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Aviation History
1931
1931 - 0773.PDF
Juv 24, 1931 Supplement to FLIGHT Edited by C. M. POULSEN July 24, 1931 CONTENTS Air-Cooled Engine Power and Weight. By W. R. Andrews,A.F.R.Ae.S. .. •- ". Correction of Aeroplane Performance to Standard Atmosphere(Density Basis). By Clifford W. Tinson, F.R.Ae.S., M.I.Ae.E. ... A Formula for the Buoyancy of the Wing Floats of Flying Boats andSingle Float Seaplanes. ' By A. R. Collins Technical Literature 49 51 5556 which is of great concern to aircraft and engine designers. With a view to investigating a purely hypothetical case of an aircraft using an engine of fixed b.h.p. and having a given range, the writer obtained empirical formulae for engine power and weight. AIR-COOLED ENGINE POWER AND WEIGHT. BY W. R. ANDREWS, A.F.R.Ae.S. Mr. Andrews, who is on the Technical Staff of A. V. Boe dc Co., Ltd., has previously contributed articles to THE AIRCRAFT ENGINEER. In the present article he turns his attention to the question of thrust horse- power available at the airscrew for every pound of engine and fuel. Empirical formula have been evolved, which appear to give at least sufficient accuracy for preliminary investigations, Mr. Andrews basing his forrnulce on the assumption that power output is pro- portional to cylinder capacity. THE question of the thrust horse-power available at the airscrew for every pound of engine and fuel is one 405 350 ui2 (3 -•Z " 1 ,'; ZD WC "6. TOTAL EN81 **" VX, J, 300 iSO HE CA«\CsTY- (CUBIC !NS.) These formulae are sufficiently accurate over a large range of powers to be of use to others interested in similar problems. As pointed out, these relationships are only empirical, and their only justification is that they agree with the actual conditions within limits which are not too large. The varying factors in engine design, such as crank- shaft r.p.m., number of cylinders, capacity of cylinders, materials used, etc., would at first sight make the task of generalising almost hopeless. However, it is obvious that since cylinder capacity is somewhat limited by various considerations, as is also the compression ratio, then the power output is pro- portional to total cylinder capacity at the satne design, r.p.m. 726a
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