Flight Performance of Various Blended Wing-Body Small Uav Designs

Nasir, Rizal Effendy Mohd; Mohamed, Firdaus; Ramly, Ramzyzan; Mamat, Aman Mohd Ihsan; Wisnoe, Wirachman; Kuntjoro, Wahyu

doi:10.11113/jt.v75.5214

Cited by 3 publications

(3 citation statements)

References 5 publications

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“…[11] Of particular interest in this study is Baseline-VII design that is developed by FTTC based on the cranked-wing flying-wing configuration. This BWB UAV design is estimated to have maximum lift-todrag ratio of 2.19 when cruise flying (i.e., at angle of attack of roughly 0°) [12]. However, it is strongly believed that its aerodynamic performance can be further improved by optimizing its planform shape design.…”

Section: Introductionmentioning

confidence: 99%

Optimization of a Blended-Wing-Body Unmanned Aerial Vehicle Design for Maximum Aerodynamic Lift-to-Drag Ratio

Romli

Sabri²,

Nasir³

2023

CFDL

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Although unmanned aerial vehicle (UAV) has found many applications in various fields, its operation has been constrained by its low flight endurance. To date, several design efforts are pursued to improve this performance and one of them is the exploration of blended-wing-body (BWB) design. In this study, parametric study is conducted on the BWB UAV design of Baseline-VII that is developed by Flight Technology and Test Center (FTTC), Universiti Teknologi MARA Shah Alam, Malaysia. The primary goal is to optimize the current Baseline-VII design for maximum lift-to-drag ratio, which in turn implies a higher flight endurance. Three design parameters are considered: inboard wing sweep angle, outboard wing sweep angle and also inboard wing span. A full-factorial design of experiments (DoE) is applied to set the total 27 design case settings for this study, with three different values considered for each design parameter: 10°, 25° and 50° for inboard and outboard wing sweep angles, and 200 mm, 300 mm and 400 mm for the inboard wing span. The computer-aided design (CAD) models for the design cases are constructed using Solidworks and the resultant aerodynamic lift-to-drag ratio is found through computational fluid dynamics (CFD) simulation analysis using ANSYS Fluent. The collected data is then statistically analysed using regression analysis in MINITAB to construct a representative regression model that aptly capture the effects of the varied design parameters on the design aerodynamic lift-to-drag ratio. Based on the results, it has been found that the maximum lift-to-drag ratio for the modified Baseline-VII UAV design is 2.8119, which is obtained with optimal settings of inboard wing sweep angle = 17.2727°, outboard wing sweep angle = 20.9091° and inboard wing span = 400 mm. This is about 28.4% increment of lift-to-drag ratio from the original Baseline-VII design.

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Section: Introductionmentioning

confidence: 99%

Optimization of a Blended-Wing-Body Unmanned Aerial Vehicle Design for Maximum Aerodynamic Lift-to-Drag Ratio

Romli

Sabri²,

Nasir³

2023

CFDL

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“…Since September 2005, UiTM has started a research on BWB-UAV [9]. There were several studies that had been carried out on BWB using CFD, wind tunnel, and finite element method [10].…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Analysis of Blended Wing Body - Unmanned Aerial Vehicle (BWB-UAV) Equipped with Horizontal Stabilizers

et al. 2019

Self Cite

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This paper presents an aerodynamic characteristic study in longitudinal direction of UiTM Blended Wing Body-Unmanned Aerial Vehicle Prototype (BWB-UAV Prototype) equipped with horizontal stabilizers. Flight tests have been conducted and as the result, BWB experienced overturning condition at certain angle of attack. Horizontal stabilizer was added at different location and size to overcome the issue during the flight test. Therefore, Computational Fluid Dynamics (CFD) analysis is performed at different configuration of horizontal stabilizer using Spalart - Allmaras as a turbulence model. CFD simulation of the aircraft is conducted at Mach number 0.06 or v = 20 m/s at various angle of attack, α. The data of lift coefficient (CL), drag coefficient (CD), and pitching moment coefficient (CM) is obtained from the simulations. The data is represented in curves against angle of attack to measure the performance of BWB prototype with horizontal stabilizer. From the simulation, configuration with far distance and large horizontal stabilizer gives steeper negative pitching moment slope indicating better static stability of the aircraft.

