It runs at 6000 rpm with an air-fuel ratio of 15:1. The ratio of venturi throat 8.8 The cubic capacity of a four-stroke SI engine is 50 cc. diameter to the fuel jet diameter is 10. The engine works with . volumetric efficiency of 75%. The venturi throat diameter is 10 m with a discharge coefficient of 0.85. The discharge coefficient of fuel nozzle is 0.65. Specific gravity of the fuel is 0.75. Calculate the lin height of the fuel nozzle. Take atmospheric conditions as 1 bar and 300 K. Neglect compressibility effect. Ans: 3.89 mm

It runs at 6000 rpm with an air-fuel ratio of 15:1. The ratio of venturi throat 8.8 The cubic capacity of a four-stroke SI engine is 50 cc. diameter to the fuel jet diameter is 10. The engine works with . volumetric efficiency of 75%. The venturi throat diameter is 10 m with a discharge coefficient of 0.85. The discharge coefficient of fuel nozzle is 0.65. Specific gravity of the fuel is 0.75. Calculate the lin height of the fuel nozzle. Take atmospheric conditions as 1 bar and 300 K. Neglect compressibility effect. Ans: 3.89 mm

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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Thermodynamic Relations

Thermodynamics is the division of physics that deals with the transfer of any kind of energy, whether it be heat, temperature, or work, from one object to another.

Question

please solve 8.8..

276
IC Engines
8.8 The cubic capacity of a four-stroke SI engine is 50 cc. It runs
6000 rpm with an air-fuel ratio of 15:1. The ratio of venturi throsk
diameter to the fuel jet diameter is 10. The engine works with
volumetric efficiency of 75%. The venturi throat diameter is 10 mm
with a discharge coefficient of 0.85. The discharge coefficient of fuel
nozzle is 0.65. Specific gravity of the fuel is 0.75. Calculate the lip
height of the fuel nozzle. Take atmospheric conditions as 1 bar and
300 K. Neglect compressibility effect.
Ans: 3.89 mm
LEGO
8.9 Determine the air-fuel ratio supplied at 4000 m altitude by a carbu-
retor which is adjusted to give a stoichiometric air-fuel ratio at sea
level where air temperature is 300 K and pressure is 1 bar.
Assume that the temperature of air decreases with altitude given by
ts - 0.00675h
where h is height in metres and ts is sea level temperature in °C. The
air pressure decreases with altitud

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