Research on analytical scaling method and scale effects for subscale flight test of blended wing body civil aircraft

Wang, Gang; Zhou, Minghui; Tao, Yujin; Li, Jie; Li, Dong; Zhang, Yizhe; Chang-sheng, Yuan; Sang, Weimin; Zhang, Binqian

doi:10.1016/j.ast.2020.106114

Cited by 15 publications

(10 citation statements)

References 12 publications

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“…For this test, atmospheric conditions were measured at wind tunnel location (ρ = 1.20978 kg/m 3 , µ = 1.7853 × 10 −5 Pa s, T = 14.8 °C and p = 99 kPa). Stainless steel was used to manufacture the scale model [24] of the designed BWB configuration in portion with 1: 1.8, and the test velocity was fixed at 68 m/s, which corresponds to a Reynolds number equal to 2.0 × 10 6 .…”

Section: Dep Induced Effects Evaluationmentioning

confidence: 99%

Aerodynamic Design, Analysis and Validation of a Small Blended-Wing-Body Unmanned Aerial Vehicle

Wang

Zhou

2022

Aerospace

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This paper describes the aerodynamic design and assessment of a blended-wing–body (BWB) configuration under the distributed electric propulsion (DEP) installation constraints. The aerodynamic design rationale and process is described, as well as how the DEP system is considered and simplified in the optimization design process. Both the BWB configuration and the DEP induced effects are numerically simulated and analyzed using the Reynolds Averaged Navier–Stokes (RANS) computational fluid dynamics (CFD) flow solvers. To further demonstrate the feasibility and reliability of the design approach, the wind tunnel tests of a scaled model of the designed BWB configuration are carried out, and both the aerodynamic characteristics and the BWB surface flow are measured and analyzed. The results indicate the reliability and feasibility of the optimization design method introduced in this paper.

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Section: Dep Induced Effects Evaluationmentioning

confidence: 99%

Aerodynamic Design, Analysis and Validation of a Small Blended-Wing-Body Unmanned Aerial Vehicle

Wang

Zhou

2022

Aerospace

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“…Nevertheless, it is feasible to study some relevant dynamic and aeroelastic problems at low speeds -such as loss of control and body-freedom flutter -that are otherwise costly or impractical to reproduce by other means or tools. Applying SFT to a wider range of aerodynamic and dynamic problems requires a careful study and management of the effects of incomplete similarity [174,175,176]. In this case, a good knowledge of the issue of interest is required beforehand, a paradox illustrated in Figure 7.1.…”

Section: Discussionmentioning

confidence: 99%

“…While this topic has been widely discussed in the wind-tunnel literature, little open information is available for free-flight models. Recent publications [174,175,176,177] show the current interest and ongoing efforts to identify and quantify these effects using both theoretical and practical approaches.…”

Section: Future Workmentioning

confidence: 99%

On subscale flight testing : Cost-effective techniques for research and development

Rueda

2021

Linköping Studies in Science and Technology. Dissertations

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“…The study of electromagnetic scattering characteristics is an important part of aircraft design, radar technology and antenna engineering applications. The drag plate increases the windward area of the aircraft and destroys the streamline of the aircraft (Canelas and Roche, 2021; Liang, 2018; Wang et al ., 2019a, b), thus the influence on the electromagnetic scattering characteristics of the aircraft has also received attention.…”

Section: Introductionmentioning

confidence: 99%

Quantitative calculation of electromagnetic scattering characteristics from drag plate of aircraft afterbody

Zhou,

Huang

2023

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PurposeThis paper aims to discuss the electromagnetic scattering characteristics of the afterbody model with two drag plates.Design/methodology/approachThe plane shape of the drag plate model is designed as a rectangle. High-precision unstructured grid technology is used to treat the target surface. A calculation method based on multiple tracking and dynamic scattering module is presented to calculate the radar cross section (RCS).FindingsThe results show that under the given observation conditions, the RCS and surface scattering characteristics of a single drag plate change with the increase of the opening angle, which makes the forward RCS of the afterbody model change more than 8.43 dBm2. The opening of two resistance plates at different fixed angles has little effect on the peak value and position of the RCS of the afterbody model. The dynamic deflection of the two drag plates can bring 16.78 dBm2 fluctuations to the forward RCS of the afterbody model, and more than 25.59 dBm2 fluctuations to the side RCS.Practical implicationsThe installation positions of the drag plate on the aircraft are various, so the method in this paper can provide reference and support for RCS analysis of the speed brake at other positions.Originality/valueThe presented calculation method is of engineering value to analyze the electromagnetic scattering characteristics of the drag plate.

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Research on analytical scaling method and scale effects for subscale flight test of blended wing body civil aircraft

Cited by 15 publications

References 12 publications

Aerodynamic Design, Analysis and Validation of a Small Blended-Wing-Body Unmanned Aerial Vehicle

Aerodynamic Design, Analysis and Validation of a Small Blended-Wing-Body Unmanned Aerial Vehicle

On subscale flight testing : Cost-effective techniques for research and development

Quantitative calculation of electromagnetic scattering characteristics from drag plate of aircraft afterbody

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