Rocket Nozzle Design and Fluid Flow Analysis

True (A)

4.5 to 8.0

<p>reactants</p> Signup and view all the answers

<p>Combustion chamber = Occurs during combustion at constant pressure Adiabatic expansion = Process in the nozzle for gas products Chemical equilibrium = Rate of forward and reverse reactions are equal Solid propellant rocket motors = Propellant contained in combustion chamber</p> Signup and view all the answers

<p>To channel and accelerate the combustion products (A)</p> Signup and view all the answers

<p>True (A)</p> Signup and view all the answers

<p>throat</p> Signup and view all the answers

<p>kinetic energy</p> Signup and view all the answers

<p>Maintains constant mass flow (D)</p> Signup and view all the answers

<p>incompressible</p> Signup and view all the answers

<p>Throat = The narrowest part of the nozzle where gases are compressed Nozzle = Guides exhaust gases to maximize velocity Thrust = The force produced by expelling exhaust gases Compressible Fluid = A fluid that exhibits significant density changes</p> Signup and view all the answers

<p>True (A)</p> Signup and view all the answers

<p>Conical nozzle (A)</p> Signup and view all the answers

<p>False (B)</p> Signup and view all the answers

<p>To accelerate the combustion products to a high exit velocity.</p> Signup and view all the answers

<p>enthalpy</p> Signup and view all the answers

<p>Conical nozzle = Diverges at a constant angle Bell/contoured nozzle = Minimizes turning divergence losses Annular nozzle = Combustion occurs around the base Expansion-deflection nozzle = Flow deflected by a plug</p> Signup and view all the answers

<p>Continuity equation (B)</p> Signup and view all the answers

<p>False (B)</p> Signup and view all the answers

<p>specific heats</p> Signup and view all the answers

<p>Isentropic flow.</p> Signup and view all the answers

<p>Annular nozzle (B)</p> Signup and view all the answers

<p>True (A)</p> Signup and view all the answers

<p>It affects fluid properties such as velocity, density, pressure, and temperature.</p> Signup and view all the answers

<p>Mach number</p> Signup and view all the answers

<p>Spike nozzle = Prominent spike center body Linear-aero-spike = Configuration without a pointed spike Truncated aerospike = Flat base replacing pointed spike Reverse-flow nozzle = Exhaust gases rotated 180º</p> Signup and view all the answers

<p>Grain (B)</p> Signup and view all the answers

<p>False (B)</p> Signup and view all the answers

<p>Metal, composite fiber</p> Signup and view all the answers

<p>8-pointed star</p> Signup and view all the answers

<p>Wrapped (C)</p> Signup and view all the answers

<p>Accelerate the hot gas</p> Signup and view all the answers

<p>Insulation layer</p> Signup and view all the answers

<p>True (A)</p> Signup and view all the answers

<p>Structural integrity</p> Signup and view all the answers

<p>It should have a predictable erosive burning. (B)</p> Signup and view all the answers

<p>False (B)</p> Signup and view all the answers

<p>It is where liquid propellants are injected, mixed, and burned to create thrust.</p> Signup and view all the answers

<p>casting</p> Signup and view all the answers

<p>Double-base (DB) = Homogeneous grain with fuel and oxidizer Extruded double-base (EDB) = Made by mechanical mixing and extrusion Cast composite (CDB) = Utilizes synthetic rubber as a binder Extruded propellant = Commonly used for rocket engines</p> Signup and view all the answers

<p>Cost of air travel (D)</p> Signup and view all the answers

<p>False (B)</p> Signup and view all the answers

<p>To raise the pressure of the propellants and feed them to the thrust chambers.</p> Signup and view all the answers

<p>oxidizer</p> Signup and view all the answers

<p>Injector, combustion chamber, nozzle (A)</p> Signup and view all the answers

<p>Cold gas propellant (D)</p> Signup and view all the answers

<p>True (A)</p> Signup and view all the answers

<p>Hydrogen peroxide or hydrazine</p> Signup and view all the answers

<p>hybrid</p> Signup and view all the answers

<p>Hydrogen peroxide (H2O2) = Decomposes at a slow rate during storage Nitric acid (HNO3) = A high-density yellow-brown liquid Nitrogen tetroxide (N2O4) = Commonly used with hydrazine fuels Liquid oxygen (O2) = Burns brightly with hydrocarbon fuels</p> Signup and view all the answers

<p>Gelled propellant (D)</p> Signup and view all the answers

<p>False (B)</p> Signup and view all the answers

<p>To store one component in liquid and the other in solid phase.</p> Signup and view all the answers

<p>corrosion</p> Signup and view all the answers

<p>Excellent heat transfer properties (C)</p> Signup and view all the answers

<p>True (A)</p> Signup and view all the answers

<p>Oxidizer feed system-induced instability.</p> Signup and view all the answers

<p>nitric acid (HNO3)</p> Signup and view all the answers

<p>Cryogenic propellant = Stored at low temperatures Cold gas propellant = Reliable and simple system Monopropellant = Single substance with oxidizer Hybrid propellant = Liquid and solid components</p> Signup and view all the answers

A nozzle with a converging and diverging section, designed to efficiently accelerate exhaust gases to supersonic speeds.

