Page History

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Author: Rajesh Bhaskaran, Cornell University

{color:#cc0000}{*}Problem Specification{*}{color}
[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]
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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]

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