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Aviation History
1940
1940 - 0075.PDF
JANUARY II, 1940. doors. It is noteworthy that the list of new features doesnot include the tricycle undercarriage. The tailwheel type of undercarriage is fitted and this would seem to be a retrograde design step in this year of 1940. Blind-landing equipment and technique will im- prove and improve, but pilots will be happier if they can fly their aeroplanes on to the ground when visibility is bad. To do this it is necessary that contact with the ground shall not increase wing incidence, so tending to lift the aeroplane and cause a bounce, which is what happens with a tail- wheel Undercarriage. But the tipping forward of the tri- cycle type decreases incidence and lift and so tends to keep the aeroplane in contact with the ground. Another necessity for blind landing is high-energy absorption in the undercarriage wheels, which in this case are designed for a descent of 8ooft. per min. vertically and have a long travel. A welcome feature in undercarriage design is provided to ensure that no retraction is possible when the aeroplane is on the ground, not even when power is applied. . - - Wing and Tail Design "/-••'.• •'• The wing structurally is of all-metal stressed-skin design with a single main shear beam and an auxiliary web. The skin, stiffened by hat-shaped stringers, carries both bend- ing and torsional loads. Aerodynamically, it is claimed by the company to have good control characteristics and to be free from undesirable tip-stalling. The aerofoil sec- tion is NACA 23017 tapering to NACA 4410.5 and the wing is twisted to give some "washout" towards the tip. Flaps extend from fuselage to aileron and are full trailing edge, slotted type. As the first of their movement is back- wards, so increasing wing area, and then downwards, they can be used in an intermediate position for take-off as well as full down for landing, in which position a landing speed of 70 m.p.h. is estimated. One glance at the tail shows it to be unusual in having dihedral on the tailplane and elevator—or should one say "elevators," for with this design it would appear to be impossible to incorporate that very desirable anti-flutter recommendation—that the two halves of the elevator shall be connected by a spar rigid in torsion. (Of course, a 29 The Curtiss-Wright fuselage cross-section, showing how theshape is formed by two eccentric circles with the cabin floor at their intersection. universal joint could be put in, but this would inevitably cause some reduction in torsional rigidity of the spar.) Two other unusual features are the high setting of the tailplane on the fuselage and the fact that the fins are not vertical, but cant in slightly. The aspect ratio of the tailplane appears to be normal, CURTISS-WRIGHT 36-passenger CIVIL TRANSPORT (rwo Wright Cyclone 14 engines) Lengin Height Tail Uotrw • Wing Span Wing Area Tread DIMENSIONS .. 75/?. Old. . »• 19/J. 2m. .*• . W8fl. Old. ... l,353s7./2.. ... 25fl. lli». (22.87 Hi) (5.84 m) (32.»1 m) (125.69 m1) (7.00 m) ENGINES • ••"-'-. •'•'•-.'- Two Wright Double Row Cyclone 14 (take-off power 1,800 *./>.) or two Wright DupUx Cyclones. AIRSCREWS Cmiits cons'tml-spad full-feathering electric type. limpty Useful Load Gross .,. WEIGHTS CYCLONE 14 DUH.EX CYCLONB 24,750 Ib.... (11.227 kg.)...28^40 Ib....(12,718 *«.> 13,250.'6:... (6,010*?.) ...14,900/4.... (6,786ft?.) 38,000 ft-....(17,237 for.)... 43,000 Ib....(10,504 kg.) Maximum Speed Cruising Speeti Loading speed ojctm j'^ -- " AEROFOIL SECTION NACA 23017 tapering to NACA 4410.5 with washota. , TANKAGE 4 wing tanks holding 1,000 U.S. gallons. MATERIAL •..--.'. ••••'.." i . .•/: Alclai 24 ST. ACCOMMODATION * Dav seals 30 to 40. Sleeper berths 20. Crete 3 to 5. Cabin height at centre <Sfi. llm. Extreme cabin width 9ft. Win. Seat spacing 41t«. CARGO Hold volume 550 at. ft. Maximum weight 5,200 Ib. PERFORMANCE CYCLONE 14 DUPLEX CYCLONE 243 m.p.ft....(300.«9 k.p.h.)...2Ti m.p.h....(439.26 k.p.h.) rt..* ... i ,- /.TOT Oft t, >. !. \ O'iA u. J, It /'ITA n"7 fc A 7< A210 m.p.h....(337.89 k.p.h.)...230 m.p.h....(37O.O7A.M.) 70 IH./>.»....(112.63 k.p.h.)... 74 m.p.h....(119.07 *./>.&•) ./mi»....(43S.9 m./mm.)...1,750 ft./min....(533.39 m./mifi.i Single ensine ceiling 13 000J? (3,962 m.) 14,000/( (4,267 f».) W««g/oa/;«s £8.1 Ib.jsq. ft....(137.24 Ag./m2)...31.8 W./sj./K. ...(155.22 ftg./m')
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