ONERA HOR20 AIRFOIL (hor20-il)
ONERA HOR20 AIRFOIL - Onera propeller blade airfoils from US Patent 4
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(hor20-il) ONERA HOR20 AIRFOIL Onera propeller blade airfoils from US Patent 4 Max thickness 20.4% at 24.3% chord. Max camber 3.3% at 51.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
ONERA HOR20 AIRFOIL
57. 61.
0.000000 0.000000
0.001989 0.010702
0.004981 0.019205
0.006977 0.023207
0.009972 0.028310
0.014965 0.035315
0.019959 0.040920
0.024954 0.046125
0.029949 0.050830
0.041290 0.060361
0.054900 0.070185
0.064294 0.075984
0.073949 0.081294
0.083804 0.086184
0.093819 0.090674
0.103955 0.094814
0.114181 0.098584
0.124498 0.102044
0.134905 0.105225
0.145392 0.108105
0.155869 0.110716
0.166317 0.113066
0.176805 0.115197
0.187293 0.117077
0.197821 0.118748
0.224508 0.122085
0.251396 0.124331
0.278104 0.125578
0.304334 0.125874
0.330505 0.125361
0.356836 0.124117
0.383018 0.122213
0.409170 0.119739
0.435353 0.116755
0.461587 0.113292
0.487451 0.109457
0.513675 0.105454
0.539969 0.101100
0.565924 0.096486
0.591748 0.091642
0.617383 0.086607
0.642939 0.081423
0.668454 0.076108
0.693859 0.070684
0.719185 0.065209
0.744480 0.059684
0.769746 0.054150
0.795041 0.048655
0.820397 0.043180
0.845732 0.037666
0.870978 0.032111
0.896183 0.026546
0.921439 0.021031
0.941633 0.016552
0.961848 0.012362
0.979991 0.008880
0.999996 0.004500
0.000000 0.000000
0.002019 -0.018998
0.005026 -0.026395
0.010034 -0.034490
0.015040 -0.040285
0.020045 -0.044880
0.025049 -0.048775
0.030052 -0.052370
0.036936 -0.056383
0.042910 -0.059677
0.048822 -0.062411
0.054625 -0.064745
0.060357 -0.066870
0.066039 -0.068784
0.077242 -0.072003
0.088165 -0.074582
0.098837 -0.076681
0.109308 -0.078391
0.119620 -0.079770
0.129801 -0.080870
0.139902 -0.081700
0.149912 -0.082310
0.159823 -0.082730
0.169663 -0.082980
0.179513 -0.083060
0.189393 -0.082981
0.199233 -0.082751
0.209072 -0.082381
0.218872 -0.081881
0.243000 -0.080217
0.266928 -0.078193
0.291036 -0.075879
0.315623 -0.073114
0.340270 -0.069870
0.364746 -0.066315
0.389392 -0.062481
0.414058 -0.058426
0.438694 -0.054241
0.463280 -0.050017
0.488236 -0.045872
0.512832 -0.041837
0.537358 -0.038123
0.562225 -0.034708
0.587222 -0.031523
0.612409 -0.028518
0.637686 -0.025692
0.662993 -0.023027
0.688401 -0.020532
0.713898 -0.018186
0.739436 -0.015971
0.764984 -0.013905
0.790522 -0.012069
0.815991 -0.010554
0.841479 -0.009419
0.867049 -0.008623
0.892668 -0.008087
0.910007 -0.007290
0.930007 -0.006770
0.950006 -0.006100
0.970005 -0.005480
1.000004 -0.004500
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Polars for ONERA HOR20 AIRFOIL (hor20-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hor20-il | 50,000 | 9 | 4.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 50,000 | 5 | 21.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor20-il | 100,000 | 9 | 34.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 100,000 | 5 | 44.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor20-il | 200,000 | 9 | 61.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 200,000 | 5 | 63.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor20-il | 500,000 | 9 | 91.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 500,000 | 5 | 83.9 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor20-il | 1,000,000 | 9 | 112.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor20-il | 1,000,000 | 5 | 99.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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