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Aviation History
1956
1956 - 0360.PDF
358 FLIGHT LEADING DATA Length (blades folded), 28ft Sin; width (blades folded). 7ft 4jin.; height, 10ft 2in; main rotor diameter, 32ft Oin; max. tip speed, 560ft/sec; blade section, NACA 23017; tail rotor diameter, 6ft Oin; normal gross weight, 2,150 Ib; max. gross weight, 2,200 Ib; max. disc loading, 2.73 Ib/sq ft. Performance (Assuming normal grots weight, ISA. sea-level conditions, and based on measured performance at Boscombe Dawn.) Max. forward speed, 88 let; max. cruising speed, 86 kt; endurance (at 45 kt), 3.3 hr; range (at 75 kt), 206 n. miles; hover ceiling (free air), 1,100ft; hover ceiling (with ground effect), 4,100ft; vertical rate of climb, 230ft/min; best climbing speed, 45 kt; max. rate of climb, 1,020ft/min; service ceiling, 11,700ft; absolute ceiling, 12,900ft. Engine Performance Max. 1 hr power 200 b.h.p. at 2,600 r.p.m. (sea level) Max. continuous power 190 b.h.p. at 2,500 r.p.m. (sea level) Max. wrak-mixtur* power 166 b.h.p. at 2,500 r.p.m. (3,500ft) Fuel consumption at max. 1 hr. power 97 Ib/hr (sea level) Fuel consumption at max. weak-mixture power 70 Ib/hr (3,500ft) 6ft die TAIL ROTOR (MAX. R.P.M. 1.769). BLADES SECTION R.A.E. 100 (15 per centi IMPROVED-WOOD SPAR. BALSA FILLING. FABRIC WRAPPED TORQUE SHAFTING TO TAIL ROTOR 4. 8 0 */ I C [ R SAUNDERS-ROE SKEETER ... pitch is applied just before touchdown, the throttle/collective-pitch linkage must be disconnected. This is accomplished by means of a twist-grip over-ride against a spring load on die throttlecontrol linkage, with a lock which can be immediately released if power is required. Once the twist-grip is locked, full collectivepitch can be applied with the engine idling. In normal use, the twist-grip handles to -the collective-pitchlever give an over-riding throttle control, so that the power output of the engine may be matched to the rotor power requirements.The twist grips are mechanically linked together. To enable the collective-pitch lever to be set in any desired position, or the"feel" to be adjusted, a friction clamp is provided on the starboard side of the control box, between the pilots' seats. The starboardthrottle twist-grip is similarly fitted with a knurled friction-nut ring below the grip itself. The pitch-change mechanism of the tail rotor, which is of the"see-sawing" type, is actuated by movement of the rudder pedals. Cables from these pedals run back to a short chain which passesover a sprocket on the end of the tail-rotor gearbox. The sprocket is attached to a screw-jack assembly which, in turn, operates a (Concluded at foot of page 374) Below, climb performance: (left) vertical climb at max. one-hour power (200 b.h.p.); (centre) max. rate of climb of max. continuous power. Right (upper and lower), havering performance at max. one-hour rating. Sea-level I.S.A. conditions are assumed. apoo 4poo apoo V9OO VKIO 2000 2,100 AIRCRAFT WEIGHT (lb| ijOOO £. eoo ooo 2OO \ \ . A.U.W . 1 \ *i „ \ WOO K V»oo J \200 tpOO IBOO WOO 2OOO 2JOO 2£O0 AIRCRAFT WEKSHT (IB) o lpoo 'J900 zpoo 2joo AIRCRAFT WEKSHT (ib) 8000 apoo APOO apoo N N \ T J<i-Tp -It O| S| 5!l-Si si 1 v i N. iIS 1! is 1pOO lpOO 2pOO AIRCRAFT WEIGHT (ibj 2200
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