Wake Measurements on Blended Wing Body with Gurney Flaps in Low Speed Flows

Yamada, Tatsuya; Taguchi, Masato; Duong, Nguyen Thanh; Kashitani, Masashi; Kusunose, Kazuhiro; Takita, Yoshihiro

doi:10.2514/6.2019-1617

Cited by 5 publications

(3 citation statements)

References 4 publications

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“…Such a pattern was also seen in a previous study. 17) Figure 6(b), at ¼ 4 , shows no significant qualitative difference from Fig. 6(a), but the area of total pressure loss at the upper wing element is slightly larger than that in Fig.…”

Section: Wake Analysismentioning

confidence: 67%

“…In low-speed wind tunnel testing, a wake measurement technique based on the conservation of momentum was proposed (the technique is called the wake integration method 16) ), and it has been used for the aerodynamic design of aircraft. [17][18][19] The technique is capable of determining the lift and drag, and also decomposing the drag to components (the profile drag and the induced drag). In addition, this technique can calculate distributions of the local lift coefficient and the local drag coefficient along the spanwise direction of the model.…”

Section: Introductionmentioning

confidence: 99%

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Aerodynamic Characteristics of Busemann Biplane by Wake Measurements in Low-Speed Wind Tunnel

Kashitani

Duong

Kusunose

et al. 2021

Trans. Japan Soc. Aero. S Sci.

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In this study, the basic aerodynamic characteristics of a Busemann biplane model in a low-speed wind tunnel were clarified by the wake survey technique. A low-speed wind tunnel of the blowdown type was used, and it had an exit nozzle size is in 1.5 m © 1.5 m. A wake measurement system and six-component balance system were installed in the test section. A five-hole probe was used in the wake measurement system to measure the velocity distribution. The Busemann biplane model was designed to cruise at Mach 1.7. The total length of the model was 742 mm, and the width was 556 mm. The shape of the fuselage was 76 mm square on a side, and the nose had a double-conical shape. The flow velocity was 20 m/s, and the Reynolds number derived from the mean chord length was 1.4 © 10 5 . The results of the study are summarized as follows. Based on the visualization of the wake flow, vortices were generated from the tips of the upper and lower wing elements of the biplane at an attack angle of ¡ = 0°, but the vortices had an opposing rotation direction. Analysis of the wake data showed that locally induced drag was not generated at the wing tip. At ¡ = 6°and 8°, the profile drag increased, probably due to the influence of the flow separation from the upper surface of the upper wing element. However, the total lift coefficient increased with an increasing angle of attack, even at ¡ > 8°. Therefore, it can be concluded that the biplane lift is mainly generated by the lower wing elements.

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Section: Wake Analysismentioning

confidence: 67%

Section: Introductionmentioning

confidence: 99%

Aerodynamic Characteristics of Busemann Biplane by Wake Measurements in Low-Speed Wind Tunnel

Kashitani

Duong

Kusunose

et al. 2021

Trans. Japan Soc. Aero. S Sci.

Self Cite

View full text Add to dashboard Cite

show abstract

“…Studies on the design optimizations of BWB were also reported by Panagiotou et al (2018) and Brown and Vos (2018). Experimental analysis conducted by Yamada et al (2019) in a low-speed tunnel at a free stream velocity of 18m/s indicated that the use of gurney flaps on the BWB configurations generated a pair of counter-rotating vortices and also improved the lift locally. Several BWBs under the prototyping stage are reported by Thompson et al (2011), Becker and Sheffler (2016), Rodzewicz et al (2018), Footohi et al (2019), Naeini et al (2019Naeini et al ( , 2021) and many others.…”

Section: Introductionmentioning

confidence: 95%

Flow Field Investigation of a Blended Wing Body in Low Speeds

2023

JAFM

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With the advancement in the modern transport system, it has become imperative to achieve larger aircraft volume at minimum cost wherein aerodynamics plays a major role. The present work aims to investigate the flow over a typical blended wing body (BWB) configuration at different angles of attack adopting experimental and computational techniques. Experiments consisted of the force measurements and oil flow visualizations at a free stream velocity of around 19 m/s. Computations were made using the commercially available software ANSYS 18.1. Results indicated that the use of a Blended Wing Body Configuration resulted in improved aerodynamic characteristics in comparison to other wing configurations such as Delta/ Double delta wings. Surface flow visualization carried out over the BWB configuration indicated the reason behind increased lift coefficients. Reasonable agreement of experiments and computations was observed.

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Recent developments of blended wing body aircraft: experimental, numerical and theoretical approaches

Handa

Srinivas

2022

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Wake Measurements on Blended Wing Body with Gurney Flaps in Low Speed Flows

Cited by 5 publications

References 4 publications

Aerodynamic Characteristics of Busemann Biplane by Wake Measurements in Low-Speed Wind Tunnel

Aerodynamic Characteristics of Busemann Biplane by Wake Measurements in Low-Speed Wind Tunnel

Flow Field Investigation of a Blended Wing Body in Low Speeds

Recent developments of blended wing body aircraft: experimental, numerical and theoretical approaches

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