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GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il)
Reynolds number: 200,000
Max Cl/Cd: 80.79 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe238-il-200000.txt
Download as CSV file: xf-goe238-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 238 (HANSA-BRANDENBURG) AIRFOIL             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1660   0.09571   0.09194  -0.0369   0.7981   0.0394
  -9.250  -0.1599   0.09275   0.08892  -0.0377   0.7872   0.0402
  -9.000  -0.2046   0.09654   0.09272  -0.0431   0.8319   0.0394
  -8.750  -0.1951   0.09391   0.08996  -0.0445   0.8124   0.0403
  -8.500  -0.1883   0.09145   0.08742  -0.0456   0.7971   0.0412
  -8.250  -0.1829   0.08910   0.08501  -0.0468   0.7840   0.0424
  -8.000  -0.1853   0.08754   0.08341  -0.0494   0.7724   0.0436
  -7.750  -0.1951   0.08633   0.08218  -0.0525   0.7619   0.0439
  -7.500  -0.1933   0.08411   0.07991  -0.0581   0.7522   0.0441
  -7.250  -0.1828   0.07992   0.07567  -0.0566   0.7446   0.0444
  -7.000  -0.1701   0.07663   0.07239  -0.0546   0.7356   0.0448
  -6.750  -0.1591   0.07396   0.06965  -0.0544   0.7283   0.0454
  -6.500  -0.1486   0.07137   0.06704  -0.0554   0.7197   0.0462
  -6.250  -0.1374   0.06879   0.06440  -0.0569   0.7127   0.0471
  -6.000  -0.1247   0.06614   0.06171  -0.0589   0.7054   0.0483
  -5.750  -0.1024   0.06367   0.05901  -0.0666   0.6986   0.0513
  -5.500  -0.0841   0.06017   0.05529  -0.0701   0.6931   0.0519
  -5.250  -0.0720   0.05691   0.05210  -0.0690   0.6859   0.0524
  -5.000  -0.0569   0.05441   0.04955  -0.0687   0.6798   0.0531
  -4.750  -0.0392   0.05209   0.04718  -0.0691   0.6733   0.0542
  -4.500  -0.0193   0.04972   0.04473  -0.0700   0.6667   0.0558
  -4.250   0.0166   0.04797   0.04242  -0.0740   0.6616   0.0603
  -4.000   0.0347   0.04430   0.03870  -0.0746   0.6554   0.0611
  -3.750   0.0521   0.04191   0.03635  -0.0743   0.6494   0.0621
  -3.500   0.0724   0.04010   0.03445  -0.0742   0.6447   0.0639
  -3.250   0.1039   0.03896   0.03295  -0.0752   0.6387   0.0701
  -3.000   0.1256   0.03593   0.02975  -0.0755   0.6334   0.0717
  -2.750   0.1467   0.03406   0.02784  -0.0754   0.6288   0.0733
  -2.500   0.1703   0.03260   0.02632  -0.0753   0.6235   0.0763
  -2.250   0.1980   0.03088   0.02424  -0.0754   0.6180   0.0837
  -2.000   0.2210   0.02940   0.02273  -0.0752   0.6134   0.0864
  -1.750   0.2477   0.02823   0.02124  -0.0751   0.6091   0.0967
  -1.500   0.2714   0.02705   0.02012  -0.0749   0.6037   0.1014
  -1.250   0.2836   0.01101   0.00436  -0.0705   0.5945   0.1174
  -1.000   0.3086   0.01044   0.00365  -0.0705   0.5899   0.1398
  -0.750   0.3330   0.00974   0.00292  -0.0704   0.5856   0.1559
  -0.500   0.3573   0.00900   0.00216  -0.0703   0.5818   0.1735
   0.250   0.4668   0.01959   0.01079  -0.0715   0.5766   0.0825
   0.500   0.4937   0.01875   0.00996  -0.0711   0.5720   0.0807
   0.750   0.5211   0.01796   0.00911  -0.0707   0.5679   0.0774
   1.000   0.5488   0.01745   0.00847  -0.0702   0.5643   0.0753
   1.250   0.5765   0.01710   0.00799  -0.0698   0.5610   0.0748
   1.500   0.6023   0.01680   0.00779  -0.0693   0.5562   0.0757
   1.750   0.6285   0.01658   0.00761  -0.0689   0.5521   0.0792
   2.000   0.6551   0.01643   0.00744  -0.0684   0.5487   0.0820
   2.250   0.6811   0.01611   0.00714  -0.0679   0.5458   0.0856
   2.500   0.7066   0.01605   0.00713  -0.0674   0.5418   0.0910
   2.750   0.7320   0.01597   0.00714  -0.0669   0.5372   0.1048
   3.000   0.7528   0.01501   0.00730  -0.0658   0.5338   0.5593
   3.250   0.8141   0.01436   0.00731  -0.0723   0.5305   1.0000
