Relevant bibliographies by topics / Droop nose leading edge

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Droop nose leading edge'

Author: Grafiati
Published: 18 April 2022
Last updated: 30 July 2025

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Journal articles on the topic "Droop nose leading edge"

1

Ameduri, Salvatore. "A SMA Based Morphing Leading Edge Architecture." Advanced Materials Research 1016 (August 2014): 383–88. http://dx.doi.org/10.4028/www.scientific.net/amr.1016.383.

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This paper analyses a morphing leading edge device, activated by a Shape Memory Alloy (SMA) actuator. The objective is to achieve the Droop Nose effect for particular phases of the flight (e.g. take-off, landing), both obtaining an increased lift and preserving the laminar flow. The device is constituted of: a kinematic chain at the level of the wing section, transmitting motion to the skin, this way fitting the Droop Nose target shape; a span-wise architecture integrated with a SMA actuator, ensuring both a reduction of the actuation forces and the balancing of the aerodynamic external load.
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Rudenko, Anton, André Hannig, Hans Peter Monner, and Peter Horst. "Extremely deformable morphing leading edge: Optimization, design and structural testing." Journal of Intelligent Material Systems and Structures 29, no. 5 (2017): 764–73. http://dx.doi.org/10.1177/1045389x17721036.

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The future generation of high-lift devices needs to be improved to reduce the noise footprint and increase the performance for takeoff and landing of transport aircraft. To contribute to these goals, an active blown Coandă flap-based high-lift system is being investigated within the German national Collaborative Research Center 880 as an alternative to the state-of-the-art flaps. A key part of this system is an adaptive gapless droop nose with extremely large morphing deformation. The design and construction of this component are based on a structural optimization framework. The framework cons
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Vasista, Srinivas, Johannes Riemenschneider, Ralf Keimer, Hans Peter Monner, Felix Nolte, and Peter Horst. "Morphing Wing Droop Nose with Large Deformation: Ground Tests and Lessons Learned." Aerospace 6, no. 10 (2019): 111. http://dx.doi.org/10.3390/aerospace6100111.

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A design for a new high lift system that features a morphing wing leading edge “droop nose” has the potential to generate high lift coefficients whilst mitigating airframe noise emissions. This seamless, continuous, and stepless flexible droop nose potentially offers improvements to stall and compressor requirements for an internally-blown active Coandă trailing edge flap. A full-scale, span-trimmed three-dimensional droop nose was manufactured and ground-tested based on results obtained from new design synthesis tools. A new component of the droop nose is the hybrid fiberglass-elastomeric ski
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Themistokleous, Charalampos, Nikolaos-Grigorios Markatos, John Prospathopoulos, Vasilis Riziotis, Giorgos Sieros, and George Papadakis. "A High-Lift Optimization Methodology for the Design of Leading and Trailing Edges on Morphing Wings." Applied Sciences 11, no. 6 (2021): 2822. http://dx.doi.org/10.3390/app11062822.

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Morphing offers an attractive alternative compared to conventional hinged, multi-element high lift devices. In the present work, morphed shapes of a NACA 64A010 airfoil are optimized for maximum lift characteristics. Deformed shapes of the leading and trailing edge are represented through Bezier curves derived from locally defined control points. The optimization process employs the fast Foil2w in-house viscous-inviscid interaction solver for the calculation of aerodynamic characteristics. Transitional flow results indicate that combined leading and trailing edge morphing may increase maximum
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De Gaspari, Alessandro, and Frédéric Moens. "Aerodynamic Shape Design and Validation of an Advanced High-Lift Device for a Regional Aircraft with Morphing Droop Nose." International Journal of Aerospace Engineering 2019 (March 27, 2019): 1–21. http://dx.doi.org/10.1155/2019/7982168.

