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GATE-Aerospace-Engineering-Question-paper-2012-->View question

The stagnation temperatures at the inlet and exit of a combustion chamber are 600 K and 1200 K, respectively GATE-Aerospace Engineering-Question-2012

The stagnation temperatures at the inlet and exit of a combustion chamber are 600 K and 1200 K,respectively. If the heating value of the fuel is 44 MJ/kg and specific heat at constant pressure for air and hot gases are 1.005 kJ/kg.K and 1.147 kJ/kg.K respectively, the fuel-to-air ratio is

(A) 0.0018 (B) 0.018 (C) 0.18 (D) 1.18


Asked On2017-07-06 10:21:33 by:Amogh

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Answer (B) 0.018
In thermodynamics and fluid mechanics, stagnation temperature is the temperature at a stagnation point in a fluid flow. At a stagnation point the speed of the fluid is zero and all of the kinetic energy has been converted to internal energy and is added to the local static enthalpy.

Answerd on:2017-07-13 Answerd By:milan-ransingh

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