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GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il)
Reynolds number: 500,000
Max Cl/Cd: 101.64 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe319-il-500000.txt
Download as CSV file: xf-goe319-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 319 (HANSA-BRANDENBURG II) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1978   0.08764   0.08532  -0.0375   0.9102   0.0262
  -7.750  -0.1925   0.08498   0.08259  -0.0385   0.8894   0.0267
  -7.500  -0.1872   0.08185   0.07939  -0.0421   0.8688   0.0275
  -7.250  -0.1745   0.07705   0.07448  -0.0540   0.8487   0.0278
  -7.000  -0.1602   0.07288   0.07022  -0.0583   0.8338   0.0279
  -6.750  -0.1490   0.07025   0.06754  -0.0575   0.8203   0.0280
  -6.500  -0.1351   0.06781   0.06506  -0.0576   0.8077   0.0282
  -6.250  -0.1191   0.06527   0.06245  -0.0590   0.7963   0.0285
  -6.000  -0.1011   0.06256   0.05966  -0.0614   0.7851   0.0289
  -5.750  -0.0809   0.05964   0.05667  -0.0645   0.7748   0.0294
  -5.500  -0.0591   0.05662   0.05354  -0.0678   0.7655   0.0301
  -5.250  -0.0164   0.05086   0.04747  -0.0783   0.7568   0.0320
  -5.000   0.0034   0.04722   0.04371  -0.0801   0.7491   0.0323
  -4.750   0.0227   0.04505   0.04152  -0.0805   0.7409   0.0325
  -4.500   0.0438   0.04312   0.03949  -0.0812   0.7322   0.0328
  -4.250   0.0670   0.04112   0.03743  -0.0821   0.7231   0.0332
  -4.000   0.0916   0.03911   0.03528  -0.0831   0.7143   0.0341
  -3.750   0.1310   0.03433   0.03002  -0.0863   0.7071   0.0370
  -3.500   0.1518   0.03239   0.02806  -0.0865   0.6986   0.0373
  -3.250   0.1751   0.03097   0.02658  -0.0867   0.6901   0.0378
  -3.000   0.1997   0.02959   0.02511  -0.0869   0.6809   0.0385
  -2.750   0.2259   0.02804   0.02343  -0.0872   0.6720   0.0398
  -2.500   0.2563   0.02482   0.01977  -0.0873   0.6629   0.0431
  -2.250   0.2812   0.02376   0.01866  -0.0873   0.6523   0.0437
  -2.000   0.3068   0.02278   0.01757  -0.0872   0.6425   0.0447
  -1.750   0.3360   0.02090   0.01530  -0.0868   0.6340   0.0495
  -1.500   0.3615   0.01997   0.01434  -0.0868   0.6256   0.0504
  -1.250   0.3883   0.01917   0.01348  -0.0867   0.6170   0.0521
  -1.000   0.4163   0.01802   0.01198  -0.0862   0.6088   0.0574
  -0.750   0.4429   0.01722   0.01118  -0.0861   0.5998   0.0589
  -0.500   0.4724   0.01811   0.01176  -0.0854   0.5906   0.0647
  -0.250   0.4975   0.01582   0.00947  -0.0855   0.5818   0.0677
   0.000   0.5279   0.01284   0.00571  -0.0838   0.5745   0.0429
   0.250   0.5556   0.01231   0.00511  -0.0835   0.5662   0.0429
   0.500   0.5830   0.01204   0.00473  -0.0831   0.5577   0.0426
   0.750   0.6106   0.01166   0.00432  -0.0828   0.5494   0.0423
   1.000   0.6375   0.01134   0.00394  -0.0824   0.5409   0.0424
   1.250   0.6644   0.01092   0.00352  -0.0821   0.5325   0.0429
   1.500   0.6910   0.01072   0.00329  -0.0817   0.5237   0.0438
   1.750   0.7182   0.01058   0.00317  -0.0814   0.5147   0.0450
   2.000   0.7449   0.01054   0.00310  -0.0810   0.5049   0.0466
   2.250   0.7723   0.01050   0.00305  -0.0808   0.4938   0.0487
   2.500   0.7991   0.01043   0.00297  -0.0805   0.4824   0.0516
   2.750   0.8259   0.01047   0.00297  -0.0801   0.4699   0.0556
   3.000   0.8526   0.01047   0.00299  -0.0798   0.4552   0.0710
   3.250   0.8906   0.00879   0.00324  -0.0825   0.4358   1.0000
   3.500   0.9158   0.00901   0.00332  -0.0819   0.4124   1.0000
   3.750   0.9398   0.00933   0.00346  -0.0812   0.3828   1.0000
   4.000   0.9629   0.00975   0.00366  -0.0803   0.3509   1.0000
   4.500   1.0093   0.01060   0.00417  -0.0788   0.3054   1.0000
   5.000   1.0578   0.01127   0.00465  -0.0776   0.2806   1.0000
