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GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il)
Reynolds number: 500,000
Max Cl/Cd: 98.32 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe314-il-500000.txt
Download as CSV file: xf-goe314-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3154   0.08714   0.08495  -0.0223   1.0000   0.0248
  -7.500  -0.3176   0.08523   0.08309  -0.0213   1.0000   0.0252
  -7.250  -0.3244   0.08347   0.08137  -0.0198   1.0000   0.0254
  -7.000  -0.2304   0.06506   0.06309  -0.0381   0.9880   0.0282
  -6.750  -0.2090   0.05906   0.05702  -0.0480   0.9800   0.0283
  -6.500  -0.1951   0.05377   0.05173  -0.0493   0.9732   0.0286
  -6.250  -0.1765   0.05025   0.04822  -0.0503   0.9646   0.0290
  -6.000  -0.1515   0.04632   0.04425  -0.0545   0.9568   0.0295
  -5.750  -0.1255   0.04221   0.04009  -0.0596   0.9437   0.0302
  -5.500  -0.0973   0.03798   0.03576  -0.0651   0.9283   0.0314
  -5.250  -0.1225   0.05143   0.04903  -0.0656   0.9478   0.0312
  -5.000  -0.0656   0.04658   0.04380  -0.0759   0.9348   0.0336
  -4.750  -0.0356   0.04146   0.03854  -0.0802   0.9198   0.0341
  -4.500  -0.0080   0.03891   0.03592  -0.0824   0.9015   0.0345
  -4.250   0.0171   0.03690   0.03377  -0.0835   0.8813   0.0350
  -4.000   0.0401   0.03505   0.03178  -0.0838   0.8628   0.0357
  -3.750   0.0631   0.03321   0.02976  -0.0839   0.8457   0.0368
  -3.250   0.1200   0.03008   0.02591  -0.0829   0.8148   0.0402
  -3.000   0.1366   0.02632   0.02202  -0.0827   0.8004   0.0410
  -2.750   0.1583   0.02497   0.02059  -0.0822   0.7852   0.0416
  -2.500   0.1810   0.02380   0.01930  -0.0816   0.7689   0.0424
  -2.250   0.2046   0.02263   0.01797  -0.0809   0.7520   0.0437
  -2.000   0.2300   0.02153   0.01663  -0.0800   0.7336   0.0464
  -1.750   0.2587   0.02171   0.01639  -0.0786   0.7124   0.0482
  -1.500   0.2786   0.01856   0.01305  -0.0779   0.6902   0.0496
  -1.250   0.3018   0.01776   0.01212  -0.0772   0.6620   0.0507
  -1.000   0.3254   0.01716   0.01133  -0.0764   0.6317   0.0526
  -0.750   0.3501   0.01673   0.01062  -0.0753   0.6001   0.0558
  -0.500   0.3768   0.01754   0.01107  -0.0741   0.5696   0.0580
   0.000   0.4230   0.01471   0.00791  -0.0728   0.5223   0.0638
   0.250   0.4506   0.01315   0.00584  -0.0712   0.5040   0.0476
   0.500   0.4763   0.01287   0.00536  -0.0705   0.4867   0.0485
   1.000   0.5279   0.01196   0.00425  -0.0693   0.4607   0.0483
   1.250   0.5528   0.01139   0.00360  -0.0686   0.4498   0.0490
   1.500   0.5782   0.01103   0.00324  -0.0680   0.4397   0.0504
   1.750   0.6037   0.01090   0.00309  -0.0674   0.4307   0.0520
   2.000   0.6295   0.01085   0.00302  -0.0669   0.4219   0.0550
   2.250   0.6553   0.01079   0.00294  -0.0664   0.4135   0.0571
   2.500   0.6805   0.01069   0.00279  -0.0658   0.4041   0.0595
   2.750   0.7063   0.01061   0.00272  -0.0653   0.3945   0.0639
   3.000   0.7319   0.01067   0.00273  -0.0647   0.3859   0.0693
   3.250   0.7580   0.01063   0.00274  -0.0643   0.3776   0.0793
   3.500   0.7835   0.01064   0.00279  -0.0637   0.3694   0.1163
   3.750   0.8394   0.00911   0.00304  -0.0704   0.3570   1.0000
   4.000   0.8640   0.00923   0.00313  -0.0696   0.3480   1.0000
