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
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(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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Polars for Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe765-il | 50,000 | 9 | 15.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 50,000 | 5 | 28.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 100,000 | 9 | 41.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 100,000 | 5 | 44.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 200,000 | 9 | 59.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 200,000 | 5 | 58.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 500,000 | 9 | 80.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 500,000 | 5 | 68.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 1,000,000 | 9 | 85.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 1,000,000 | 5 | 79.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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