   5.250   1.0819   0.01161   0.00491  -0.0770   0.2726   1.0000
   5.500   1.1068   0.01187   0.00514  -0.0765   0.2662   1.0000
   5.750   1.1307   0.01221   0.00542  -0.0759   0.2604   1.0000
   6.000   1.1553   0.01250   0.00569  -0.0753   0.2559   1.0000
   6.250   1.1801   0.01275   0.00595  -0.0749   0.2517   1.0000
   6.500   1.2041   0.01306   0.00623  -0.0743   0.2475   1.0000
   6.750   1.2271   0.01345   0.00658  -0.0736   0.2433   1.0000
   7.000   1.2512   0.01374   0.00689  -0.0730   0.2401   1.0000
   7.250   1.2757   0.01399   0.00716  -0.0725   0.2368   1.0000
   7.500   1.2994   0.01429   0.00747  -0.0720   0.2332   1.0000
   7.750   1.3219   0.01468   0.00783  -0.0712   0.2294   1.0000
   8.000   1.3433   0.01515   0.00828  -0.0703   0.2257   1.0000
   8.250   1.3673   0.01539   0.00858  -0.0698   0.2232   1.0000
   8.500   1.3906   0.01568   0.00891  -0.0692   0.2202   1.0000
   8.750   1.4129   0.01602   0.00927  -0.0685   0.2170   1.0000
   9.000   1.4337   0.01645   0.00969  -0.0676   0.2136   1.0000
   9.250   1.4531   0.01700   0.01023  -0.0665   0.2099   1.0000
   9.500   1.4757   0.01723   0.01055  -0.0658   0.2069   1.0000
   9.750   1.4972   0.01752   0.01089  -0.0650   0.2028   1.0000
  10.000   1.5154   0.01795   0.01131  -0.0638   0.1985   1.0000
  10.250   1.5311   0.01853   0.01189  -0.0621   0.1944   1.0000
  10.500   1.5511   0.01882   0.01227  -0.0611   0.1911   1.0000
  10.750   1.5695   0.01921   0.01272  -0.0600   0.1871   1.0000
  11.000   1.5851   0.01978   0.01328  -0.0586   0.1830   1.0000
  11.250   1.6008   0.02037   0.01392  -0.0572   0.1786   1.0000
  11.500   1.6192   0.02080   0.01443  -0.0563   0.1738   1.0000
  11.750   1.6340   0.02148   0.01511  -0.0551   0.1691   1.0000
  12.000   1.6477   0.02226   0.01592  -0.0538   0.1649   1.0000
  12.250   1.6641   0.02290   0.01663  -0.0528   0.1602   1.0000
  12.500   1.6769   0.02380   0.01754  -0.0516   0.1554   1.0000
  12.750   1.6890   0.02478   0.01856  -0.0505   0.1513   1.0000
  13.000   1.7026   0.02569   0.01954  -0.0495   0.1470   1.0000
  13.250   1.7127   0.02690   0.02077  -0.0484   0.1428   1.0000
  13.500   1.7218   0.02823   0.02214  -0.0473   0.1388   1.0000
  13.750   1.7332   0.02942   0.02340  -0.0465   0.1344   1.0000
  14.000   1.7398   0.03104   0.02504  -0.0455   0.1300   1.0000
  14.250   1.7464   0.03271   0.02677  -0.0447   0.1264   1.0000
  14.500   1.7554   0.03420   0.02835  -0.0440   0.1229   1.0000
  14.750   1.7604   0.03610   0.03029  -0.0432   0.1194   1.0000
  15.000   1.7610   0.03843   0.03265  -0.0424   0.1159   1.0000
  15.250   1.7685   0.04014   0.03447  -0.0419   0.1127   1.0000
  15.500   1.7718   0.04229   0.03668  -0.0413   0.1088   1.0000
  15.750   1.7696   0.04503   0.03945  -0.0408   0.1052   1.0000
  16.000   1.7724   0.04734   0.04185  -0.0404   0.1018   1.0000
  16.250   1.7742   0.04981   0.04440  -0.0402   0.0979   1.0000
  16.500   1.7699   0.05302   0.04766  -0.0401   0.0943   1.0000
  16.750   1.7692   0.05589   0.05062  -0.0400   0.0910   1.0000
  17.000   1.7681   0.05889   0.05371  -0.0401   0.0870   1.0000
  17.250   1.7602   0.06278   0.05764  -0.0404   0.0832   1.0000
  17.500   1.7566   0.06620   0.06116  -0.0407   0.0792   1.0000
  17.750   1.7475   0.07043   0.06544  -0.0413   0.0750   1.0000
  18.000   1.7369   0.07492   0.07000  -0.0421   0.0712   1.0000
  18.250   1.7241   0.07979   0.07495  -0.0430   0.0673   1.0000
  18.500   1.7071   0.08537   0.08060  -0.0443   0.0640   1.0000
  18.750   1.6923   0.09074   0.08606  -0.0457   0.0605   1.0000
  19.000   1.6718   0.09703   0.09244  -0.0475   0.0577   1.0000
  19.250   1.6530   0.10324   0.09874  -0.0494   0.0549   1.0000
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