Numerical simulation and wind tunnel tests investigation and validation of a morphing wing-tip demonstrator aerodynamic performance

Gabor, Oliviu Şugar; Koreanschi, Andreea; Botez, Ruxandra Mihaela; Mamou, Mahmoud; Mébarki, Youssef

doi:10.1016/j.ast.2016.03.014

Cited by 48 publications

(11 citation statements)

References 35 publications

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“…To avoid the contamination of pressure sensors, but also the negative influence on the pressure readings from the 32 Kulite sensors, the area on the upper wing surface where the two sensor lines were mounted was not coated with the paint. The measurement of the monitored surface temperature has been performed with a Jenoptik VarioCAM camera, operating at a frame rate of 30 Hz at 640 × 480 IR pixel resolution and equipped with 60 • lens to visualise the transition region over the whole upper surface of the morphing wing model (46)(47)(48)(49) . upstream and downstream fronts.…”

Section: Results Obtained During Wind-tunnel Testing Of the Morphing mentioning

confidence: 99%

A new hybrid control methodology for a morphing aircraft wing-tip actuation mechanism

et al. 2019

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The focus of this paper is on the modelling of miniature electromechanical actuators used in a morphing wing application, on the development of a control concept for these actuators, and on the experimental validation of the designed control system integrated in the morphing wing-tip model for a real aircraft. The assembled actuator includes as its main component a brushless direct current motor coupled to a trapezoidal screw by using a gearing system. A Linear Variable Differential Transformer (LVDT) is attached on each actuator giving back the actuator position in millimetres for the control system, while an encoder placed inside the motor provides the position of the motor shaft. Two actuation lines, each with two actuators, are integrated inside the wing model to change its shape. For the experimental model, a full-scaled portion of an aircraft wing tip is used with the chord length of 1.5 meters and equipped on the upper surface with a flexible skin made of composite fibre materials. A controllable voltage provided by a power amplifier is used to drive the actuator system. In this way, three control loops are designed and implemented, one to control the torque and the other two to control the position in a parallel architecture. The parallel position control loops use feedback signals from different sources. For the first position control loop, the feedback signal is provided by the integrated encoder, while for the second one, the feedback signal comes from the LVDT. For the experimental model, the parameters for the torque control, but also for the position control-based encoder signal, are implemented in the power amplifier energising the electrical motor. On the other hand, a National Instruments real-time system is used to implement and test the position control-based LVDT signal. The experimental validation of the developed control system is realised in two independent steps: bench testing with no airflow and wind-tunnel testing. The pressure data provided by a number of Kulite sensors equipping the flexible skin upper surface and the infrared thermography camera visualisations are used to estimate the laminar-to-turbulent transition point position.

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Section: Results Obtained During Wind-tunnel Testing Of the Morphing mentioning

confidence: 99%

A new hybrid control methodology for a morphing aircraft wing-tip actuation mechanism

et al. 2019

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“…By modulating the shape memory intensity and the positioning of the strips, a novel and enhanced model for the delivery of a morphable wing was defined. The comparison of the results from wind tunnel tests and numerical modeling regarding a morphing wing fitted out with flexible upper surface actuated by aileron have been presented by Gabor et al [32]. The experimental setup was demonstrative of a real airplane's wing tip section.…”

Section: Sma Applications On Wingsmentioning

confidence: 99%

Shape Memory Alloys for Aerospace, Recent Developments, and New Applications: A Short Review

2020

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Shape memory alloys (SMAs) show a particular behavior that is the ability to recuperate the original shape while heating above specific critical temperatures (shape memory effect) or to withstand high deformations recoverable while unloading (pseudoelasticity). In many cases the SMAs play the actuator's role. Starting from the origin of the shape memory effect, the mechanical properties of these alloys are illustrated. This paper presents a review of SMAs applications in the aerospace field with particular emphasis on morphing wings (experimental and modeling), tailoring of the orientation and inlet geometry of many propulsion system, variable geometry chevron for thrust and noise optimization, and more in general reduction of power consumption. Space applications are described too: to isolate the micro-vibrations, for low-shock release devices and self-deployable solar sails. Novel configurations and devices are highlighted too.Materials 2020, 13, 1856 2 of 16 and novelty of the proposals. Ni-Ti alloys are the most employed ones, but the subject is not limited to them. Origin of the Shape Memory EffectFor the comprehension of the basic principles regarding the shape memory effect and pseudoelasticity, many contributions are useful. The crystallography of martensite, the transformation temperatures, and rate of martensite formation are discussed in details by Nishiyama [6].Materials 2020, 13, x FOR PEER REVIEW 2 of 16 relevance, number of articles, and novelty of the proposals. Ni-Ti alloys are the most employed ones, but the subject is not limited to them. Origin of the Shape Memory EffectFor the comprehension of the basic principles regarding the shape memory effect and pseudoelasticity, many contributions are useful. The crystallography of martensite, the transformation temperatures, and rate of martensite formation are discussed in details by Nishiyama [6]. Figure 1. Binary phase diagram of Ti-Ni alloy [7]. Figure 1

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“…ANSYS Fluent version 16.1 for simulation was used including the "coupled" algorithm and the second order upwind for solving of the steady-state Navier-Stokes equations. In order to precisely estimate adverse pressure gradient flows in the flow area on the surface of wing and the transition flow, the SST k-ω was chosen as the turbulence model [13,14,15]. Each calculation consists of 1000 iterations.…”

Section: Numerical Setup and Validationsmentioning

confidence: 99%

The impact of aspect ratio on aerodynamic performance and flow separation behavior of a model wing composed from different profiles

Aşkan

Tangöz

2018

Journal of Energy Systems

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In this study the impact of aspect ratio on the aerodynamic performances and flow separation behavior were investigated on a model wing made up four different profiles used to the wing of the Boeing 737-Classic aircrafts. The experiments were carried out in a wind tunnel with low speed at different angles of attack ranging from -4° to 40° and at the 2x10 5 Reynolds number on wing models having different aspect ratios (0.7-1.3). It was observed from the experiments and numerical studies that the changing of the aspect ratio affected the drag and lift and flow separation. The highest lift/drag ratio has been measured from the wing having aspect ratio of 1.3 at angle of attack of 7 0 . Moreover, the airflow was flowed as laminar in the areas near the middle of the wing until angle of attack of 24 0 . But, the flow was disturbed at wing tip due to vortex. The separation bubbles have been seen at 24°-32 0 for all aspect ratios. In addition, the increase of angle of attack caused the bubbles form clearly for 1.1 and 1.3 aspect ratios. Finally, the increases in aspect ratio and in angle of attack have been triggered flow separation. Cite this paper as:Aşkan, A., Tangöz, S., The impact of aspect ratio on aerodynamic performance and flow separation behavior of a model wing composed from different profiles.

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Numerical simulation and wind tunnel tests investigation and validation of a morphing wing-tip demonstrator aerodynamic performance

Cited by 48 publications

References 35 publications

A new hybrid control methodology for a morphing aircraft wing-tip actuation mechanism

A new hybrid control methodology for a morphing aircraft wing-tip actuation mechanism

Shape Memory Alloys for Aerospace, Recent Developments, and New Applications: A Short Review

The impact of aspect ratio on aerodynamic performance and flow separation behavior of a model wing composed from different profiles

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