Morphing wing with skin discontinuity – kinematic concept

Tarnowski, Andrzej

doi:10.1108/aeat-11-2016-0208

Cited by 4 publications

(4 citation statements)

References 15 publications

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“…During the comparison study, the XFOIL results did not match with FLUENT at high Reynold's number (3,492,402) as shown in Figure 8. There was a noticeable delay in the stall AoA attained by Config_3, as predicted by XFOIL.…”

Section: Resultsmentioning

confidence: 93%

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A 2d aerodynamic study on morphing of the naca 2412 aerofoil

Meghani¹

2019

13th Research and Education in Aircraft Design: Conference Proceedings

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This paper investigates the potential of modifications of the NACA 2412 aerofoil geometry which could be implemented as a morphing wing in the Cessna 172SP. A 2D study on three morphing configurations: landing, take-off and stall maneuvering was conducted. The new geometries were designed using XFLR5. The initial aerodynamics characteristics were computed using XFOIL and compared to that of NACA 2412 in the Cessna 172SP. A selected configuration (landing) was tested at the University of Brighton wind tunnel facility and comparison to XFOIL predictions. Moreover, the ESDU 07010 report was used to extrapolate the Reynold's number to full scale, which was necessary to obtain an approximation of the aerodynamic characteristics at actual flight. The paper presents results of ANSYS FLUENT simulations for all three configurations. Results reveal that XFOIL is suitable for morphing airfoil configuration analysis but only at low Reynolds number (Re≈500,000). Adaptive aerofoil geometry improves the lift to drag (L/D) ratio by decreasing the drag coefficient; it also expands the flight envelope by delaying stall.

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Section: Resultsmentioning

confidence: 93%

“…Its construction consists of a multi-flap control system and integrates all control function (pitch, roll and yaw) with continuous performance optimisation by changing multipoint wing twist distribution. [3]…”

Section: Modern Wing Morphing Technologymentioning

confidence: 99%

A 2d aerodynamic study on morphing of the naca 2412 aerofoil

Meghani¹

2019

13th Research and Education in Aircraft Design: Conference Proceedings

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“…The proposed novel construction of the discontinuous morphing flying wing 1 depicted in Figure 1, has not been previously used as wing structure. It is formed by individual, rigid segments without shared or continuous skin.…”

Section: Discontinuous Morphingmentioning

confidence: 99%

Design of morphing wing with surface discontinuity

Tarnowski

Goetzendorf‐Grabowski

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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Aircraft wing morphing or radical shape change in flight has long been the subject of inquisitive research around the world. It happens because morphing ensures optimal adaptation to any flight conditions such as takeoff , cruise, landing and other manoeuvres. The current state of material engineering is not yet in a position to provide adequate technologies to achieve such significant changes in the wing's shape as morphing requires, though interesting progress can be observed. This article presents a new concept of the wing morphing, which potentially circumvents problems related to the elastic deformation of the wing structure. The first part of this article presents the principle of the operation and capabilities of the morphing wing, while the second part focuses on preparation for investigation of its numerical aerodynamic characteristics as groundwork to wind tunnel research.

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“…Generally, a successful wing morphing system must be able to overcome the aerodynamic load shifting (due to the change in aerodynamic center of aircraft during morphing) as well as the weight penalty of added mechanical systems. Tarnowski and Goetzendorf-Grabowski [21] and Tarnowski [22] presented a novel concept of wing morphing that circumvented the issue of elastic deformation. e interesting part of the study was its validation through wind tunnel testing, which is generally not attempted during morphing studies.…”

Section: Introductionmentioning

confidence: 99%

Stability Characteristics of Wing Span and Sweep Morphing for Small Unmanned Air Vehicle: A Mathematical Analysis

Umer

Maqsood

Riaz

et al. 2020

Mathematical Problems in Engineering

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Morphing aircraft are the flight vehicles that can reconfigure their shape during the flight in order to achieve superior flight performance. However, this promising technology poses cross-disciplinary challenges that encourage widespread design possibilities. This research aims to investigate the flight dynamic characteristics of various morphed wing configurations that can be incorporated in small-scale UAVs. The objective of this study was to analyze the effects of in-flight wing sweep and wingspan morphing on aerodynamic and flight stability characteristics. Longitudinal, lateral, and directional characteristics were evaluated using linearized equations of motion. An open-source code based on Vortex Lattice Method (VLM) assuming quasi-steady flow was used for this purpose. Trim points were identified for a range of angles of attack in prestall regime. The aerodynamic coefficients and flight stability derivatives were compared for the aforementioned morphing schemes with a fixed-wing counterpart. The results indicated that wingspan morphing is better than wing sweep morphing to harness better aerodynamic advantages with favorable flight stability characteristics. However, extension in wingspan beyond certain limits jeopardizes the advantages. Dynamically, wingspan and sweep morphing schemes behave in an exactly opposite way for longitudinal modes, whereas lateral-directional dynamics act in the same fashion for both morphing schemes. The current study provided a baseline to explore the advanced flight dynamic aspects of employed wing morphing schemes.

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Morphing wing with skin discontinuity – kinematic concept

Cited by 4 publications

References 15 publications

A 2d aerodynamic study on morphing of the naca 2412 aerofoil

A 2d aerodynamic study on morphing of the naca 2412 aerofoil

Design of morphing wing with surface discontinuity

Stability Characteristics of Wing Span and Sweep Morphing for Small Unmanned Air Vehicle: A Mathematical Analysis

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