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University of Oxford T6 Piston Reflected Shock Tunnel

University of OxfordOxford

NWTF describes Oxford’s T6 as a multi-mode facility for reflected-shock, expansion-tunnel and shock-tube research driven by a free piston. The listed applications include boundary-layer, intake, supersonic combustion and freeflight studies. Conflicting speed figures and undated installation wording prevent a single current performance or commissioning claim.

Reviewed by Arc · About this review

Key facts

Multi-mode research facility
The page describes reflected-shock-tunnel, expansion-tunnel and shock-tube modes driven by the T3 free-piston driver.

Testing capabilities

High-enthalpy aerodynamic research

Specialist rigs are listed for boundary-layer stability and transition, supersonic or hypersonic intakes, supersonic combustion and freeflight testing.

Fast flow and surface measurements

The source lists high-response pressure transducers, thin-film heat-transfer gauges, fast Schlieren and laser-based optics, and freeflight data acquisition. Gauge and pressure-transducer sensitivity and frequency-response calibration are listed research uses.

Equipment and published limits

Public information not available. Contact test facility provider for more information.

Access and contact

The NWTF page offers an information route for industry and academic users. Confirm the selected mode, current commissioned equipment and its measured flow conditions directly before planning a programme.

Facility contact

Address
Oxford

Standards and accreditation

Public information not available. Contact test facility provider for more information.

What to confirm with the facility

  • The current page’s introduction and performance block give different speed figures, and the linked undated sheet has installation-status wording. No single maximum speed or present commissioning status is stated here; confirm the selected mode and current performance with the operator.
  • Agree the working gas, model support, flow region, heat-transfer and pressure measurements, run conditions and reporting before requesting tests.

Before requesting a test

Public information not available. Contact test facility provider for more information.

Frequently asked questions

Public information not available. Contact test facility provider for more information.

  • University of Oxford High Density Tunnel

    Compare hypersonic tunnel Schlieren flow visualisation for the proposed article. Agree hypersonic test article, optical arrangement, pressure/enthalpy and flow chemistry, run duration and image objective.

  • University of Oxford Low Density Tunnel

    Compare hypersonic tunnel Schlieren flow visualisation for the proposed article. Agree hypersonic test article, optical arrangement, pressure/enthalpy and flow chemistry, run duration and image objective.

Further reading

  • Aerodynamics and aerothermal testing

    Browse aerodynamics and aerothermal testing for Fast flow and surface measurements. Compare the documented article, method and conditions in each entry.

  • Write a test procedure for a requirement

    For hypersonic tunnel Schlieren flow visualisation; Schlieren or fast surface/flow diagnostics, specify the material or product, preparation, apparatus, loading or measurement steps and required observations before requesting a report.

Sources and review

Arc reviewed the current NWTF facility page and its linked undated data sheet on 13 October 2026. The guide retains supported identity and methods and records the specific source conflict. The data-sheet status is not treated as the current commissioning status. Confirm current equipment, configuration and project suitability with the operator.

Arc publishes this directory entry and does not operate the test facility. Suggest a correction to Arc with a supporting source.

  1. T6 Piston Reflected Shock - NWTF

    National Wind Tunnel Facility (NWTF) · Reviewed

    The exact current NWTF page supports named T6 identity and published multi-mode methods. Its greater-than-20 km/s introduction is inconsistent with an 8 km/s performance block and is not used as a verified universal speed.

  2. University of Oxford T6 Free Piston Reflected Shock Tunnel HS2 data sheet (undated)

    National Wind Tunnel Facility (NWTF) · Reviewed

    The observed linked data sheet is retained as an undated original for the specific comparison and scope qualification. Its historical-looking status or conflicting values are not converted into a present operating or commissioning claim.