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Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il)

Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 - Used on the Me163 Komet


Airfoil goe765-il
Details Dat file Parser  
(goe765-il) Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300
Used on the Me163 Komet
Max thickness 14.4% at 30% chord.
Max camber 1.9% at 25.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 
  1.000000  -0.000000 
  0.989894   0.000681 
  0.979818   0.001451 
  0.969768   0.002306 
  0.959744   0.003241 
  0.949742   0.004251 
  0.939760   0.005332 
  0.929797   0.006480 
  0.919852   0.007690 
  0.909921   0.008959 
  0.900004   0.010282 
  0.890099   0.011656 
  0.880204   0.013078 
  0.870319   0.014543 
  0.860440   0.016049 
  0.850569   0.017592 
  0.840702   0.019170 
  0.830839   0.020778 
  0.820980   0.022415 
  0.811122   0.024076 
  0.801265   0.025760 
  0.791409   0.027463 
  0.781551   0.029184 
  0.771693   0.030918 
  0.761832   0.032664 
  0.751969   0.034419 
  0.742102   0.036181 
  0.732232   0.037948 
  0.722357   0.039717 
  0.712477   0.041485 
  0.702591   0.043251 
  0.692701   0.045013 
  0.682804   0.046768 
  0.672900   0.048514 
  0.662990   0.050250 
  0.653073   0.051973 
  0.643149   0.053681 
  0.633218   0.055373 
  0.623278   0.057046 
  0.613331   0.058699 
  0.603376   0.060330 
  0.593413   0.061938 
  0.583441   0.063519 
  0.573461   0.065074 
  0.563472   0.066599 
  0.553475   0.068093 
  0.543469   0.069555 
  0.533454   0.070983 
  0.523430   0.072376 
  0.513397   0.073731 
  0.503355   0.075047 
  0.493303   0.076322 
  0.483243   0.077555 
  0.473172   0.078745 
  0.463093   0.079889 
  0.453003   0.080986 
  0.442904   0.082034 
  0.432796   0.083032 
  0.422677   0.083979 
  0.412549   0.084871 
  0.402410   0.085709 
  0.392262   0.086490 
  0.382103   0.087212 
  0.371934   0.087874 
  0.361755   0.088474 
  0.351565   0.089011 
  0.341365   0.089482 
  0.331155   0.089885 
  0.320934   0.090220 
  0.310703   0.090484 
  0.300461   0.090675 
  0.290208   0.090785 
  0.279946   0.090803 
  0.269673   0.090725 
  0.259390   0.090547 
  0.249098   0.090261 
  0.238797   0.089864 
  0.228488   0.089348 
  0.218172   0.088708 
  0.207849   0.087937 
  0.197522   0.087028 
  0.187191   0.085974 
  0.176858   0.084767 
  0.166525   0.083397 
  0.156195   0.081855 
  0.145870   0.080131 
  0.135554   0.078212 
  0.125250   0.076086 
  0.114964   0.073738 
  0.104700   0.071149 
  0.094465   0.068300 
  0.084267   0.065166 
  0.074117   0.061714 
  0.064025   0.057907 
  0.054009   0.053690 
  0.044090   0.048989 
  0.039176   0.046425 
  0.034298   0.043693 
  0.029464   0.040768 
  0.024683   0.037614 
  0.019965   0.034182 
  0.015330   0.030393 
  0.010806   0.026119 
  0.006448   0.021104 
  0.002392   0.014696 
 -0.000000   0.000000 
  0.007608  -0.012992 
  0.013552  -0.017745 
  0.019194  -0.021153 
  0.024670  -0.023870 
  0.030035  -0.026149 
  0.035317  -0.028118 
  0.040536  -0.029854 
  0.045702  -0.031406 
  0.050824  -0.032810 
  0.055910  -0.034090 
  0.065991  -0.036349 
  0.075975  -0.038289 
  0.085883  -0.039981 
  0.095733  -0.041470 
  0.105535  -0.042792 
  0.115300  -0.043972 
  0.125036  -0.045030 
  0.134750  -0.045983 
  0.144446  -0.046843 
  0.154130  -0.047620 
  0.163805  -0.048323 
  0.173475  -0.048960 
  0.183142  -0.049537 
  0.192809  -0.050060 
  0.202478  -0.050534 
  0.212151  -0.050962 
  0.221828  -0.051349 
  0.231512  -0.051699 
  0.241203  -0.052014 
  0.250902  -0.052297 
  0.260610  -0.052551 
  0.270327  -0.052779 
  0.280054  -0.052981 
  0.289792  -0.053162 
  0.299539  -0.053322 
  0.309297  -0.053469 
  0.319066  -0.053609 
  0.328845  -0.053740 
  0.338635  -0.053862 
  0.348435  -0.053973 
  0.358245  -0.054075 
  0.368066  -0.054164 
  0.377897  -0.054242 
  0.387738  -0.054306 
  0.397590  -0.054358 
  0.407451  -0.054395 
  0.417323  -0.054417 
  0.427204  -0.054424 
  0.437096  -0.054414 
  0.446997  -0.054388 
  0.456907  -0.054345 
  0.466828  -0.054283 
  0.476757  -0.054203 
  0.486697  -0.054104 
  0.496645  -0.053984 
  0.506603  -0.053844 
  0.516570  -0.053683 
  0.526546  -0.053500 
  0.536531  -0.053295 
  0.546525  -0.053066 
  0.556528  -0.052813 
  0.566539  -0.052535 
  0.576559  -0.052232 
  0.586587  -0.051903 
  0.596624  -0.051546 
  0.606669  -0.051161 
  0.616722  -0.050748 
  0.626782  -0.050305 
  0.636851  -0.049831 
  0.646927  -0.049325 
  0.657010  -0.048787 
  0.667100  -0.048215 
  0.677196  -0.047607 
  0.687299  -0.046964 
  0.697409  -0.046284 
  0.707523  -0.045565 
  0.717643  -0.044806 
  0.727768  -0.044006 
  0.737898  -0.043163 
  0.748031  -0.042276 
  0.758168  -0.041343 
  0.768307  -0.040363 
  0.778449  -0.039333 
  0.788591  -0.038253 
  0.798735  -0.037121 
  0.808878  -0.035934 
  0.819020  -0.034690 
  0.829161  -0.033388 
  0.839298  -0.032026 
  0.849431  -0.030600 
  0.859560  -0.029110 
  0.869681  -0.027552 
  0.879796  -0.025925 
  0.889901  -0.024225 
  0.899996  -0.022451 
  0.910079  -0.020600 
  0.920148  -0.018668 
  0.930203  -0.016654 
  0.940240  -0.014555 
  0.950258  -0.012367 
  0.960256  -0.010088 
  0.970232  -0.007715 
  0.980182  -0.005244 
  0.990106  -0.002674 
  1.000000  -0.000000 
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Lednicer format dat file
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Polars for Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe765-il50,000915.1 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   goe765-il50,000528.4 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   goe765-il100,000941.5 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe765-il100,000544.6 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe765-il200,000959.4 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe765-il200,000558.6 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   goe765-il500,000980.4 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe765-il500,000568.5 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe765-il1,000,000985.9 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   goe765-il1,000,000579.6 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
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