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“…Blended Wing-Body (BWB) aircraft has the potential to be more efficient than current conventional configuration [1]. Various designs of small BWB UAVs have been studied in past 13 years in Universiti Teknologi Mara and found that not all BWB designs are efficient because aerodynamic efficiency depends on many factors [2]. However, compared to the conventional aircraft with separated fuselage and wing, a Blended Wing-Body aircraft design has proven to be able to generate more lift, less parasitic drag, and improve fuel efficiency to more than 20%.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamics of a Blended Wing Body Aircraft with Close-Coupled Tail: Computational Fluid Dynamics Simulations of Two Different Tail Sweep Angle Cases

Azan Haiqal Mohamed Shafari,

Effendy Mohd Nasir,

Zulfazli Arief Abd Latif

et al. 2018

IJET

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This paper presents the aerodynamic performance of Baseline V blended wing-body aircraft via Computational Fluid Dynamic (CFD) simulation. Baseline V has a set of close-coupled tail plane that can change its incidence and tilt angle for pitch and yaw control. Based on previous research, Baseline V has insufficient longitudinal stability in term of pitch moment at zero angle of attack which is negative value at zero tail incidence angles. When tail incidence is set at âˆ’10Â°, the moment coefficient at zero angle of attack is zero thus not sufficient for trim flight with stable pitch moment slope. This leads to the idea of sweeping the tail of the aircraft to increase moment arm. In this paper, two cases are considered which is 0Â° (case I) and 30Â° (case II) tail sweep angle in which both cases have tail incidence at âˆ’10Â°. NUMECA suit is used as computational tool for this simulation. The simulated environment consists of half-model Baseline V BWB in domain 20 times the length of the aircraft with body centre plane acts as a mirror. The angle of attack used for this simulation is between -10Â° to +17Â° while airspeed is fixed at 15m/s or Mach 0.05. Due to aircraftâ€™s small mean chord and low airspeed flight, its Reynold number is low at 1.0 x 105 even at its body chord. Therefore, Laminar Navier-Stoke Equation is used for the computational simulation. Lift, drag and pitch moment coefficients with respect to angle of attack for both tail cases are computed from the simulation. The results from the CFD simulation is then compared with wind tunnel experiment results measured at AEROLAB, Universiti Teknologi Malaysia. The result shows that the trends of lift, drag and moment coefficients against angle of attack obtained from CFD simulations are similar to plots obtained from wind tunnel experiment for both tail sweep angle cases. It is found that tail sweep angle case of 30Â° has slightly less lift but higher drag coefficients compared with 30Â° tail sweep angle case while its pitch moment coefficient at zero angle of attack has now improved to allow positive trim angle of attack. However, the former has much lower maximum lift-to-drag ratio than the latter.Â Â

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Flight Performance of Various Blended Wing-Body Small Uav Designs

Cited by 3 publications

References 5 publications

Optimization of a Blended-Wing-Body Unmanned Aerial Vehicle Design for Maximum Aerodynamic Lift-to-Drag Ratio

Optimization of a Blended-Wing-Body Unmanned Aerial Vehicle Design for Maximum Aerodynamic Lift-to-Drag Ratio

Aerodynamic Analysis of Blended Wing Body - Unmanned Aerial Vehicle (BWB-UAV) Equipped with Horizontal Stabilizers

Aerodynamics of a Blended Wing Body Aircraft with Close-Coupled Tail: Computational Fluid Dynamics Simulations of Two Different Tail Sweep Angle Cases

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