ONERA HOR04 AIRFOIL (hor04-il)
ONERA HOR04 AIRFOIL - Onera propeller blade airfoils from US Patent 4
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(hor04-il) ONERA HOR04 AIRFOIL Onera propeller blade airfoils from US Patent 4 Max thickness 4.1% at 33.2% chord. Max camber 1.4% at 38.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
ONERA HOR04 AIRFOIL
60. 51.
0.000000 0.000000
0.001417 0.003301
0.003433 0.005163
0.005446 0.006562
0.007460 0.007761
0.009472 0.008729
0.012490 0.009935
0.015507 0.010970
0.020062 0.012271
0.025139 0.013430
0.030236 0.014519
0.035343 0.015406
0.040439 0.016294
0.045545 0.017081
0.050641 0.017868
0.060852 0.019241
0.071074 0.020513
0.081285 0.021786
0.091495 0.022908
0.101716 0.023960
0.111936 0.024961
0.122156 0.025892
0.132376 0.026743
0.142595 0.027513
0.152815 0.028233
0.163044 0.028913
0.173263 0.029553
0.183482 0.030142
0.193711 0.030682
0.203939 0.031171
0.229500 0.032202
0.255060 0.032973
0.280620 0.033582
0.306179 0.034112
0.331728 0.034501
0.357276 0.034769
0.383086 0.034966
0.408843 0.034440
0.434208 0.033975
0.459794 0.033500
0.485409 0.032763
0.510974 0.031836
0.536508 0.030758
0.562001 0.029580
0.587495 0.028341
0.618333 0.027366
0.648468 0.026062
0.678601 0.024457
0.708735 0.022952
0.738868 0.021246
0.769001 0.019440
0.799133 0.017634
0.829266 0.015828
0.859398 0.013921
0.889531 0.011914
0.919663 0.009907
0.939750 0.008435
0.959838 0.006963
0.979926 0.005490
1.000015 0.004521
0.000000 0.000000
0.001396 -0.003189
0.003401 -0.004602
0.005408 -0.005262
0.008389 -0.006005
0.011432 -0.006447
0.015449 -0.006771
0.020471 -0.006989
0.025494 -0.007146
0.030517 -0.007222
0.035540 -0.007229
0.040563 -0.007215
0.045586 -0.007211
0.055632 -0.007264
0.075724 -0.007430
0.095816 -0.007496
0.115909 -0.007461
0.136002 -0.007326
0.156094 -0.007291
0.176187 -0.007156
0.196280 -0.007121
0.216372 -0.007086
0.236465 -0.007051
0.256557 -0.007016
0.276650 -0.006981
0.296744 -0.006545
0.326884 -0.006141
0.357024 -0.005536
0.387165 -0.005031
0.417305 -0.004427
0.447446 -0.003621
0.477588 -0.002815
0.507729 -0.002009
0.537870 -0.001204
0.568011 -0.000599
0.598152 0.000006
0.628292 0.000510
0.658432 0.000914
0.688571 0.001218
0.718711 0.001421
0.748849 0.001423
0.778988 0.001324
0.809126 0.001126
0.839263 0.000726
0.869400 0.000225
0.899536 -0.000476
0.919626 -0.001245
0.939716 -0.002013
0.959806 -0.002782
0.979896 -0.003651
0.999985 -0.004521
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Polars for ONERA HOR04 AIRFOIL (hor04-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hor04-il | 50,000 | 9 | 28.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor04-il | 50,000 | 5 | 32.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor04-il | 100,000 | 9 | 45.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor04-il | 100,000 | 5 | 40.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor04-il | 200,000 | 9 | 54.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor04-il | 200,000 | 5 | 46.2 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor04-il | 500,000 | 9 | 61.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor04-il | 500,000 | 5 | 58.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor04-il | 1,000,000 | 9 | 68.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor04-il | 1,000,000 | 5 | 70.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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