HOR12 Airfoil

Onera propeller blade airfoils from US Patent 4,773,825

HOR12 Airfoil (x,y) Co-ordinates

0 0
0.002017 0.007742
0.004025 0.011585
0.006031 0.014479
1.00E-02 0.019218
0.014047 0.023157
0.018053 0.026446
0.022057 0.029286
0.026652 0.032324
0.031207 0.035322
3.58E-02 0.03804
0.040465 0.040578
0.045148 0.043026
0.049881 0.045374
0.059457 0.04976
0.069182 0.053826
0.079096 0.057592
0.08911 0.061087
0.099212 0.064332
0.109385 0.067327
0.119596 0.070093
0.129857 0.072658
0.140178 0.075023
0.150548 0.077198
0.160888 0.079174
0.171208 0.080989
0.181567 0.082644
0.191915 0.08415
0.202294 0.085505
0.228448 0.088294
0.2548 0.090292
0.280821 0.091542
0.306691 0.092142
0.332539 0.092203
0.358476 0.091733
0.384282 0.090804
0.410107 0.089466
0.435951 0.087757
0.461815 0.085668
0.487397 0.083301
0.513459 0.080652
0.539211 0.077694
0.564882 0.074506
0.590432 0.071099
0.615902 0.067532
0.641342 0.063826
0.666741 0.059979
0.692081 0.056042
0.71739 0.052046
0.742699 0.04799
0.767958 0.043923
0.793277 0.039817
0.818615 0.035631
0.843914 0.031325
0.869162 0.026949
0.89442 0.022532
0.919688 0.018026
0.939891 0.014382
0.960094 0.011187
0.980297 0.007892
1.00047 0.004497
0.99953 -0.004497
0.979114 -0.002391
0.958718 -0.000255
0.938322 0.001791
0.917935 0.003107
0.89244 0.004365
0.866953 0.005264
0.841457 0.005942
0.815999 0.00637
0.790591 0.006489
0.765153 0.006307
0.739683 0.005916
0.714224 0.005395
0.688774 0.004754
0.663354 0.003992
0.638004 0.003091
0.612693 0.00202
0.587402 0.000789
0.5622 -0.000613
0.537108 -0.002224
0.512105 -0.004096
0.487401 -0.006258
0.462217 -0.008669
0.437323 -0.011221
0.412408 -0.013862
0.387464 -0.016514
0.362509 -0.019125
0.337175 -0.021636
0.312761 -0.024068
0.287857 -0.02629
0.263114 -0.028322
0.238691 -0.030295
0.214067 -0.032238
0.20415 -0.032954
0.194183 -0.033621
0.184227 -0.034218
0.17424 -0.034735
0.164274 -0.035182
0.154327 -0.035559
0.144331 -0.035845
0.134285 -0.036042
0.12419 -0.036129
0.114055 -0.036086
0.10384 -0.035882
0.093545 -0.035509
0.083141 -0.034925
0.072568 -0.034051
0.061826 -0.032807
0.0564 -0.031995
0.050935 -0.031053
0.04543 -0.029981
0.039876 -0.028669
0.034272 -0.027016
0.028659 -0.025124
0.020779 -0.022517
0.01395 -0.019123
0.009958 -0.016415
0.005968 -0.012808
0.003974 -0.010454
0.001983 -0.006801
0 0

HOR12 Airfoil CAD files

DOWNLOAD FROM HERE

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