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Aviation History
1941
1941 - 0152.PDF
pads for centre section, landing gear fork and tail wheel, i tail wheel steering fork, i Librascope (load distribu- tion computer), i set Lockheed special tools. Compass. Airspeed Indicator. Turn and Bank Indicator. Ver- tical Speed Indicator. Clock. Gyro Horizon. Direc- tional Gyro (with ball-bank). Sensitive Altimeter. Car- burettor Air Temperature Indicators. Fuel Pressure Warning Lights. Outside Air Temperature Indicator. Fuel Gauges. Fuel Gauge Selector Switch. Landing Gear Position Indicator. Wing Flap Position Indicator. WEIQHT8 ModelNumber 18-K)18-14 18-40 18-50 18-56 Engine Type V & W SIC3-G ...P&WS4C4-G ... Wright G-102A ... Wright G-202A ... Wright G-205A ... Standard Gross Weight 1b. 17,50017,500 17,500 17,500 17,500 Weight Empty lb. 12,21612,291 11,(533 11,830 11,846 Useful Load (Standard) lb. 5,2845,209 5,867 5,664 5.654 I.—Weight empty includes an allowance of 230 lb. for installation of two- way radio. Weights based on data available November 1st, 1940. For airline use only there is a provisional gross weight of 18,500 lb. For this case the useful load is then 1,000 1b. above the standard useful load. DIMENSIONS Length, overall (thrust line level) 49ft. lOin. Span 65ft. Oin. Span of the horizontal tail 25ft. lOiii. Mean aerodynamic chord ... 115.8in. Landing gear tread ... ... 15ft. 4in. Incidence of wins 2deg. Aspect ratio 7.7U12ft. 3in. 17ft. 10in. lift. llin. 28.5 to 39.0 per cent. M.A.C. 551 sq. ft. 74.4 sq. ft. Height over cabin (datum line level)... Height over tail (tlatum line level) ... Height over cabin (3-pt. landing) C.G. range (C.A.A. approved) Projected wing area, including fuselage Area covered by fuselage ....... Landing gear Hydraulic retracting Size of main wheel tyres 42.3in. Size of auxiliary wheel tyre 18in. Volume of passenger cabin ... ... ... ... 747 cu. ft. Volume of cargo compartments ... ... ... 190 cu. ft. Maximum height inside cabin... ... ... ... 6ft. 3in. Maximum length inside cabin 24ft. fliu. Maximum width inside cabin ... ... ... 65in. Aisle width (average) ... ... ... ... ... llin. Seat spacing 37in. JANUARY I6TH, 1941. THE LOCKHEED LODESTAR (Continued) The Lockheed-Fowler wing flaps are of large area and movebackward and downward to ensure a reasonable landing speed though wing loading is high. v LOADINGS Lodestar Model 18-10 18-14 18-40 18-50 18-50 P Engine Type P&WSIC3-G ...(14 cyl.). P&WS4C4-G ... (14 cyl.). Wright G-102A ... (0 cyl.).Wright G-202A ... (9 cyl.).Wright G-205A ... (0 cyl.). Power, Take-off and Normal 12001050 1200 1050 1100 9001200 10001200 1000 Standard Gross Weight— 17,500 Is. lb./h.p. 7.298.3S 7.208.33 7.95 U.727.2» 8.757.29 8.75 Wing Ldg. 31.76 31.76 33.76 31.76 31.76 Airscrews : 10ft. 6in. diameter. Normal fuel capacity : 644 U.S. gallons. Normal oil capacity : 40 or 44 U.S. gallons. For provisional gross weight of 18,500 lb. wing loading is 33.5. ,.....; PERFORMANCE (Provisional gross weight of 18,500 Ib., except as noted.) Engineering Design MAXIMUM SPEED Sea Level Critical Alt. with ramLow blower ... High blower CRUISING SPEED at Cruising Power At sea levelAt 5,000ft At 12,000ft Maximum TAKE-OFF & LANDING 1 Max T.O. run—S.L. / Distance required to clear 50ft. obstacle standing start—S.LDistance required to stop after clearing! 50ft. ob-stacle—S.L Landing speed—S.L.+ ... RATE OF CLIMB Maximum at S.L. normal power—2 engines Max. at S.L.—1 Eng.* ... CEILINGS Absolute—2 engines ... Absolute—1 engine* ..."Service—2 engines ... •"Usable—1 engine* ... Unit m.p.h.m.p.h. m.p.h. % h.p. b.h.p./eng. m.p.h.m.p.h. m.p.h. m.p.h. Sec. ft. ft. ft. m.p.h. ft./min. ft./min. ft. ft.ft. ft. 8IC3-G 18 10 238263 at 8800ft. 62 650 208217 232 239 at15000ft. 18 985 1870 1750 65 1850 370 25700 1190023500 10900 S4C4-6 18-14 238263 at 8800ft.276 at 16700ft. 62 650 208217 232 248 at19000ft. 18 985 1870 1750 65 1850 370 28000 1300027000 10900 G-102A 18-40 228250 at 7900ft. 69£ 625 204214 229 22Bat12000ft. 18 1080 1970 1750 65 1480 200 23000 900021800 8000 G-202A 18-50 236259 at 8200ft. 65 650 208217 232 23» at15000ft. 18 985 1870 1750 65 1730 303 24500 1050023500 9500 G-205A. 18-56 236252 at 5800ft.271 at 15300ft. 65 650 208217 232 248 at19000ft. 18 985 187(1 1750 65 1730 303 27000 1300026000 10000 * Note.—* Inoperative propeller feathered. •• Service ceiling is altitude where rate of climb is 100 ft./min. ••• Usable ceiling is altitude where rate of climb i 50 ft./min. I At standard gross weight of 17,500 Ib. R.A.F. NEEDS ENGINEER-OFFICERS ENGINEER and other technical officers are still requiredin the Royal Air Force, and commissions in the R.A.F.V.R. for the duration of the war will be granted tosuitable applicants between the ages of 21 and 50 years. In making this announcement, the Air Ministry stressed thepoint that candidates who have previously applied for such commissions should not renew their applications, and also thatthose engaged on the production of aircraft, engines or acces- sories, or on other important national work should, beforesubmitting their applications, consult their employers as to the possibility of their being spared for R.A.F. duties. Certain qualifications are required and the vacancies fallunder the headings of Engineer, Armament and Signals. In the first of these, the applicants should either hold amechanical engineering degree, be a member of an appropriate institution and alt:o have had at ]east two years' practical ex-perience, or be a practical engineer who has served an appren- ticeship followed by a number of years' experience with I.C.engines and aircraft structures. The armament applicant should possess similarly appropriate engineering qualifications,experience in armament manufacture being a particular advan- tage. Signals applicants should either be holders of electrical engineering or science degrees with experience of wireless, orholders of technical-college or approved institution diplomas with two years' experience in telecommunications engineering. Vacancies also exist for candidates possessing a soundtheoretical knowledge of elementary magnetism and electricity and of the principles of wireless telegraphy and telephony.Some practical experience is desirable. Candidates for any of these vacancies should apply in writingto the Air Ministry S.7 (e) 1, Adastral House, Kingsway, W.C.2, and give full particulars of their qualifications, trainingand experience. New Publication HTHE Journal of the Aeronautical Sciences has an offspring,•*• which commenced as a monthly in November. Known as The Aeronautical Review, the new publication deals exclusivelyin reviews of books and articles and in lists of reference on aero- nautical subjects. It is intended for all the busy people whocannot read all the technical matter but find it essential to know of. the various sources of information. In its own words," The Aeronautical Review is not a substitute for books and magazines, but a guide to and through them."
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