   0.00255  -0.0733   0.4211   0.0274
  -0.750   0.3458   0.00948   0.00240  -0.0729   0.4100   0.0278
  -0.500   0.3722   0.00940   0.00226  -0.0725   0.3994   0.0283
  -0.250   0.3988   0.00935   0.00216  -0.0721   0.3894   0.0289
   0.000   0.4254   0.00930   0.00207  -0.0717   0.3805   0.0296
   0.500   0.4786   0.00920   0.00189  -0.0710   0.3642   0.0305
   0.750   0.5050   0.00917   0.00182  -0.0706   0.3561   0.0309
   1.000   0.5316   0.00909   0.00172  -0.0702   0.3495   0.0319
   1.250   0.5583   0.00908   0.00170  -0.0698   0.3427   0.0327
   1.500   0.5850   0.00909   0.00170  -0.0695   0.3365   0.0336
   1.750   0.6114   0.00913   0.00171  -0.0691   0.3256   0.0347
   2.000   0.6377   0.00919   0.00172  -0.0687   0.3131   0.0359
   2.250   0.6640   0.00927   0.00176  -0.0684   0.3014   0.0369
   2.500   0.6902   0.00933   0.00179  -0.0680   0.2924   0.0398
   2.750   0.7167   0.00939   0.00184  -0.0676   0.2837   0.0422
   3.000   0.7429   0.00948   0.00191  -0.0673   0.2746   0.0441
   3.250   0.7688   0.00959   0.00197  -0.0668   0.2627   0.0474
   3.500   0.7945   0.00972   0.00207  -0.0664   0.2491   0.0509
   3.750   0.8198   0.00991   0.00218  -0.0659   0.2328   0.0538
   4.000   0.8450   0.01008   0.00231  -0.0654   0.2174   0.0616
   4.250   0.8702   0.01023   0.00247  -0.0649   0.2042   0.1012
   4.750   0.9452   0.00911   0.00306  -0.0700   0.1779   1.0000
   5.000   0.9689   0.00931   0.00322  -0.0692   0.1700   1.0000
   5.250   0.9923   0.00954   0.00339  -0.0683   0.1620   1.0000
   5.500   1.0161   0.00974   0.00356  -0.0675   0.1552   1.0000
   5.750   1.0395   0.00999   0.00375  -0.0667   0.1473   1.0000
   6.000   1.0633   0.01020   0.00394  -0.0659   0.1400   1.0000
   6.250   1.0851   0.01059   0.00421  -0.0648   0.1213   1.0000
   6.500   1.0998   0.01163   0.00492  -0.0627   0.0611   1.0000
   6.750   1.1227   0.01194   0.00522  -0.0618   0.0568   1.0000
   7.000   1.1456   0.01224   0.00551  -0.0609   0.0532   1.0000
   7.250   1.1689   0.01251   0.00578  -0.0601   0.0507   1.0000
   7.500   1.1925   0.01274   0.00603  -0.0594   0.0499   1.0000
   7.750   1.2159   0.01299   0.00631  -0.0587   0.0487   1.0000
   8.000   1.2389   0.01327   0.00660  -0.0579   0.0472   1.0000
   8.250   1.2613   0.01358   0.00692  -0.0571   0.0452   1.0000
   8.500   1.2834   0.01393   0.00727  -0.0561   0.0431   1.0000
   8.750   1.3053   0.01427   0.00763  -0.0552   0.0411   1.0000
   9.000   1.3279   0.01453   0.00792  -0.0544   0.0401   1.0000
   9.250   1.3500   0.01483   0.00823  -0.0536   0.0379   1.0000
   9.500   1.3705   0.01525   0.00862  -0.0525   0.0334   1.0000
  10.000   1.4050   0.01649   0.00974  -0.0494   0.0146   1.0000
  10.250   1.4236   0.01697   0.01025  -0.0481   0.0131   1.0000
  10.500   1.4411   0.01749   0.01079  -0.0466   0.0119   1.0000
  10.750   1.4572   0.01806   0.01141  -0.0449   0.0108   1.0000
  11.000   1.4732   0.01854   0.01194  -0.0431   0.0103   1.0000
  11.250   1.4867   0.01905   0.01249  -0.0409   0.0098   1.0000
  11.500   1.4988   0.01960   0.01309  -0.0385   0.0093   1.0000
  11.750   1.5099   0.02023   0.01375  -0.0361   0.0089   1.0000
  12.000   1.5198   0.02093   0.01452  -0.0337   0.0085   1.0000
  12.250   1.5287   0.02172   0.01536  -0.0313   0.0081   1.0000
  12.500   1.5369   0.02259   0.01629  -0.0290   0.0078   1.0000
  12.750   1.5459   0.02345   0.01722  -0.0269   0.0076   1.0000
  13.000   1.5539   0.02442   0.01826  -0.0250   0.0074   1.0000
  13.250   1.5611   0.02552   0.01942  -0.0232   0.0071   1.0000
  13.500   1.5665   0.02681   0.02080  -0.0214   0.0069   1.0000
  13.750   1.5714   0.02826   0.02230  -0.0199   0.0066   1.0000
  14.000   1.5742   0.02997   0.02410  -0.0186   0.0064   1.0000
  14.250   1.5768   0.03184   0.02604  -0.0175   0.0062   1.0000
  14.500   1.5760   0.03417   0.02845  -0.0166   0.0061   1.0000
  14.750   1.5737   0.03681   0.03119  -0.0161   0.0058   1.0000
  15.000   1.5694   0.03986   0.03435  -0.0159   0.0058   1.0000
  15.250   1.5659   0.04303   0.03762  -0.0160   0.0057   1.0000
  15.500   1.5627   0.04633   0.04102  -0.0165   0.0056   1.0000
  15.750   1.5555   0.05033   0.04514  -0.0173   0.0056   1.0000
  16.000   1.5471   0.05464   0.04957  -0.0184   0.0055   1.0000
  16.250   1.5378   0.05920   0.05424  -0.0198   0.0055   1.0000
  16.500   1.5241   0.06449   0.05966  -0.0214   0.0055   1.0000
  16.750   1.5118   0.06971   0.06499  -0.0231   0.0054   1.0000
  17.000   1.4984   0.07513   0.07052  -0.0250   0.0053   1.0000
  17.250   1.4826   0.08105   0.07655  -0.0271   0.0053   1.0000
  17.500   1.4670   0.08704   0.08266  -0.0294   0.0053   1.0000
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