HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il)
HUGHES HELICOPTERS HH-02 AIRFOIL - Hughes helicopters HH-02 rotorcraft airfoil
| Details | Dat file | Parser | |
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(hh02-il) HUGHES HELICOPTERS HH-02 AIRFOIL Hughes helicopters HH-02 rotorcraft airfoil Max thickness 9.6% at 30% chord. Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
HUGHES HELICOPTERS HH-02 AIRFOIL
40. 40.
0.0000000 0.000000
0.0005000 0.002830
0.0010000 0.004050
0.0020000 0.005940
0.0035000 0.008190
0.0050000 0.010090
0.0065000 0.011760
0.0080000 0.013270
0.0100000 0.015100
0.0125000 0.017170
0.0160000 0.019750
0.0200000 0.022370
0.0250000 0.025310
0.0350000 0.030290
0.0500000 0.036400
0.0650000 0.041370
0.0800000 0.045530
0.1000000 0.050120
0.1250000 0.054680
0.1500000 0.058280
0.2000000 0.063280
0.2500000 0.066080
0.3000000 0.067380
0.3500000 0.067500
0.4000000 0.066400
0.4500000 0.063910
0.5000000 0.060080
0.5500000 0.055040
0.6000000 0.048910
0.6500000 0.041740
0.7000000 0.033440
0.7500000 0.024030
0.8000000 0.014360
0.8500000 0.004810
0.9000000 -0.004310
0.9250000 -0.003940
0.9500000 -0.002030
0.9750000 -0.000060
0.9900000 0.001120
1.0000000 0.001900
0.0000000 0.000000
0.0005000 -0.002840
0.0010000 -0.003880
0.0020000 -0.005320
0.0035000 -0.006830
0.0050000 -0.008000
0.0065000 -0.008950
0.0080000 -0.009780
0.0100000 -0.010720
0.0125000 -0.011720
0.0160000 -0.012900
0.0200000 -0.014040
0.0250000 -0.015240
0.0350000 -0.017140
0.0500000 -0.019430
0.0650000 -0.021270
0.0800000 -0.022760
0.1000000 -0.024320
0.1250000 -0.025750
0.1500000 -0.026750
0.2000000 -0.027930
0.2500000 -0.028430
0.3000000 -0.028340
0.3500000 -0.027550
0.4000000 -0.026000
0.4500000 -0.023770
0.5000000 -0.021040
0.5500000 -0.017970
0.6000000 -0.014820
0.6500000 -0.011760
0.7000000 -0.009520
0.7500000 -0.008510
0.8000000 -0.008890
0.8500000 -0.009840
0.9000000 -0.010410
0.9250000 -0.007770
0.9500000 -0.005830
0.9750000 -0.003870
0.9900000 -0.002690
1.0000000 -0.001900
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Polars for HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hh02-il | 50,000 | 9 | 30.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 50,000 | 5 | 33.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hh02-il | 100,000 | 9 | 46.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 100,000 | 5 | 45.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hh02-il | 200,000 | 9 | 60.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 200,000 | 5 | 56.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hh02-il | 500,000 | 9 | 76.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 500,000 | 5 | 72.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hh02-il | 1,000,000 | 9 | 89.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hh02-il | 1,000,000 | 5 | 84.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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