ONERA HOR12 AIRFOIL (hor12-il)
ONERA HOR12 AIRFOIL - Onera propeller blade airfoils from US Patent 4
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(hor12-il) ONERA HOR12 AIRFOIL Onera propeller blade airfoils from US Patent 4 Max thickness 11.9% at 22.8% chord. Max camber 3.7% at 46.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
ONERA HOR12 AIRFOIL
61. 61.
0.000000 0.000000
0.002017 0.007742
0.004025 0.011585
0.006031 0.014479
0.010040 0.019218
0.014047 0.023157
0.018053 0.026446
0.022057 0.029286
0.026652 0.032324
0.031207 0.035322
0.035811 0.038040
0.040465 0.040578
0.045148 0.043026
0.049881 0.045374
0.059457 0.049760
0.069182 0.053826
0.079096 0.057592
0.089110 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 0.084150
0.202294 0.085505
0.228448 0.088294
0.254800 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
0.717390 0.052046
0.742699 0.047990
0.767958 0.043923
0.793277 0.039817
0.818615 0.035631
0.843914 0.031325
0.869162 0.026949
0.894420 0.022532
0.919688 0.018026
0.939891 0.014382
0.960094 0.011187
0.980297 0.007892
1.000470 0.004497
0.000000 0.000000
0.001983 -0.006801
0.003974 -0.010454
0.005968 -0.012808
0.009958 -0.016415
0.013950 -0.019123
0.020779 -0.022517
0.028659 -0.025124
0.034272 -0.027016
0.039876 -0.028669
0.045430 -0.029981
0.050935 -0.031053
0.056400 -0.031995
0.061826 -0.032807
0.072568 -0.034051
0.083141 -0.034925
0.093545 -0.035509
0.103840 -0.035882
0.114055 -0.036086
0.124190 -0.036129
0.134285 -0.036042
0.144331 -0.035845
0.154327 -0.035559
0.164274 -0.035182
0.174240 -0.034735
0.184227 -0.034218
0.194183 -0.033621
0.204150 -0.032954
0.214067 -0.032238
0.238691 -0.030295
0.263114 -0.028322
0.287857 -0.026290
0.312761 -0.024068
0.337175 -0.021636
0.362509 -0.019125
0.387464 -0.016514
0.412408 -0.013862
0.437323 -0.011221
0.462217 -0.008669
0.487401 -0.006258
0.512105 -0.004096
0.537108 -0.002224
0.562200 -0.000613
0.587402 0.000789
0.612693 0.002020
0.638004 0.003091
0.663354 0.003992
0.688774 0.004754
0.714224 0.005395
0.739683 0.005916
0.765153 0.006307
0.790591 0.006489
0.815999 0.006370
0.841457 0.005942
0.866953 0.005264
0.892440 0.004365
0.917935 0.003107
0.938322 0.001791
0.958718 -0.000255
0.979114 -0.002391
0.999530 -0.004497
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Polars for ONERA HOR12 AIRFOIL (hor12-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hor12-il | 50,000 | 9 | 30.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor12-il | 50,000 | 5 | 38 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor12-il | 100,000 | 9 | 54.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor12-il | 100,000 | 5 | 57.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor12-il | 200,000 | 9 | 76.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor12-il | 200,000 | 5 | 76.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor12-il | 500,000 | 9 | 103.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor12-il | 500,000 | 5 | 97.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor12-il | 1,000,000 | 9 | 121.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor12-il | 1,000,000 | 5 | 108.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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