Review of Transonic Wall Interference Corrections and Considerations for Development

Davis, Tyler W.

doi:10.2514/6.2019-3094

Cited by 7 publications

(3 citation statements)

References 24 publications

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“…Furthermore, below a certain threshold of working section area, the tunnel walls will begin to influence the flow around the test model, and can result in non-representative flow distributions which are not directly comparable with the intake operation during flight. A typical wall interference mechanism, commonly encountered in supersonic and transonic facilities, is related to shock wave reflection at the tunnel walls, which can then lead to secondary reflections on the aerodynamic surfaces of the test model [20]. The presence of such reflecting shocks alters the flow distribution around the test model which may yield misleading conclusions.…”

Section: Working Section Design and Model Integrationmentioning

confidence: 99%

Design of a high-speed intake distortion simulator for propulsion integration research

Migliorini

Szymański

Zachos

et al. 2023

AIAA SCITECH 2023 Forum

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High levels of inlet flow distortion can be a critical aspect in supersonic air induction systems due to the complex spatial nature and notable temporal unsteadiness. This can affect the operability and performance of the propulsion system. Simulation of the intake shock system in a relatively less expensive, lower technology readiness level experimental facility can be an important element to mitigate a significant part of the risk that industrial and certification testing carries. The work described in this paper is part of a programme that aims to develop such a distortion simulation test rig where the capability of advanced nonintrusive measurement techniques would be applied in propulsion integration research. The paper describes the concept, preliminary design and sizing of the working section of the rig, the exhaust system design and the integration of the test model. A brief summary of the rig architecture is provided along with details of the high-pressure system that drives the supersonic flow. The work indicates that careful design of the working section is required to ensure sufficient operating range and representative aerodynamics of the test model. It is also shown that the working section wall interference on the test model is tightly linked with the type and size of the aircraft intake to be tested. Ways to mitigate this interference are herein explored. I.Nomenclature ACIntake capture area AH Working section cross-sectional area A0 Area of stream tube entering the inlet Amax Maximum inlet projected area, A* Nozzle throat area Cp Static pressure coefficient H Working section height Ht Intake throat height h Diverter height

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Section: Working Section Design and Model Integrationmentioning

confidence: 99%

Design of a high-speed intake distortion simulator for propulsion integration research

Migliorini

Szymański

Zachos

et al. 2023

AIAA SCITECH 2023 Forum

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“…Advances in instrumentation systems have had some impact, particularly optical measurements of model surface 23 properties such as pressure 24 , temperature and deformation [72], but the mainstays of testing in large industrial transonic facilities remain the traditional internal sting balance [73] for forces and moments, and the electronic multiplexed pressure scanner for surface pressure distributions. Developments in instrumentation, data acquisition systems, and data reduction methods [96] have contributed to the data productivity trends of Fig. 5, but Fig.…”

Section: Industrial Testingmentioning

confidence: 99%

“…In these circumstances bugs are to be expected, and having to reprocess data during and/or after a test is not uncommon. Data corrections for wind tunnel interference effects in ventilated test sections can be problematic for unconventional model configurations and test types, particularly for facilities still relying on older semi-empirical methods [96]. flow physics failure – when an expensive test fails to give the results the customer expects, life can become very difficult for the test engineer.…”

Section: Industrial Testingmentioning

confidence: 99%

Transonic industrial wind tunnel testing in the 2020s

Greenwell¹

2021

Aeronaut. j.

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Wind tunnels remain an essential element in the design and development of flight vehicles. However, graduates in aerospace engineering tend to have had little exposure to the demands of industrial experimental work, particularly at high speed, a situation exacerbated by a lack of up-to-date reference material. In an attempt to fill this gap, this paper presents an overview of the current and near-term status and usage of transonic industrial wind tunnels. The review is aimed at recent entrants to the field, with the aim of helping them make the step from research projects in small university facilities to commercial projects in large industrial facilities. In addition, a picture has emerged from the review that contradicts received wisdom that the wind tunnel is in decline. Globally, the industrial transonic wind tunnel is undergoing somewhat of a renaissance. Numbers are increasing, investment levels are rising, capabilities are being enhanced, and facilities are busy.

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Influence of T-128 wind tunnel perforated walls on aerodynamic characteristics of reentry vehicles at transonic speed

et al. 2019

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Review of Transonic Wall Interference Corrections and Considerations for Development

Cited by 7 publications

References 24 publications

Design of a high-speed intake distortion simulator for propulsion integration research

Design of a high-speed intake distortion simulator for propulsion integration research

Transonic industrial wind tunnel testing in the 2020s

Influence of T-128 wind tunnel perforated walls on aerodynamic characteristics of reentry vehicles at transonic speed

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