Consider a rocket that burns steadily. The higher pressure in the combustion chamber, the faster the...

Consider a rocket that burns steadily. The higher pressure in the combustion chamber, the faster the propellant burns. Why is this? The relationship is such that the higher the pressure, the closer the gaseous flame is to the surface and the more effectively it can transfer heat back to the surface thereby gasifying the propellant quicker. The rate of gas generation, ?_? , can be described by the equation: ?_?=?_1 ?^?, where P is the pressure, and C1 and n are the constants for a given propellant with given exposed surface area.

The hot gas leaving the rocket must pass through the throat of the exhaust nozzle at sonic velocity.

▪The higher the pressure, the greater the density of this gas and the greater the rate of mass flow at sonic velocity. (The speed of sound in a gas is independent of pressure.) Accordingly, the rate of gas escape, ??r_e , is described by the equation: ??=?2?r_e=C_2 P where C2 is a constant, dependent on cross section area of the nozzle throat and on the velocity of sound in the combustion products.

▪What is the steady operating pressure of a solid-propellant rocket for the given values of the constants C1 , C2, and n? What values of n keep it stable?

PLEASE WRITE CLEARLY AND EXPLAIN WHY IS THE ANSWER THE WAY IT IS PLEASE THANK YOU

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Colby Messinger answered 1 year ago

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