FlightGlobal.com
Home
Premium
Archive
Video
Images
Forum
Atlas
Blogs
Jobs
Shop
RSS
Email Newsletters
You are in:
Home
Aviation History
1928
1928 - 0595.PDF
JULY 5, 1928 THE CIERVA "AUTOGIRO" "C.8. MARK II.' Two-Seater, Dual Control, with 180 H.P. "Lynx" Engine GENERAL As is now generally known, a more or less standard typeof " Autogiro " has been evolved combining the advantages of safety which are characteristic of this invention, withperformance possibilities of the ordinary fixed wing aero- plane. This type embodies the construction and a numberof components of the Avro " Lynx " Training Aircraft 504/N, in so far as applicable with the autogiro rotor in place of thefixed wings. Fuselage.—Standard Avro type of construction modified where necessary to accommodate the Autogiro rotor system. Undercarriage and Tail Skid.—Two-wheel, with wide trackand oleo and compression rubber legs. Steerable tail skid with compression rubber springs. Rotor System.—Four blades, doubly articulated. Central hub running on four ball bearings (two radial, two thrust) ; loads transmitted to structure by cabane of four steel tube struts. Rotor Blades.—Single steel tube spar, spruce ribs, fabriccovered ; leading edge reinforced with 3-ply top and bottom. Adjustable, easily accessible weights at blade tips forbalancing. Auxiliary and Control Surfaces.—Stabilising monoplane, semi-cantilever, spruce spars covered 3-ply and fabric throughout, carrying normal type unbalanced ailerons. Adjustable tailplanc and elevators horn balanced, and balanced rudder of standard Avro type. Accommodation and Pilots' Controls.—Two cockpits intandem with complete dual control, including tail trimming gear. Rotor lateral trimming gear in front cockpit. Machineand engine controls are of standard type. Removable balance weights in after end of fuselage toallow of machine being flown as single seater from front cockpit. Power Plant Engine Total horse-powerPropeller drive . . Fuel capacity ..Placing of fuel tanks Fuel supply Armstrong-Siddeley " Lynx IV" 210 b.h.p.Direct. 24 gallons (108 litres).In fuselage. Direct gravity feed. Main Dimensions Diameter of rotorLength o.a. Overall height— Tail down Tail upSpan of stabilising plane Span of aileronsWheel track 39 ft. 8 in. (12-1 m.). 36 ft. Oin. (11 m.). 14 ft. 9 in. (4-5 m.).13 ft. 0 in. (3-96 m). 23 ft. 2 in. (7 m.).7 ft. 3 in. (2-21 m.). 11 ft. Oin. (3-35 ra.). Weights and Loading Weight empty 1,735 lbs. (790 kg.).Fuel (24 gallons) .. .. 182 lbs. (83 kg.). Oil (3J gallons) 35 lbs. (16 kg.).Crew (two) 360 lbs. (164 kg.). Extra disposable load .. . . 50 lbs. (22-7 kg.).Total loaded weight .. .. 2,380 lbs. (1075-7 kg.). Performance Maximum speed (sea level)Cruising speed Minimum speed..Rate of climb (sea level) Endurance (at cruising speed)Normal rotor speed 100 m.p.h. (153 krn./h.). 85 m.p.h. (129 km./h.). 25 m.p.h. (40 km./h.). 500 ft./min. (2-54 m./sec. 3 hours. 115 r.p.m. 543 G2
Sign up to
Flight Digital Magazine
Flight Print Magazine
Airline Business Magazine
E-newsletters
RSS
Events
