Use of Wall Suction In Half Model Wind Tunnel Testing

Mailk, Abdullah; Render, P. M.

doi:10.2514/6.2010-4828

Cited by 3 publications

(1 citation statement)

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“…Eliasson (2008) suggests that changing the peniche height only redistributes the strength of the flow displacement and cannot be avoided, but that the shape of the peniche may alleviate this. Other studies have tried to reduce the flow displacement, and resulting vortical structures, through leading edge suction, thereby reducing mass flow and velocity gradients (Malik and Render 2010). There is a little evidence to suggest, however, that suction ahead of the peniche can produce a significant improvement in the aerodynamic characteristics of semi-span models.…”

mentioning

confidence: 99%

Semi-span wind tunnel testing without conventional peniche

Skinner

Zare‐Behtash

2017

Exp Fluids

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mentioning

confidence: 99%

Semi-span wind tunnel testing without conventional peniche

Skinner

Zare‐Behtash

2017

Exp Fluids

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Investigation of Aerodynamic Support Interference for Testing a Semispan T Tail Aircraft Model

Mamou

Broughton

2023

Journal of Aircraft

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High-fidelity computational fluid dynamics (CFD) flow simulations were carried out to assess the sources of aerodynamic support interference of an aircraft half-model with a T-tail empennage mounted in a wind tunnel in an attempt to improve how well a semispan model can represent the corresponding full-span aircraft. The Bombardier research aircraft configuration (BRAC) model was used, which consists of a fuselage, a fuselage to wing fairing, a cruise wing with flap fairings, an engine nacelle and pylon, a vertical tail, and a horizontal stabilizer (HSTAB). The standard half-model support used at the National Research Council of Canada’s 1.5 m trisonic wind tunnel consists of a wall-mounted splitter plate to remove a sizable portion of the upstream tunnel wall boundary layer and a two-dimensional peniche sandwiched between the model symmetry plane and the splitter plate. CFD simulations of the BRAC model mounted in the wind tunnel were performed using the Menter shear stress transport turbulence model at a Mach number of 0.2. The CFD results for the standard (baseline) mounting arrangement compared favorably well with the half-model experimental data. The BRAC CFD model was then modified to provide reference “full-span” data and to examine several alternate model mounting arrangements. All simulations were compared with the ideal full-span reference simulations. Significant disturbances were found to be induced by the reflection plane boundary layer and primary horseshoe vortex on the flowfield surrounding the HSTAB, which had a direct impact on the measured overall model forces and moments.

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