This structure investigates subsonic and supersonic air flow, including flow around two-dimensional models.

• Laboratory-scale wind tunnel for subsonic and supersonic tests, nominally up to Mach 1.8
• Supplied with aerodynamic models for supersonic tests – including model angle-feedback encoder
• Supplied with a set of different liners for controlled subsonic and supersonic air flow
• Induction flow for better air flow and accurate results

Learning Outcomes

• Pressure distribution along a convergent/divergent (Laval) nozzle with subsonic and supersonic air flow
• Comparison of theoretical and actual pressure distributions
• Comparison of actual and theoretical area ratios of a nozzle at supersonic air velocities
• Pressures around a two-dimensional model in subsonic and supersonic flow conditions, at different angles of incidence
• Lift coefficients for aerodynamic models in supersonic flow
• Shock waves and expansion patterns around a two-dimensional model in supersonic flow conditions

Essential Ancillaries:

• Air Compressor Receiver and Dryer (AF300B)
• Versatile Data Acquisition System – Frame-mounted version

Recommended Ancillaries:

• Schlieren Apparatus (AF300A)