   3.500   0.8405   0.01463   0.00745  -0.0720   0.5279   1.0000
   3.750   0.8647   0.01489   0.00778  -0.0713   0.5237   1.0000
   4.000   0.8899   0.01508   0.00796  -0.0708   0.5194   1.0000
   4.250   0.9161   0.01522   0.00805  -0.0704   0.5158   1.0000
   4.500   0.9432   0.01538   0.00811  -0.0701   0.5125   1.0000
   4.750   0.9670   0.01564   0.00846  -0.0694   0.5077   1.0000
   5.000   0.9921   0.01579   0.00864  -0.0689   0.5028   1.0000
   5.250   1.0188   0.01584   0.00863  -0.0685   0.4984   1.0000
   5.500   1.0439   0.01597   0.00878  -0.0679   0.4929   1.0000
   5.750   1.0684   0.01603   0.00890  -0.0673   0.4863   1.0000
   6.000   1.0955   0.01602   0.00881  -0.0669   0.4812   1.0000
   6.250   1.1193   0.01620   0.00910  -0.0662   0.4752   1.0000
   6.500   1.1443   0.01625   0.00918  -0.0657   0.4688   1.0000
   6.750   1.1707   0.01629   0.00917  -0.0652   0.4631   1.0000
   7.000   1.1936   0.01635   0.00939  -0.0644   0.4548   1.0000
   7.250   1.2198   0.01632   0.00929  -0.0639   0.4479   1.0000
   7.500   1.2421   0.01642   0.00956  -0.0630   0.4389   1.0000
   7.750   1.2667   0.01644   0.00957  -0.0623   0.4307   1.0000
   8.000   1.2892   0.01652   0.00979  -0.0614   0.4207   1.0000
   8.250   1.3118   0.01660   0.00996  -0.0605   0.4098   1.0000
   8.500   1.3338   0.01668   0.01009  -0.0595   0.3968   1.0000
   8.750   1.3549   0.01682   0.01031  -0.0584   0.3814   1.0000
   9.000   1.3750   0.01702   0.01059  -0.0572   0.3625   1.0000
   9.250   1.3930   0.01734   0.01090  -0.0557   0.3365   1.0000
   9.500   1.4073   0.01792   0.01137  -0.0538   0.3027   1.0000
   9.750   1.4138   0.01897   0.01218  -0.0510   0.2684   1.0000
  10.000   1.4161   0.02028   0.01332  -0.0479   0.2411   1.0000
  10.250   1.4140   0.02170   0.01461  -0.0442   0.2175   1.0000
  10.500   1.4087   0.02315   0.01600  -0.0402   0.1948   1.0000
  11.000   1.3838   0.02819   0.02069  -0.0348   0.1232   1.0000
  11.250   1.3698   0.03157   0.02391  -0.0334   0.1044   1.0000
  11.500   1.3603   0.03477   0.02706  -0.0324   0.0952   1.0000
  11.750   1.3532   0.03785   0.03015  -0.0316   0.0893   1.0000
  12.000   1.3450   0.04114   0.03345  -0.0310   0.0853   1.0000
  12.250   1.3424   0.04391   0.03632  -0.0304   0.0816   1.0000
  12.500   1.3369   0.04704   0.03951  -0.0300   0.0784   1.0000
  12.750   1.3288   0.05044   0.04292  -0.0296   0.0756   1.0000
  13.000   1.3252   0.05337   0.04590  -0.0291   0.0730   1.0000
  13.250   1.3253   0.05599   0.04860  -0.0287   0.0700   1.0000
  13.500   1.3250   0.05872   0.05137  -0.0284   0.0672   1.0000
  13.750   1.3242   0.06126   0.05383  -0.0276   0.0639   1.0000
  14.000   1.3286   0.06350   0.05615  -0.0271   0.0610   1.0000
  14.250   1.3325   0.06588   0.05863  -0.0269   0.0580   1.0000
  14.500   1.3377   0.06796   0.06068  -0.0263   0.0552   1.0000
  14.750   1.3483   0.06921   0.06190  -0.0248   0.0519   1.0000
  15.000   1.3521   0.07180   0.06462  -0.0249   0.0495   1.0000
  15.250   1.3579   0.07406   0.06693  -0.0247   0.0472   1.0000
  15.500   1.3784   0.07418   0.06691  -0.0223   0.0441   1.0000
  15.750   1.3783   0.07737   0.07031  -0.0229   0.0430   1.0000
  16.000   1.3811   0.08021   0.07332  -0.0232   0.0415   1.0000
  16.250   1.3849   0.08291   0.07614  -0.0235   0.0399   1.0000
  16.500   1.3882   0.08561   0.07889  -0.0239   0.0385   1.0000
  16.750   1.4070   0.08633   0.07951  -0.0222   0.0367   1.0000
  17.000   1.4029   0.09022   0.08366  -0.0233   0.0361   1.0000
  17.250   1.4001   0.09407   0.08774  -0.0242   0.0354   1.0000
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