ONERA HOR07 AIRFOIL (hor07-il)
ONERA HOR07 AIRFOIL - Onera propeller blade airfoils from US Patent 4
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(hor07-il) ONERA HOR07 AIRFOIL Onera propeller blade airfoils from US Patent 4 Max thickness 7.2% at 23.2% chord. Max camber 4.5% at 39.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
ONERA HOR07 AIRFOIL
45. 56.
0.000000 0.000000
0.003773 0.008671
0.009040 0.014252
0.014225 0.017769
0.021437 0.021708
0.026576 0.024189
0.032220 0.026756
0.035803 0.028218
0.041616 0.030503
0.046460 0.032340
0.056549 0.035851
0.066638 0.039130
0.074678 0.041625
0.084785 0.044712
0.094963 0.047639
0.105200 0.050404
0.115476 0.053007
0.125779 0.054976
0.136122 0.056935
0.146511 0.059900
0.156884 0.061859
0.167242 0.062810
0.177626 0.064768
0.188010 0.066727
0.198403 0.068685
0.224553 0.071566
0.245079 0.073873
0.295448 0.076422
0.345806 0.077158
0.396155 0.076082
0.446497 0.073697
0.496832 0.070204
0.547160 0.065301
0.597484 0.059491
0.647803 0.052977
0.698119 0.045858
0.748437 0.038941
0.798755 0.032125
0.849071 0.025107
0.899390 0.018492
0.919517 0.015665
0.949708 0.011575
0.969835 0.008848
0.989963 0.006222
1.000026 0.004909
0.000000 0.000000
0.003168 -0.006372
0.008110 -0.008896
0.012996 -0.010423
0.018026 -0.011457
0.023057 -0.012199
0.028090 -0.012770
0.033123 -0.013109
0.043191 -0.013667
0.053261 -0.013922
0.065345 -0.013987
0.074410 -0.013855
0.085490 -0.013441
0.095565 -0.012740
0.105640 -0.011887
0.116108 -0.011188
0.126315 -0.010216
0.136482 -0.009213
0.146608 -0.008200
0.156705 -0.007166
0.166802 -0.006123
0.176918 -0.005070
0.187015 -0.004006
0.197102 -0.002922
0.207179 -0.001828
0.232209 0.000827
0.257147 0.003211
0.295072 0.006532
0.315223 0.008236
0.335372 0.009639
0.355519 0.010437
0.375665 0.011336
0.395817 0.013242
0.426034 0.014086
0.456252 0.014931
0.496540 0.015722
0.526757 0.016566
0.556969 0.016404
0.597251 0.016188
0.627461 0.015723
0.657670 0.014957
0.697945 0.013431
0.728151 0.012161
0.758355 0.010589
0.798627 0.008459
0.828831 0.006685
0.848965 0.005369
0.869100 0.004052
0.899303 0.002178
0.919436 0.000559
0.939571 -0.000657
0.959705 -0.002075
0.979840 -0.003391
0.989907 -0.004140
0.994940 -0.004480
0.999974 -0.004909
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Polars for ONERA HOR07 AIRFOIL (hor07-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hor07-il | 50,000 | 9 | 43.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor07-il | 50,000 | 5 | 43.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor07-il | 100,000 | 9 | 61.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor07-il | 100,000 | 5 | 59.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor07-il | 200,000 | 9 | 78.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor07-il | 200,000 | 5 | 73 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor07-il | 500,000 | 9 | 98 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor07-il | 500,000 | 5 | 80.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hor07-il | 1,000,000 | 9 | 106.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hor07-il | 1,000,000 | 5 | 88.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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