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In the present work, the aerodynamic shape design of an advanced high-lift system for a natural laminar flow (NLF) wing, based on the combination of a morphing droop nose and a single slot trailing edge flap, is presented. The paper presents both the aerodynamic design and optimization of the NLF wing and the high-lift configuration considering the mutual effects of both flap devices. Concerning the morphing droop nose (DN), after defining the parameterization techniques adopted to describe the geometry in terms of morphing shape and flap settings, the external configuration is obtained by an
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Bashir, Musavir, Simon Longtin-Martel, Nicola Zonzini, Ruxandra Mihaela Botez, Alessandro Ceruti, and Tony Wong. "Optimization and Design of a Flexible Droop Nose Leading Edge Morphing Wing Based on a Novel Black Widow Optimization (B.W.O.) Algorithm—Part II." Designs 6, no. 6 (2022): 102. http://dx.doi.org/10.3390/designs6060102.

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This work presents an aerodynamic and structural optimization for a Droop Nose Leading Edge Morphing airfoil as a high lift device for the UAS-S45. The results were obtained using three optimization algorithms: coupled Particle Swarm Optimization-Pattern Search, Genetic Algorithm, and Black Widow Optimization algorithm. The lift-to-drag ratio was used as the fitness function, and the impact of the choice of optimization algorithm selection on the fitness function was evaluated. The optimization was carried out at various Mach numbers of 0.08, 0.1, and 0.15, respectively, and at the cruise and
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Moens. "Augmented Aircraft Performance with the Use of Morphing Technology for a Turboprop Regional Aircraft Wing." Biomimetics 4, no. 3 (2019): 64. http://dx.doi.org/10.3390/biomimetics4030064.

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This article presents some application of the morphing technology for aerodynamic performance improvement of turboprop regional aircraft. It summarizes the results obtained in the framework of the Clean Sky 2 AIRGREEN2 program for the development and application of dedicated morphing devices for take-off and landing, and their uses in off design conditions. The wing of the reference aircraft configuration considers Natural Laminar Flow (NLF) characteristics. A deformable leading edge morphing device (“droop nose”) and a multi-functional segmented flap system have been considered. For the droop
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Vasista, Srinivas, Felix Nolte, Hans Peter Monner, Peter Horst, and Marco Burnazzi. "Three-dimensional design of a large-displacement morphing wing droop nose device." Journal of Intelligent Material Systems and Structures 29, no. 16 (2018): 3222–41. http://dx.doi.org/10.1177/1045389x18770863.

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The numerical three-dimensional structural design of a large-displacement flexible morphing wing leading edge, otherwise known as a droop nose, is presented in this article. The droop nose is an essential component of a novel internally blown high-lift system for a transport aircraft to delay stall and reduce internal compressor requirements. A design chain consisting of optimization procedures was used to arrive at the structural design of the droop nose composed of a composite fiberglass skin with integral stringers and supporting kinematic mechanisms. The optimization tools aim to produce a
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Bashir, Musavir, Simon Longtin-Martel, Ruxandra Mihaela Botez, and Tony Wong. "Aerodynamic Design Optimization of a Morphing Leading Edge and Trailing Edge Airfoil–Application on the UAS-S45." Applied Sciences 11, no. 4 (2021): 1664. http://dx.doi.org/10.3390/app11041664.

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This work presents an aerodynamic optimization method for a Droop Nose Leading Edge (DNLE) and Morphing Trailing Edge (MTE) of a UAS-S45 root airfoil by using Bezier-PARSEC parameterization. The method is performed using a hybrid optimization technique based on a Particle Swarm Optimization (PSO) algorithm combined with a Pattern Search algorithm. This is needed to provide an efficient exploitation of the potential configurations obtained by the PSO algorithm. The drag minimization and the endurance maximization were investigated for these configurations individually as two single-objective op
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De Gaspari, Alessandro, Vittorio Cavalieri, and Sergio Ricci. "Advanced Design of a Full-Scale Active Morphing Droop Nose." International Journal of Aerospace Engineering 2020 (June 18, 2020): 1–19. http://dx.doi.org/10.1155/2020/1086518.