The narrowest section of a nozzle, where exhaust gases are compressed to high pressure.

The force produced by the expanding gases pushing against the nozzle walls.

The gases expelled from a rocket engine.

The energy of the hot chamber gases is transformed into the kinetic energy that drives the rocket.

Flow where the direction of the fluid is along a straight line.

Part of a rocket engine that accelerates combustion products to increase exhaust speed.

A fluid whose density changes significantly with pressure.

The pressure inside the combustion chamber where fuel and oxidizer burn, usually kept constant during the combustion process.

The process where combustion products expand rapidly and adiabatically through the nozzle, accelerating to high speeds.

States that the total pressure of a gas mixture is the sum of the partial pressures of each individual gas, all at the same temperature.

The ideal proportion of fuel and oxidizer for maximizing rocket engine performance, usually slightly richer than the stoichiometric ratio.

A state in a reversible reaction where the rates of forward and reverse reactions are equal, resulting in a constant concentration of reactants and products.

A type of rocket engine that uses a solid propellant to generate thrust.

A type of rocket engine that uses a liquid propellant to generate thrust.

The solid body of hardened propellant in a solid rocket motor.

A component that initiates combustion in a solid rocket motor.

The shape formed by the burning surface of a grain with a central cylindrical cavity and eight tapered slots.

A hole or passage through the grain.

The central cylindrical cavity in a grain.

A protective layer that shields the case from high temperatures generated by combustion.

Propellant grains manufactured directly in the rocket case, forming a strong bond.

Propellant grains manufactured separately and inserted into the rocket case.

The shape and arrangement of the solid propellant within a rocket motor, designed to control the burn rate and thrust profile.

Choosing the right propellant for a rocket based on performance, mechanical properties, safety, and cost.

Ensuring the propellant grain can withstand stresses from pressure, acceleration, and temperature changes.

The space within the propellant grain where combustion occurs, impacting burn rate and stability.

The manufacturing process used to create the propellant grain, impacting cost and quality.

Propellants that contain both fuel and oxidizer in the same chemical compound, often used for high-performance applications.

Propellants where fuel and oxidizer are separate components, often combined with a rubber binder.

The combustion chamber of a liquid-propellant rocket engine, where the propellants mix, burn, and create thrust.

A device that mixes and atomizes liquid propellants before they enter the combustion chamber.

The components that deliver the liquid propellants from their tanks to the thrust chamber.

A flow that depends only on the cross-sectional area, requiring frictionless and adiabatic flow.

The sum of internal thermal energy and flow work, often expressed as specific heat times absolute temperature.

A statement of the principle of conservation of energy in a system.

A mathematical form of the principle of conservation of mass in steady flow.

Properties of a fluid if its velocity were reduced to zero.

A dimensionless flow parameter, defined as the ratio of flow velocity to local acoustic velocity.

A simple nozzle design with walls diverging at a constant angle.

A more efficient nozzle, minimizing divergence losses. Its shape creates isentropic flow.

A nozzle design with combustion occurring along a ring.

A nozzle type forcing exhaust gasses into a converging throat, followed by bell shaping.

Fuel injected from underneath, exhaust flipped 180 degrees.

Fuel injected sideways, exhaust rotated 90 degrees.

Nozzle with a pointed spike at the center.

A spike nozzle without the pointed spike, but with a flat base.

Determination of specific heats, thermal conductivity, and specific heat ratio.

A propellant system that uses two separate components, one oxidizer and one fuel, stored separately and mixed only in the combustion chamber.

A single substance that acts as both oxidizer and fuel, containing both components in a single material.

A propellant stored at very high pressure, releasing gas energy for thrust.

A liquid stored at extremely low temperatures, used as a propellant, like liquid oxygen or hydrogen.

Liquid propellants that can be stored at room temperature for long periods.

A propellant with a thickening agent, creating a thixotropic liquid with a jelly-like consistency.

A substance that reacts with fuel to provide oxygen for combustion, typically stored in liquid form.

A rocket propulsion system that combines a liquid oxidizer with a solid fuel.

A kind of instability in the oxidizer supply system, caused by compressibility and insufficient isolation from the engine.

An acoustic instability in the combustion chamber, often observed in solid fuel ramjets.

A commonly used liquid oxidizer in rocket engines, burning with a bright white-yellow flame.

A highly concentrated liquid oxidizer used in rockets, decomposing during storage, releasing gas.

A common liquid oxidizer, storable and often used with hydrazine-based fuels.

A high-density, storable liquid oxidizer used with fuels like hydrazine, producing a powerful thrust.