Investigates subsonic and supersonic air flow, including flow around two dimensional models report aeronautical lab 1

Objectives:

• 1. Pressure distribution along a convergent/divergent (Laval) nozzle with subsonic and
• supersonic airflow
• 2. To compare the experimental results with that calculated from 1-D frictionless flow.
• 3. To comparison of actual and theoretical area ratio of a nozzle at supersonic air velocities
• (Mach numbers).
• 4. Pressures around a two-dimensional model in subsonic and supersonic flow conditions, at
• different angles of incidence Angle.
• 5. Lift coefficient for aerodynamic models in supersonic flow

Description

A compressed air supply induces a flow in the working section of the wind tunnel. This gives a less turbulent and

more stable flow for accurate results and comparison with theory. Students use a delivery valve to allow

compressed air to enter the wind tunnel. The wind tunnel includes two analogue pressure gauges. One measures

the compressed air pressure available from the supply (for reference); the other measures the pressure delivered

to the wind tunnel and includes an analogue transducer that connects to record the pressure.

The working section of the wind tunnel is a convergent divergent nozzle with a removable top part (‘liner’). The

shape of the liner controls the maximum air velocity at the divergent part of the working section. Included are

three different liners.

High optical-quality glass windows (‘portals’) are at each side of the divergent part of the working 

section. 

Spaced at precise intervals along the working section of the wind tunnel are pressure taps. Two extra taps

connect to one of the models when in use. Hg manometer displays the pressures and you must transmits them to

paper for instant recording and calculations of pressure ratios and Mach numbers.

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