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Created by Prop.exe - Version Beta3 18Mar2001
Copyright (C) 2001 Microaernautics : For free distribution only

Monday, June 18, 2001 @ 20:22
Input Data File : propChar.txt
Data items flagged with an @ are input data.

ATMOSPHERIC CONDITIONS

@ Air Temperature = 21.00 deg C ( 69.80 deg. F)
@ Pressure Altitude = 0.500 km ( 1640.4 ft)
@ Relative Humidity = 70.0 percent
Pressure = 716.04 mm Hg ( 28.19 in. Hg)
Speed of Sound = 343.82 m/sec ( 769.1 stat mi/hr)
Kinematic Viscosity = 16.08E-6 m^2/sec (173.1E-6 ft^2/sec)
Air Density = 1.1306 kg/m^3 ( 2.194 E-3 slug/ft^3)
Density Altitude = 0.899 km ( 2948.4 ft)

AIRCRAFT & FLIGHT CHARACTERISTICS

@ Aircraft Drag Area = 35.20 cm^2 ( 5.456 in^2)
@ Airspeed = 59.00 m/sec (132.0 stat mi/hr)
Dynamic Pressure = 1967.82 N/m^2 ( 41.10 lbf/ft^2 )
Thrust Power = 408.68 w (0.548 HP)
Thrust power = power reqd. @ 100% prop eficiency
@ Engine speed = 430.00 Hz ( 25800.0 RPM)
Flight Helix Pitch = 137.21 mm ( 5.402 in)

PROPELLER CHARACTERISTICS

@ Number of Blades = 2
@ Diameter = 163.00 mm ( 6.417 in)
Effective Diameter = 133.76 mm ( 5.266 in.)
@ Zero Lift AOA = -2.50 deg
@ AoA Above Zero Lift = 6.00 deg.
AOA from reference line =3.50 deg
Const. Rn for Chord = 200000
Thrust Loading = 0.2505
Ideal Efficiency = 0.9357
Advance Ratio (J) = 0.8418
Inflow Pitch Incr = 9.43 mm ( 0.371 in.)