Flight Testing of FlexFloil<sup>TM</sup> Adaptive Compliant Trailing Edge

Kota, Sridhar; Flick, Peter; Collier, F. S.

doi:10.2514/6.2016-0036

Cited by 56 publications

(40 citation statements)

References 4 publications

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“…The ACTE flight research project was a joint effort between NASA, the U.S. Air Force Research Laboratory (AFRL) (Wright-Patterson Air Force Base, Ohio), and FlexSys Inc. (Ann Arbor, Michigan) to flight-test the ACTE technology [11]. The objective of the project was to demonstrate a seamless adaptive compliant structural control surface in flight.…”

Section: Adaptive Compliant Trailing Edge Flapsmentioning

confidence: 99%

Flight and Ground Operations in Support of Airframe Noise Reduction Tests

Baumann

Waggoner

2018

2018 AIAA/CEAS Aeroacoustics Conference

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Section: Adaptive Compliant Trailing Edge Flapsmentioning

confidence: 99%

Flight and Ground Operations in Support of Airframe Noise Reduction Tests

Baumann

Waggoner

2018

2018 AIAA/CEAS Aeroacoustics Conference

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“…Their approaches suggest that even with a small portion of morphing wing a fuel consumption reduction of more than 5% is possible on conventional aircraft [4]. Some of the structural designs are already applied on actual flying aircraft showing the maturation of some technologies [5]. These approaches are highly applicable to modern sailplanes with possibility of retrofitting current sailplanes with morphing flaps.…”

Section: Introductionmentioning

confidence: 99%

Investigation of performance gains on a sailplane with morphing wing trailing edge

Lendraitis

2019

mech

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Increasing the performance of a modern sailplane is challenging. Most of the known valid approaches have already been applied in practice. Morphing technology, which could allow to adapt to various flight stages is yet to be applied. An investigation of possible flight performance benefits of such technology is carried out here. Using a genetic algorithm, a morphing trailing edge flap for airfoil HQ-17 is formed for -4° and +12° flap deflections. The performance is evaluated and compared with a regular flap, which shows that for the HQ-17 airfoil, drag could be reduced by up to 36% in comparison with regular flap. To show the advantage of morphing flaps, a hypothetical sailplane wing is modeled and evaluated with morphing and conventional flaps using non-linear LLT method. Results show that incorporation of a morphing flap could extend the flight envelope and increase the L/D ratio by 2-5% trough the full flight speed range.

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“…Another trailing edge morphing concept has been developed by NASA in cooperation with FlexSys Inc. Endurance flight tests are currently done, [6]. The Adaptive Compliant Trailing Edge flaps demonstrates the ability of a compliant structure to be actuated and deformed.…”

Section: Introductionmentioning

confidence: 99%

Implementation of a Hybrid Electro-Active Actuated Morphing Wing in Wind Tunnel

Jodin

Scheller

Duhayon

et al. 2017

SSP

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OATAO is an open access repository that collects the work of Toulouse researchers and makes it freely available over the web where possible. This is an author-deposited version published in: http://oatao.univ-toulouse.fr/ Eprints ID: 19940 Abstract. Amongst current aircraft research topics, morphing wing is of great interest for improving the aerodynamic performance. A morphing wing prototype has been designed for wind tunnel experiments. The rear part of the wing -corresponding to the retracted flap -is actuated via a hybrid actuation system using both low frequency camber control and a high frequency vibrating trailing edge. The camber is modified via surface embedded shape memory alloys. The trailing edge vibrates thanks to piezoelectric macro-fiber composites. The actuated camber, amplitude and frequency ranges are characterized. To accurately control the camber, six independent shape memory alloy wires are controlled through nested closed-loops. A significant reduction in power consumption is possible thanks this control strategy. The effects on flow via morphing have been measured during wind tunnel experiments. This low scale mock-up aims to demonstrate the hybrid morphing concept, according to actuator capabilities point of view as well as aerodynamic performance.

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Flight Testing of FlexFloil^TM Adaptive Compliant Trailing Edge

Cited by 56 publications

References 4 publications

Flight and Ground Operations in Support of Airframe Noise Reduction Tests

Flight and Ground Operations in Support of Airframe Noise Reduction Tests

Investigation of performance gains on a sailplane with morphing wing trailing edge

Implementation of a Hybrid Electro-Active Actuated Morphing Wing in Wind Tunnel

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Flight Testing of FlexFloilTM Adaptive Compliant Trailing Edge

Cited by 56 publications

References 4 publications

Flight and Ground Operations in Support of Airframe Noise Reduction Tests

Flight and Ground Operations in Support of Airframe Noise Reduction Tests

Investigation of performance gains on a sailplane with morphing wing trailing edge

Implementation of a Hybrid Electro-Active Actuated Morphing Wing in Wind Tunnel

Contact Info

Product

Resources

About

Flight Testing of FlexFloil^TM Adaptive Compliant Trailing Edge