Author: Rajesh Bhaskaran, Cornell University

**Problem Specification**

1. Pre-Analysis & Start-up

2. Geometry

3. Mesh

4. Setup (Physics)

5. Solution

6. Results

7. Verification & Validation

Problem 1

Problem 2

## Problem Specification

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*

*at the inlet is 300 K. The static pressure*

_{o}*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