   4.250   0.8878   0.00942   0.00323  -0.0688   0.3387   1.0000
   4.500   0.9121   0.00956   0.00334  -0.0680   0.3286   1.0000
   4.750   0.9363   0.00973   0.00347  -0.0672   0.3196   1.0000
   5.000   0.9600   0.00993   0.00362  -0.0664   0.3100   1.0000
   5.250   0.9844   0.01009   0.00376  -0.0657   0.3003   1.0000
   5.500   1.0083   0.01030   0.00393  -0.0649   0.2903   1.0000
   5.750   1.0318   0.01053   0.00412  -0.0640   0.2795   1.0000
   6.000   1.0559   0.01074   0.00430  -0.0633   0.2687   1.0000
   6.250   1.0795   0.01098   0.00451  -0.0625   0.2579   1.0000
   6.500   1.1027   0.01125   0.00474  -0.0617   0.2471   1.0000
   6.750   1.1259   0.01153   0.00499  -0.0609   0.2359   1.0000
   7.000   1.1492   0.01181   0.00524  -0.0601   0.2248   1.0000
   7.250   1.1720   0.01212   0.00552  -0.0592   0.2132   1.0000
   7.500   1.1944   0.01247   0.00582  -0.0583   0.2008   1.0000
   7.750   1.2165   0.01284   0.00614  -0.0574   0.1885   1.0000
   8.000   1.2384   0.01322   0.00647  -0.0565   0.1776   1.0000
   8.250   1.2608   0.01356   0.00681  -0.0556   0.1675   1.0000
   8.500   1.2821   0.01398   0.00720  -0.0546   0.1540   1.0000
   8.750   1.3020   0.01451   0.00764  -0.0534   0.1354   1.0000
   9.000   1.3118   0.01588   0.00860  -0.0510   0.0745   1.0000
   9.250   1.3289   0.01660   0.00930  -0.0494   0.0662   1.0000
   9.500   1.3475   0.01716   0.00991  -0.0480   0.0623   1.0000
   9.750   1.3641   0.01784   0.01063  -0.0464   0.0586   1.0000
  10.000   1.3788   0.01861   0.01145  -0.0445   0.0546   1.0000
  10.250   1.3974   0.01906   0.01198  -0.0431   0.0524   1.0000
  10.500   1.4137   0.01963   0.01262  -0.0415   0.0489   1.0000
  10.750   1.4223   0.02052   0.01356  -0.0387   0.0446   1.0000
  11.000   1.4403   0.02083   0.01392  -0.0373   0.0393   1.0000
  11.250   1.4518   0.02151   0.01456  -0.0349   0.0318   1.0000
  11.500   1.4603   0.02236   0.01537  -0.0323   0.0259   1.0000
  11.750   1.4664   0.02338   0.01640  -0.0296   0.0229   1.0000
  12.000   1.4722   0.02445   0.01754  -0.0270   0.0212   1.0000
  12.250   1.4745   0.02580   0.01894  -0.0244   0.0199   1.0000
  12.500   1.4745   0.02741   0.02065  -0.0219   0.0190   1.0000
  12.750   1.4765   0.02902   0.02238  -0.0200   0.0184   1.0000
  13.000   1.4770   0.03089   0.02436  -0.0183   0.0179   1.0000
  13.250   1.4748   0.03317   0.02676  -0.0170   0.0173   1.0000
  13.500   1.4723   0.03567   0.02937  -0.0161   0.0170   1.0000
  13.750   1.4673   0.03865   0.03247  -0.0155   0.0167   1.0000
  14.000   1.4591   0.04224   0.03617  -0.0155   0.0163   1.0000
  14.250   1.4462   0.04671   0.04076  -0.0162   0.0159   1.0000
  14.500   1.4356   0.05120   0.04539  -0.0172   0.0158   1.0000
  14.750   1.4191   0.05671   0.05102  -0.0187   0.0155   1.0000
  15.000   1.4059   0.06186   0.05629  -0.0203   0.0154   1.0000
  15.250   1.3952   0.06678   0.06133  -0.0218   0.0152   1.0000
  15.500   1.3845   0.07174   0.06640  -0.0233   0.0152   1.0000
  15.750   1.3762   0.07645   0.07122  -0.0249   0.0150   1.0000
  16.000   1.3690   0.08111   0.07599  -0.0265   0.0148   1.0000
  16.250   1.3600   0.08605   0.08103  -0.0282   0.0146   1.0000
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