David Mee

New calibration technique for multiple-component stress wave force balances

Publisher: AIP Publishing

Date: 06-2007

DOI: 10.1063/1.2744235

Abstract: The measurement of forces in hypervelocity expansion tubes is not possible using conventional techniques. The stress wave force balance technique can be applied in expansion tubes to measure forces despite the short test times involved. This article presents a new calibration technique for multiple-component stress wave force balances where an impulse response created using a load distribution is required and no orthogonal surfaces on the model exist. This new technique relies on the tensorial superposition of single-component impulse responses analogous to the vectorial superposition of the calibration loads. The ex le presented here is that of a scale model of the Mars Pathfinder, but the technique is applicable to any geometry and may be useful for cases where orthogonal loads cannot be applied.

Infrared Thermography in Expansion Tubes for Martian Entry Flows

Publisher: American Institute of Aeronautics and Astronautics

Date: 10-03-2020

DOI: 10.2514/6.2020-2415

An experimental study on aerodynamic performance of turbine nozzle guide vanes with trailing-edge span-wise ejection

Publisher: ASME International

Date: 25-03-2013

DOI: 10.1115/1.4006663

Abstract: The present experimental study is to examine the influence of trailing-edge coolant ejection with the span-wise inclination on the aerodynamic loss of turbine nozzle guide vanes. This study uses a cascade of five vanes located in the test section of a low-speed wind tunnel. The vanes have the profile of high-pressure nozzle guide vanes, and the central vane is equipped with the internal cooling and the trailing-edge coolant ejection. The coolant is ejected through trailing-edge slots that are inclined in the span-wise direction at angles varying from 0 deg to 45 deg in 15 deg increments. The results indicate an optimum ejection rate, at which the aerodynamic loss is minimum. There is a little variation in loss as the span-wise inclination is varied when the ratio of coolant to mainstream gas mass flow rate is less than 1.5%. For higher coolant flow rates, however, the loss increases with increases in the span-wise ejection angle.

Boundary Layers on a Flat Plate at Sub- and Superorbital Speeds

Publisher: American Institute of Aeronautics and Astronautics (AIAA)

Date: 10-2007

DOI: 10.2514/1.26894

Numerical modelling of the self-heating process of a wet porous medium

Publisher: Elsevier BV

Date: 12-2011

DOI: 10.1016/J.IJHEATMASSTRANSFER.2011.08.025

Shock Layer Radiation Measurements at a Mars Entry Condition for Infrared Thermography

Publisher: American Institute of Aeronautics and Astronautics

Date: 14-06-2019

DOI: 10.2514/6.2019-3006

Scramjets and shock tunnels—The Queensland experience

Publisher: Elsevier BV

Date: 08-2005

DOI: 10.1016/J.PAEROSCI.2005.08.002

Rarefied, superorbital flows in an expansion tube

Publisher: Emerald

Date: 06-2004

DOI: 10.1108/09615530410532277

Discovery Projects - Grant ID: DP0665016

Start Date: 2006

End Date: 02-2010

Amount: $260,000.00

Funder: Australian Research Council

Discovery Projects - Grant ID: DP230101367

Start Date: 07-2023

End Date: 07-2027

Amount: $445,000.00

Funder: Australian Research Council

Discovery Projects - Grant ID: DP170103191

Start Date: 2017

End Date: 12-2019

Amount: $405,000.00

Funder: Australian Research Council

Discovery Projects - Grant ID: DP0208744

Start Date: 2002

End Date: 12-2005

Amount: $284,000.00

Funder: Australian Research Council

Linkage Infrastructure, Equipment And Facilities - Grant ID: LE130100036

Start Date: 2013

End Date: 04-2014

Amount: $310,000.00

Funder: Australian Research Council

Discovery Projects - Grant ID: DP120101009

Start Date: 2012

End Date: 12-2015

Amount: $320,000.00

Funder: Australian Research Council

Discovery Projects - Grant ID: DP220101478

Start Date: 12-2022

End Date: 12-2025

Amount: $390,000.00

Funder: Australian Research Council

Discovery Projects - Grant ID: DP170101105

Start Date: 2017

End Date: 12-2019

Amount: $393,000.00

Funder: Australian Research Council

Linkage Infrastructure, Equipment And Facilities - Grant ID: LE160100194

Start Date: 2016

End Date: 12-2016

Amount: $250,000.00

Funder: Australian Research Council

Discovery Projects - Grant ID: DP0452374

Start Date: 2004

End Date: 12-2009

Amount: $1,805,000.00

Funder: Australian Research Council