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Author:

Rajesh

Bhaskaran,

Cornell

University {color:#cc0000}{*}Problem Specification{*}{color} [1.

University

Problem Specification
1. Pre-Analysis

&

Start-up

|FLUENT - Compressible Flow in a Nozzle- Step 1] [


2.

Geometry|FLUENT - Compressible Flow in a Nozzle- Step 2] [3. Mesh|FLUENT - Compressible Flow in a Nozzle- Step 3] [4. Setup (Physics)|FLUENT - Compressible Flow in a Nozzle- Step 4 *New] [5. Solution|FLUENT - Compressible Flow in a Nozzle- Step 5 *New] [6. Results|FLUENT - Compressible Flow in a Nozzle- Step 6 *New] [7. Verification & Validation|FLUENT - Compressible Flow in a Nozzle- Step 7] [Problem 1|FLUENT - Compressible Flow in a Nozzle- Problem 1] [Problem 2|FLUENT - Compressible Flow in a Nozzle- Problem 2] {panel} h2. Problem Specification !nozzle2.jpg! Consider air flowing at high-speed through a convergent-divergent nozzle having a circular cross-sectional area, _A_, that varies with axial distance from the throat, _x_, according to the formula A = 0.1 + x{^}2^; \-0.5 < x < 0.5 where _A_ is in square meters and _x_ is in meters. The stagnation pressure _p{_}{_}{~}o{~}_ at the inlet is 101,325 Pa. The stagnation temperature _T{_}{_}{~}o{~}_ at the inlet is 300 K. The static pressure _p_ at the exit is 3,738.9 Pa. We will calculate the Mach number, pressure and temperature distribution in the nozzle using FLUENT and compare the solution to quasi-1D nozzle flow results. The Reynolds number for this high-speed flow is large. So we expect viscous effects to be confined to a small region close to the wall. So it is reasonable to model the flow as inviscid. Go to [Step 1: Pre-Analysis & Start-up|FLUENT - Compressible Flow in a Nozzle- Step 1] [See and rate the complete Learning Module|Fluent - Compressible Flow in a Nozzle-Full] [Go to all FLUENT Learning Modules|FLUENT Learning Modules]

Geometry
3. Mesh
4. Setup (Physics)
5. Solution
6. Results
7. Verification & Validation
Problem 1
Problem 2

Problem Specification

Image Added

Consider air flowing at high-speed through a convergent-divergent nozzle having a circular cross-sectional area, A, that varies with axial distance from the throat, x, according to the formula

A = 0.1 + x2; -0.5 < x < 0.5

where A is in square meters and x is in meters. The stagnation pressure po at the inlet is 101,325 Pa. The stagnation temperature To at the inlet is 300 K. The static pressure p at the exit is 3,738.9 Pa. We will calculate the Mach number, pressure and temperature distribution in the nozzle using FLUENT and compare the solution to quasi-1D nozzle flow results. The Reynolds number for this high-speed flow is large. So we expect viscous effects to be confined to a small region close to the wall. So it is reasonable to model the flow as inviscid.

Go to Step 1: Pre-Analysis & Start-up

See and rate the complete Learning Module

Go to all FLUENT Learning Modules