The Design and Construction of a Blended Wing Body UAV

Thompson, Daniel; Feys, Joshuo; Filewich, Michael; Abdel-Magid, Sharif; Dalli, Dennis; Goto, Fumitaka

doi:10.2514/6.2011-841

Cited by 14 publications

(11 citation statements)

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“…Therefore, a high lift co-efficient (CL) airfoil was required in the center. It was realized that with high CL (high camber) comes a relatively more negative moment of coefficient (CM) [4] thus the outer wing must have a positive CM in order to balance out its effects. CM contributes significantly to the longitudinal stability of tail less aircrafts since they do not have a tail to counter the negative pitching moment (nose down) of the cambered airfoils [11].…”

Section: Air-foil Selectionmentioning

confidence: 99%

“…BWB is very unstable in pitch because of lack of tail section. Setting the center of gravity (CG) ahead of the neutral point of the aircraft is essential for the plane to be statically and dynamically stable [4,14]. This will ensure that the aircraft recovers from any disturbance.…”

Section: Center Of Gravitymentioning

confidence: 99%

“…It does not have a tail that significantly contributes to drag generation [2]. Majority of lift is created by center body [2] thus eliminating the aerodynamically redundant fuselage from the conventional configuration [3,4].…”

Section: Introductionmentioning

confidence: 99%

“…This showed that stability issues can be solved by design thus proving a BWB superior in all aspects. Thomson et al [4] made a 5-meter wingspan BWB unmanned air vehicle (UAV). Stability was improved by moving center of gravity in front of the center of pressure and by using reflex airfoils to reduce aerodynamic moments [4].…”

Section: Introductionmentioning

confidence: 99%

“…Thomson et al [4] made a 5-meter wingspan BWB unmanned air vehicle (UAV). Stability was improved by moving center of gravity in front of the center of pressure and by using reflex airfoils to reduce aerodynamic moments [4]. Dehpanah and Nejat [8] placed an external mass that could move along the centerline to provide stability in pitch.…”

Section: Introductionmentioning

confidence: 99%

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A New Methodology for Aerodynamic Design and Analysis of a Small Scale Blended Wing Body

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Ta²,

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et al. 2018

J Aeronaut Aerospace Eng

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The blended wing body (BWB) concept is a relatively new concept of an aircraft. The wings and the fuselage blend into one integral structure greatly reduce drag and increases lift thus making it a highly efficient design. The aim of the research was to design a radio controlled small scale BWB aircraft for use over long ranges at low altitudes in order to deliver payloads. The BWB was divided into the center body and the outer wing. Four airfoils, HS522, LA2573A, NACA 25111 and MH78 were analyzed in XFLR5. In consideration of their lift and moment characteristics, NACA 25111 and MH78 were selected for the center body and the wing respectively. The stall speed and wing loading were the primary factors used in determining the area and size of the aircraft which converged to a design having a five feet wingspan. Center of gravity was placed ahead of aerodynamic center to provide static and dynamic stability in pitch. Twist, dihedral and sweep were given to increase stability and controllability. The final design was tested in XFLR5 for stability and in commercial computational fluid dynamic code ANSYS-Fluent for comparison. These simulation results were compared to wind tunnel tests of a 20% scaled down prototype. 3D Panel Method results in XFLR5 were found to be very close to wind tunnel results but CFD results were seen to be not conforming to the wind tunnel results after 10° angle of attack. Thus, CFD was deemed to be unnecessary for designing a plane of this size. Ultimately, a larger test prototype was made out of polystyrene foam and a successful flight was achieved.

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Section: Air-foil Selectionmentioning

confidence: 99%

Section: Center Of Gravitymentioning

confidence: 99%