Intermittent Supersonic Wind Tunnel

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)
Intermittent Supersonic Wind Tunnel Image

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. The essential compressed air supply includes filters and air dryers to give the dust-free and dry air source needed for good results.

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