Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il)

HUGHES HELICOPTERS HH-02 AIRFOIL - Hughes helicopters HH-02 rotorcraft airfoil


Airfoil hh02-il
Details Dat file Parser  
(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
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

RAF 28 AIRFOILPreviewDetails
SD7084 (9.6%)PreviewDetails
NACA 2410PreviewDetails
S3016-095-87PreviewDetails
S3021-095-84PreviewDetails
SD8040 (10%)PreviewDetails
RG 14 9.5% AIRFOILPreviewDetails
SD7080 (9.2%)PreviewDetails
S3014-095-85PreviewDetails
MH 45 9.85%PreviewDetails

Polars for HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hh02-il50,000930.5 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   hh02-il50,000533.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hh02-il100,000946.5 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   hh02-il100,000545.5 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hh02-il200,000960.9 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hh02-il200,000556.7 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hh02-il500,000976.4 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hh02-il500,000572.2 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hh02-il1,000,000989.3 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hh02-il1,000,000584.4 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit