Use of a Ring Wing Model to investigate Factors affecting Transition Measurement using Temperature Sensitive Paint and Hot Films in Transonic Flow

Ciarella, Andrea; Lawson, Sally N.

doi:10.2514/6.2017-1217

Cited by 3 publications

(1 citation statement)

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“…The particle image velocimetry (PIV) [39] technique was then used to give the velocity field information over the suction surface at the center section. Afterwards, transition locations were measured on the suction surface by the temperature sensitive paint (TSP) technique [12] [40]. Only the middle one third of the wing was painted by TSP.…”

Section: Experimental Measurementsmentioning

confidence: 99%

Shock Control of a Low-Sweep Transonic Laminar Flow Wing

Zhu

Qin

et al. 2019

AIAA Journal

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This paper presents a combined experimental and computational study of a low-sweep transonic natural laminar flow (NLF) wing with shock control bumps (SCBs). A transonic NLF wing with a relatively low sweep angle of 20° was chosen for this study. To avoid the complexity of the flow introduced by perforated/slotted walls commonly used for transonic wind tunnel tests for reducing the wall interference, both experimental tests and computational simulations were conducted with solid wind tunnel wall conditions. This allows for like-to-like validation of the computational simulation.Optimization of the shock control bumps was first conducted to design the wind tunnel test model with bumps. Two critical parameters of the three-dimensional SCBs for shock control, i.e. bump crest * Professor of Aerodynamics, AIAA Associate Fellow, Corresponding Author.

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Section: Experimental Measurementsmentioning

confidence: 99%