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Aviation History
1946
1946 - 0462.PDF
a38 FLIGHT MARCH JTVS, 1940 FREIGHTER AND WAYFARER speed-range, but this may be simplified in the production aircraft. There are spring tabs both on the elevator and the rudder, plus a normal trimmer tab on the former and a reverse servo-cum-trhnmer tab on the latter. Separate geared-servo and trimmer tabs are fitted to each of the ailerons. As a matter of interest, the only real troubles experienced during the Freighter development test work have been concerned with control characteristics and, initially, the fore and aft control situation was further involved by the fact that the tailplane position was already known to be too high. The original design was for Perseus engines and, pending the results of further wind-tunnel tests on the Hercules engined version, work on the original structure was continued. Power Services An electro-hydraulic system is used for the operation of the only two services which require power—the freight doors and the flaps. The Wayfarer has a 24-volt generator in each nacelle, and an electrically driven hydraulic pump unit, mounted in the aft part of the control cabin, supplies the power; a hand-pump being provided for use in case of a power failure. So that the freight doors may still be operated on the ground without excessive loading on the accumulator, the Freighter version has only one engine- driven generator, a second being driven by an auxiliary power unit in the control cabin. Here, also, is a combus- tion heater for the crew of the Freighter, with a second and larger heater for providing the necessary cabin warmth in the passenger-carrying Wayfarer. Throughout the design of the 170 it is obvious that a major effort has been applied to the problems involved in assuring both a quick turn-round when in use, and rapid and easy servicing generally. There are ample inspection panels, each of which has a quick-action thumb-operated locking catch, and, wherever possible, these panels are con- The control cabin layout of the 170 is exceptionally tidy,with a central control bank and, in the Wayfarer, individual blind-flying panels. This view is of the cabin of the pro-! totype. A four-point, quick-release engine-mounting, rationalised control, electrical and pipeline connections, and "unit" installation of ancillaries make the work of engine-changinga simple matter. veniently placed both from the working and accessibility point of view. Above the leading edges between power unit and fuselage are large hinged doors through which the con- trol cables and incidental pipelines can be reached for inspection; and hinged panels, with built-in jury struts, are arranged in the engine cowlings so that casual inspec- tion and attention are simplified. As already explained, the engines and their accessories DIMENSIONS AND PERFORMANCE FREIGHTER AND WAYFARER 2 Bristol Hercules 131 (take-off power 1,675 b.h.p. each) ESTIMATED DATA Maximum all-up weight " ... 36,500 1b. Span ... 98ft. Length 68ft. 4in. Height (over fin) 21ft. Sin. Wing area 1,405 sq.ft. Wing loading 26 1b/sq.ft. Geometric mean chord 14ft. 4in. Span loading ratio 3.8 Service ceiling ... ... ... ... ... ... ... 20,000ft. Maximum still-air range (at 140 m p h ) ... ... ... 1,085 miles Maximum level speed (at 8,000ft ) 236 m.p.h. Stalling speed (flaps up) 85 m.p.h. ,, ,, (flaps down) 73 m.p.h. PERFORMANCE AT FULL LOAD Fuel Altitude B.H.P. Level speed consumption feet perengine m.p.h. galls./hour Maximum power... Sea level 1,675 215 363 (S min. limit) ... 5,000 1,745 230 379 Maximum weak ... Sea level 1,175 190 138 Mixture power ... 5,000 1,230 200 143 Weak mixture cruising ... 5,000 960 180 109 Weak mixture cruising ... 5,000 700 150 80 Take-off distance to clear 50ft barrier (concrete runway) „. 650 yds. Landing distance over 50ft. barrier (concrete runway) ... 700 yds. 'late of climb at full load and max. continuous power : sea level I,l35ft./min. 5,000ft I,l30ft./min. Single-engine Performance (airscrew feathered) Take-off distance to clear 50ft. barrier with one engine failed at " unstick " (on concrete runway) 1,050 yds. Rate of climb at maximum power at sea level ... ... 3l0ft./min. Rate of climb at rated power at 5,000ft Il5ft./min. (Take off, landing, and single-engined performance estimates are based on a head- wind not exceeding 5 m.p.h.)
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