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Aviation History
1934
1934 - 0074.PDF
FLIGHT, JANUARY 25, 1934 THE The latest Lockheed product which cruises at 180 m.p.h. with a 2,200 Ib. pay load THE Lockheed " Electra "is an all-metal low-wingmonoplane of compara-tively small overall dimensions and low power, butpossessing a remarkable perform- ance as the result of clean aero-dynamic design. The all-metal wings are of fullcantilever construction, the centre section being built integral withthe fuselage. To facilitate the replacement of damaged wings, theouter sections are detachable from a point just outside of thenacelles. The surface is smooth skin throughout, and rivets aremade flush over part of the upper surface where they would offer re-sistance. The construction is of the " stressed skin " type, with heavycorrugations under the skin, making it possible for a person towalk down the centre portion of the wing without causing damage.The skin over the centre section and part of the outer wings is ofheavy-gauge duralumin of the latest type manufactured by theAluminium Company, namely, 24 S.T. All outer skin is Alclad24 S.T., which has remarkable corrosion-resisting properties. Theinterior of the wings and centre section are carefully cleaned andcoated with Lionoil. The centre section, which contains thenacelles, fuel tanks and cargo compartments, is cut away at thefuselage, which is placed partly within the wing, giving the air-craft a very small frontal area. The ailerons are in the conven-tional positions at the trailing edge and tip. Inboard of theailerons are the wing flaps, which extend through under the fuse-lage. These flaps give an increase in lift of approximately 25 percent, and a large increase in drag. Although a reduction in the load LOCKHEED " ELECTRA THE LOCKHEED ' MODEL 2 " WASP JUNIORS 'ELECTRA" 10A " TYPE S.B. Dimensions Length SpanRoot chord Tip chord Wing area Wing incidence Dihedral—median line. . Aerofoil section Wing taper in planAspect ratio ' Overall height TrackAirscrews Passenger cabin capacity Front baggage compart-ment Wing baggage compart- mentMaximum width of cabin Maximum height of cabin Areas Fin Rudder Tail plane ElevatorsAilerons Weights Gross weightWeight empty Disposable loadPower loading Wing loading 38 ft. 7 in. 55 ft.145 in. 48ft in.458-3 sq. ft. 0 deg. 5 deg. 34 min. (root) Clark Y-1S, (tip) Clark Y-9. 3-1.6-6. 10 ft. 1 in. 13 ft. 7 in.Smith control- lable pitch. 300 cu. ft. 40 cu. ft. 28 cu. ft.58£ in. 60 in. 15 sq. ft. 16-9 sq. ft. 48 sq. ft. 33-6 sq. ft.29-2 sq. ft. 9,000 lb.5,455 lb. 3,545 1b.10-71 lb./h.p. 19-64 Ib./sq. ft. Performance Maximum speed at 8,000 IT. Cruising speed at 5,000ft. Landing speed at sea level (with flaps) Maximum rate of climbat sea level Service ceiling Fuel capacity Oil capacityCruising range Cruising duration 215 m.p.h. 190 m.p.h. at 2.000 r.p.m. 63 m.p.h. 1,350 ft./min.20,000 ft. 200 gall. 14 gall.750 miles at 48 gal./hr. 4-17 hr. at 48 gal./hr. factors for multi-engined trans-ports has been allowed by the Department of Commerce, this hasnot been used in the wings of the " Electra." In fact, the wholemachine has been designed to single-engine factors. The monocoque fuselage isconstructed entirely of 24 S.T. duralumin. A smooth skin ofAlclad 24 S.T. is used throughout. This skin is reinforced and held inplace at frequent intervals by channel bulkheads and longi-tudinal stringers. The skin over the passenger cabin is 0.032 in.thick. Special attention has been given to the lail of the fuselageto give rigid support to the canti- lever empennage and tail wheel.Seating accommodation is pro- vided for ten passengers, but fewerpassengers and a correspondingly larger baggage or mail load maybe carried. A lavatory is situated at the rear of the cabin. The tail plane and elevator reston top of the fuselage in which position the maximum protectionis afforded from flying stones. Forward of the pilot's cabin is abaggage compartment of 40 cu. ft. capacity, reinforced so that thebaggage will not injure the outer skin of the fuselage. A removabletail fairing forms the end of the fuselage and houses the tail wheel.Easy access is given to all moving parts of the empennage. The engine nacelles are locateddirectly ahead of the leading edge of the wing. According to testsconducted by the N.A.C.A-, this arrangement gives the lowest dragand the maximum lift. Wind tunnel tests with the " Electra,"with and without nacelles, proved that the lift was the same in eachcase. The nacelle structure and engine mountings are of steeltubes. Numerous large holes are provided for inspection. Thenacelle not only supports the en- gines but also the landing gearand retracting mechanism. The tail surfaces are cantilevermetal structures with smooth skin covering. Fin and tail plane are 74
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