Post by Br. Marius on Feb 8, 2015 16:53:06 GMT
A main rotor and helicopter characteristics are given as:
Rotor
4 blades, radius = 25 feet, chord = 1.5 feet
Tip speed = 700 feet/sec, flap frequency = 1.036/rev
Lock number = 8.0
Airfoil CL = 5.73α, Cd = 0.01
Vehicle
Weight = 18,000 lbs
h = 6.0 ft, lT = 32 ft
flat plate area = 25 ft2
xcg = 2 feet forward of shaft axis, ycg = 0
Engine shaft HP = 2000
Assume MxF = 0, and MyF = 0
Assume uniform induced inflow in hover and forward flight with correction factors κhover = 1.15, and κFF = 1.00
(a) Calculate for hover at sea level
(a) shaft HP required
(b) control settings
(c) maximum climb velocity
(d) flap response
Rotor
4 blades, radius = 25 feet, chord = 1.5 feet
Tip speed = 700 feet/sec, flap frequency = 1.036/rev
Lock number = 8.0
Airfoil CL = 5.73α, Cd = 0.01
Vehicle
Weight = 18,000 lbs
h = 6.0 ft, lT = 32 ft
flat plate area = 25 ft2
xcg = 2 feet forward of shaft axis, ycg = 0
Engine shaft HP = 2000
Assume MxF = 0, and MyF = 0
Assume uniform induced inflow in hover and forward flight with correction factors κhover = 1.15, and κFF = 1.00
(a) Calculate for hover at sea level
(a) shaft HP required
(b) control settings
(c) maximum climb velocity
(d) flap response