Experimental result analysis for scaled model of UiTM tailless blended wing-body (BWB) Baseline 7 unmanned aerial vehicle (UAV)

Nasir, Rizal Effendy Mohd; Ahmad, Aiman M.; Latif, Z. A.A.; Saad, Rosfadzimi Mat; Kuntjoro, Wahyu

doi:10.1088/1757-899x/270/1/012005

Cited by 2 publications

(4 citation statements)

References 4 publications

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“…The analysis is done in the same method from previous research and has seen an improvement of aerodynamic characteristic. The liftto-drag ratio improves from 15.9 to 22.0 as a result of wing sweep reduction from 45 0 to 40 0 [7] while retaining cranked-wing planform shape. The maximum lift-to-drag ratio occurs at 5 0 angle of attack based on the experiment plot but the regression analysis based on equations presented in this paper only yields a maximum lift-to-drag ratio of 10 at 3 0 angle of attack.…”

Section: Discussionmentioning

confidence: 99%

“…Baseline 7 BWB design is initially introduced to study the behaviour of the control surface, given 4 elevons without vertical stabilizer and no wingtip [7]. The challenge for this BWB design is that the aircraft should fly with improved stability solely depending on airfoil selection and four control surfaces to stabilize the aircraft thoroughly [8][9][10][11][12].…”

Section: Introductionmentioning

confidence: 99%

“…The challenge for this BWB design is that the aircraft should fly with improved stability solely depending on airfoil selection and four control surfaces to stabilize the aircraft thoroughly [8][9][10][11][12]. The tail-less design should simplify the mechanism while improving the design characteristics of the Baseline 7 [7]. The objective of this paper is to obtain aerodynamic characteristic of the cranked planform blended wing-body aircraft with 40 0 sweep angle through an experimental analysis conducted at UTM-LST Aerolab, Skudai, Johor.…”

Section: Introductionmentioning

confidence: 99%

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Aerodynamic characteristics of a cranked planform blended wing-body aircraft with 400 sweep angle

Ahmad¹,

Nasir

Latif³

et al. 2018

IJET

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Baseline 7 Blended Wing-Body design is introduced to study the behaviour of the control surfaces, given four elevons without vertical stabilizer and wingtip. The objective of the paper is to obtain an aerodynamic characteristic of a cranked planform blended wing-body aircraft. The airfoil used for the entire body is NACA 2412, which is selected for ease of fabrication process. The wingspan of the model is 1.4 m with 0.2 m thickness. The sweep angle of the model is fixed to 400. The wingspan area is calculated at 0.405 m2. The experiment is conducted at UTM-LST Wind Tunnel, AEROLAB, Skudai, Johor with test wind speed of 15 m/s. The maximum lift-to-drag ratio for the model is found to be around 21.9, which is better than many conventional aircraft. Nonetheless, the parabolic regression made to the drag versus lift plot only yields maximum lift-to-drag ratio of 10.0. The value of drag coefficient at zero lift is 0.012 while the maximum lift coefficient found is at 0.65 at 150 angle of attack. The lift-to-drag ratio improves 38.3% from 15.9 in the previously-published design. The neutral point is found to be located at 30.6% of the mean geometric chord in front of the wind tunnel model reference center or about 0.398 m from the nose of the 0.63 m long aircraft model or at 63.1% of aircraft length from the nose.

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Section: Discussionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Aerodynamic characteristics of a cranked planform blended wing-body aircraft with 400 sweep angle

Ahmad¹,

Nasir

Latif³

et al. 2018

IJET

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“…It was commonly understood that most BWB aircrafts are of tailless configuration thus their flight stability may not be sufficient to ensure safe flight. Wind tunnel experiments had been executed on a model of BWB aircraft with four elevons that could be deflected at different angles independently or in unison (Nasir et. al, 2017).…”

Section: Literature Reviewmentioning

confidence: 99%

Blended Wing-Body Unmanned Aerial Transport Aircraft: A conceptual design

Nasir

Mohamad

Noh

2022

E-BPJ

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UAVs have advantages for tasks like aerial surveillance, agriculture, and transportation because of their low operating costs and the ability to automate the work. This paper introduces a conceptual design of a parcel transport UAV called Baseline-X BWB that carries two kilogrammes of payload for inter-city transport. The scope of discussion is limited to aerodynamic estimation, flight performance, and monetary cost. This UAV prototype has a longer battery charge range, a larger and heavier payload capacity, and a lower operating cost-per-mile and fleet cost per route than conventional designs of the same size, making it feasible and profitable for operators. Keywords: Air Transport; Blended Wing-Body; Unmanned Aerial Vehicle eISSN: 2398-4287© 2022. The Authors. Published for AMER ABRA cE-Bs by e-International Publishing House, Ltd., UK. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/). Peer–review under responsibility of AMER (Association of Malaysian Environment-Behaviour Researchers), ABRA (Association of Behavioural Researchers on Asians/Africans/Arabians) and cE-Bs (Centre for Environment-Behaviour Studies), Faculty of Architecture, Planning & Surveying, Universiti Teknologi MARA, Malaysia. DOI: https://doi.org/10.21834/ebpj.v7iSI9.4313

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Experimental result analysis for scaled model of UiTM tailless blended wing-body (BWB) Baseline 7 unmanned aerial vehicle (UAV)

Cited by 2 publications

References 4 publications

Aerodynamic characteristics of a cranked planform blended wing-body aircraft with 400 sweep angle

Aerodynamic characteristics of a cranked planform blended wing-body aircraft with 400 sweep angle

Blended Wing-Body Unmanned Aerial Transport Aircraft: A conceptual design

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