The aerodynamics performance of Blended Wing Body Baseline-II E2

Ali, Zaileha Md; Kuntjoro, Wahyu; Wisnoe, Wirachman; Nasir, Rizal Effendy Mohd; Mohamad, Firdaus; Reduan, Nor Fazira

doi:10.1109/iccsn.2011.6014899

Cited by 6 publications

(1 citation statement)

References 5 publications

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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]. Recently, wind tunnel experiment has been done in Baseline-V at Mach number 0.05.…”

Section: Introductionmentioning

confidence: 99%

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

et al. 2019

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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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Section: Introductionmentioning

confidence: 99%

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

et al. 2019

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Effect of canard to the aerodynamic characteristics of Blended Wing Body airplane

Ali

Kuntjoro

Wisnoe

2012

2012 IEEE Symposium on Business, Engineering and Industrial Applications

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This paper describes a series of ongoing wind tunnel experiments of Blended Wing Body equipped with canard as longitudinal control surface. The canard has a rectangular shape with fixed aspect ratio and planform area. All tests were conducted in the subsonic wind tunnel at the Universiti Teknologi MARA, at Mach number of 0.1. Angles of attack, α were varied from -16 to 50 . The lift curve slope, C Lα shows that the lift coefficient does not change much with different canard setting angles. As expected, the lift coefficient increases with increasing angles of attack at any canard setting angle. In general, the moment coefficient increases as the canard setting angle is increased. The visualization using mini tufts were performed to observe airflow at the upper surface of the canard.

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Numerical Simulation of the Flow Around a Light Aircraft Wing

Musa

Abdulla

Elsayed

2012

The International Conference on Applied Mechanics and Mechanica

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This work aims to study and simulate the behavior of flow over SAFAT-01's wing using numerical simulation based on solving Reynolds's Averaged Navier-Stokes equations coupled with K-ω turbulent model. The wing model is simple rectangular with elliptical ends. In the present work, aerodynamics characteristics and different flow phenomena were predicted at different design conditions (e.g. at different angles of attack) and at Re=5.2×10 6 . The present study analysis the vortices which occur over wing and captured their effective regions at critical design conditions. This study indicates that the maximum lift coefficient for SAFAT-01's wing is 1.44 occurred at stall angle of attack 12 o , maximum lift to drag ratio (L/D) is 26 which occurs at -4 o , and the zero lift drag coefficient is 0.0142. To validate this numerical simulation, a typical wing which found in Ref. [3] was analyzed, a comparison between predicted results and available results indicate that this numerical simulation has high ability for predicting the aerodynamics characteristics.

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The aerodynamics performance of Blended Wing Body Baseline-II E2

Cited by 6 publications

References 5 publications

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

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

Effect of canard to the aerodynamic characteristics of Blended Wing Body airplane

Numerical Simulation of the Flow Around a Light Aircraft Wing

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