Experimental Investigation of a Morphable Biplane

Traub, Lance W.; Nix, Thomas

doi:10.2514/1.c031471

Cited by 7 publications

(6 citation statements)

References 10 publications

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“…An earlier study of non-planarity in the form of a 'X-Wing' (5,6) indicated that anhedral/dihedral angles of approximately 20º were optimal, consistent with this study. An analytic analysis in this study (6) also showed that the span efficiency factor (e i ) for non-planar wings of this form (essentially a similar wing geometry as in the current study with zero stagger) was only dependent on the lift curve slope augmentation.…”

Section: Aerodynamic Characterisationsupporting

confidence: 87%

“…The selected geometry is analogous to a staggered variant of that in Ref. 5. The design of the fuselage was dictated primarily by the need to accommodate the sting balance in conjunction with a reliable method to attach the wings at precise anhedral/dihedral angles.…”

Section: Equipment and Proceduresmentioning

confidence: 99%

“…An obvious example of such is morphing technology. Morphing may take many forms, ranging from variable camber (2) , variable twist (3) , sweep (1) , span (1,4) to variable non-planarity (5)(6)(7) . The fundamental goal of morphing is to augment aircraft performance and efficiency.…”

Section: Introductionmentioning

confidence: 99%

“…The largest issue with multi-wing or non-planar configurations (were the projected wing span is fixed) is typically that of increased wetted area. A resultant increase in the minimum drag coefficient often makes multi-wing or annular wing configurations uncompetitive (5,6,11) for most regimes except for those where flight at high sustained loads is required.…”

Section: Introductionmentioning

confidence: 99%

“…end plates or winglets), where the strength of the trailing vortex sheet is greatest (following from the variation of the spanwise loading). Prior examination (5)(6)(7) of non-staggered biplanes in an 'X' geometry has shown significant aerodynamic benefit for both moderate aspect ratio unswept wings as well as delta wings, with anhedral/dihedral angles of approximately 20º proving optimal (both experimentally and theoretically). Considered individually, a '∨' wing shows attenuated lifting performance and efficiency compared to an equivalent arc length planar wing (15) , due to a reduced quantity of fluid that is captured to generate the lift impulse.…”

Section: Introductionmentioning

confidence: 99%

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Characterisation of a highly staggered spanwise cambered biplane

Traub¹,

Waghela

Bordignon

2015

Aeronaut.j.

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An investigation is presented to elucidate the performance of a staggered, spanwise cambered biplane. The spanwise camber yielded wings forming a '∧' or '∨' when viewed streamwise. The configuration is examined in terms of its aerodynamic and stability characteristics. The feasibility of negating the requirement for a conventional empennage is explored. Geometric variation encompassed front and back wing anhedral/dihedral angles yielding 49 combinations. Evaluation of the geometry was accomplished using both wind tunnel testing and numerical simulation. The results indicated that front wing dihedral in conjunction with aft wing anhedral was most beneficial, such that the benefit of wake spacing was maximised. Aerodynamic benefit was indicated compared to a conventional empennage geometry. The greatest disparity in behaviour of the fore and aft wing anhedral/dihedral distribution was in the high lift regime, where the nature of the stall varied. Simulations to establish the viability of the geometry in terms of controllability were also conducted and indicated that the configuration is viable.

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Section: Aerodynamic Characterisationsupporting

confidence: 87%

Section: Equipment and Proceduresmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Characterisation of a highly staggered spanwise cambered biplane

Traub¹,

Waghela

Bordignon

2015

Aeronaut.j.

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Effects of propeller thrust trimming on tailless unmanned aerial vehicle performance

Wang

Song

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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Flight performance and longitudinal static stability are two contradictory requirements for aircraft. This is especially true for a tailless configuration, whose flight performance is traded for static stability. A new tailless gull wing configuration with propeller thrust trimming is proposed in this paper. It is expected that the propeller thrust can help to provide a nose-up pitching moment and improve the flight performance. In the present configuration, a cambered airfoil is used to increase the lift-to-drag ratio as well as the maximum lift coefficient. Two approaches are adopted to obtain the nose-up pitching moment. Firstly, the thrust line is shifted below the center of gravity to make a positive contribution to the pitching moment. Secondly, the thrust vectoring is employed to trim longitudinally instead of elevon deflection. The wind-tunnel data indicate that the lift-to-drag ratio and maximum lift coefficient increase notably with the help of propeller thrust trimming. To determine the performance benefits of the gull wing with propeller thrust trimming, a conceptual design environment of the electric-powered unmanned aerial vehicle is developed by integrating the modules of the conceptual parameters, aerodynamics, stability, propulsion, weight, performance, as well as optimization. The optimization results suggest that, compared with the two other conventional tailless configurations, the gull wing with propeller thrust trimming results in 20 and 34% endurance increase. Flight tests of a 2.5 kg built aircraft demonstrate the aerodynamic feasibility of the gull wing with propeller thrust trimming concept.

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Improving Performance of Flying Wing Mini-UAV with Propeller Thrust Involved Trimming the Pitching Moment

Wang

2013

2013 Aviation Technology, Integration, and Operations Conference

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Experimental Investigation of a Morphable Biplane

Cited by 7 publications

References 10 publications

Characterisation of a highly staggered spanwise cambered biplane

Characterisation of a highly staggered spanwise cambered biplane

Effects of propeller thrust trimming on tailless unmanned aerial vehicle performance

Improving Performance of Flying Wing Mini-UAV with Propeller Thrust Involved Trimming the Pitching Moment

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