At this speed, the volumetric efficiency of the engine is 92%, Apa 0.07 bar, C, 0.85, C =2. A four-stroke, 6-eylinder, 3.6 Itr SI engine, is designed to have a maximum speed of 6000 F-p.a0.6, fuel density =700 kg/m'. At sea level the air temperature and pressure are 27°C and 1bar réspectively, and AF 15. Caleulate: (i) Throat diameter of the carburetor. (i1) Fuel ome!!area. (iii) AF at altitude of 3000 m.

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bar respectively, and AF = 15. Calculate: (i) Throat diameter of the carburetor. (ii) Fuel orifice 0.6, fuel density 700 kg/m'. At sea level the air temperature and pressure are 27°C and 1.03 A four-stroke, 6-cylinder, 3.6 Itr SI engine, is designed to have a maximum speed of 6000 r.p.m. At this speed, the volumetric efficiency of the engine is 92%, Apa 0.07 bar, C, 0.85, Cf= At this speed, the volumetric efficiency of the engine is 92%, Apa 0.07 bar. C, 0,83, Cr %3D %3D bar respectively, and AF 15. Calculate: (i) Throat diameter of the carburetor. (ii) Fuel orifice %3D area. (iii) AF at altitude of 3000 m.

bar respectively, and AF = 15. Calculate: (i) Throat diameter of the carburetor. (ii) Fuel orifice 0.6, fuel density 700 kg/m'. At sea level the air temperature and pressure are 27°C and 1.03 A four-stroke, 6-cylinder, 3.6 Itr SI engine, is designed to have a maximum speed of 6000 r.p.m. At this speed, the volumetric efficiency of the engine is 92%, Apa 0.07 bar, C, 0.85, Cf= At this speed, the volumetric efficiency of the engine is 92%, Apa 0.07 bar. C, 0,83, Cr %3D %3D bar respectively, and AF 15. Calculate: (i) Throat diameter of the carburetor. (ii) Fuel orifice %3D area. (iii) AF at altitude of 3000 m.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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6. A four-stroke, 6-cylinder, 3.6 Itr SI engine, is designed to have a maximum speed of 6000 r.p.m. At this speed, the volumetric efficiency of the engine is 0.92, fuel density is 700 kg/m C 15. Calculate: (1) %3! 0.85, C 0.6, Apg = 0.07 bar, at sea level T, = 27°C, p. = 1.03 bar, and AE Throat diameter of the carburetor. (2) Fuel orifice area. (3) AF at altitude of 4000 m
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TThe venturi of a simple carburetor has a throat diar the coefficient of flow is 0.8. The fuel orifice has a and the coefflicient of fuel flow is 0.65. The gasolin surface is 5 mm below the throat, calculate * of 20 mm and er of 1.14 mm when the nozzle (i) the air-fuel ratio for a pressure drop of 0.0. tip is ne arted (ii) the aiaeDW atio when the nozzle tip is taken into account (iii) the minimum velocity of air or critical air velocity requi red to start the fuel flow when the nozzle tip is provided. Assume the density of air and fuel as 1.20 and 750 kg/m respectively.
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The Venturi of a simple carburetor has a throat diameter of 25 mm and the coefficient of air flow is 0.87. The fuel orifice has a diameter of 1.35 mm and the coefficient of the fuel flow is 0.66. The petrol surface is 6 mm below the throat. Find (a) The air-fue ratio for a pressure drops of 0.07 N/m² when the nozzle tip is neglected. (b) The air-fuel ratio when the nozzle tip is taken into account (c) the minimum velocity of air or critical air velocity required to start the fuel flow when nozzle tip is provided. Take the density of air and fuel as 1.2 and 750 kg/m³ respectively.
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