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This paper describes the design of a morphing droop nose conceived to increase the performance in high-lift conditions of a twin-prop regional aircraft, while ensuring the natural flow laminarity of the wing. Starting from the results obtained in a previous phase, mainly concerned with the performance augmentation, a detailed structural design is conducted. The main aim is the achievement of a feasible solution based on the use of conventional materials, such as aluminium alloy for the internal structure and glass-fibre for the skin. A finite element model of the complete device is generated f
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Dissertations / Theses on the topic "Droop nose leading edge"

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Pecorella, Daniele. "Methodology for the design and optimization of a morphing wing droop-nose structure for greener aircraft." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2022.

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Droop-Nose Leading Edge (DNLE) morphing wings are one of the most promising devices in order to achieve aerodynamic drag and noise reduction during take-off and landing phases. An accurate design of these structures could lead to the decrease of aircraft fuel consumption in the perspective of reaching a greener aviation, following the objectives indicated by Flightpath 2050 issued by the E.U. However, due to the challenges related to the realization of this technology and TRL reached, DNLE are more likely implemented in Unmanned Aerial Systems (UAS) for testing and evaluation purposes. In the
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Books on the topic "Droop nose leading edge"

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J, Kerschen E., and United States. National Aeronautics and Space Administration., eds. Leading-edge receptivity for blunt-nose bodies: Semi-annual progress report. National Aeronautics and Space Administration, 1992.

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J, Kerschen E., and United States. National Aeronautics and Space Administration., eds. Leading-edge receptivity for blunt-nose bodies: Semi-annual progress report. National Aeronautics and Space Administration, 1992.

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J, Kerschen E., and United States. National Aeronautics and Space Administration., eds. Leading-edge receptivity for blunt-nose bodies: Semi-annual progress report. National Aeronautics and Space Administration, 1992.

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4

Hammerton, P. W. Leading-edge receptivity for blunt-nose bodies: Semi-annual progress report. Arizona University, Dept. of Aerospace and Mechanical Engineering, 1992.

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United States. National Aeronautics and Space Administration., ed. Leading-edge receptivity for blunt-nose bodies: Annual progress report, May 1, 1990-April 30, 1991. National Aeronautics and Space Administration, 1991.

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United States. National Aeronautics and Space Administration., ed. Leading-edge receptivity for blunt-nose bodies: Annual progress report, May 1, 1990-April 30, 1991. National Aeronautics and Space Administration, 1991.

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7

Kerschen, Edward J. Leading-edge receptivity for blunt-nose bodies: Annual progress report, May 1, 1990 - April 30, 1991. Arizona University, 1991.

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8

National Aeronautics and Space Administration (NASA) Staff. Leading-Edge Receptivity for Blunt-Nose Bodies. Independently Published, 2018.

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9

National Aeronautics and Space Administration (NASA) Staff. Effects of Nose Radius and Aerodynamic Loading on Leading Edge Receptivity. Independently Published, 2018.

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Book chapters on the topic "Droop nose leading edge"

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Vasista, Srinivas, Johannes Riemenschneider, Hans Peter Monner, Ralf Keimer, Felix Nolte, and Peter Horst. "Large-Displacement Morphing Wing Leading Edge Droop Nose: Optimization, Manufacture and Instrumentation." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-52429-6_10.

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Nolte, Felix, André Hannig, Peter Horst, Srinivas Vasista, and Hans Peter Monner. "Large-Displacement Morphing Wing Leading Edge Droop Nose: Structural Concept, Testing and Systems Integration." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-52429-6_11.

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Reddy, Mahendranth, Kumar K. Pavan, Prakash K. Bhanu, et al. "Experimental Investigation of Wing with Leading Edge Droop." In Advances in Additive Manufacturing Technologies. CRC Press, 2024. http://dx.doi.org/10.1201/9781003545774-81.

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Hammerton, P. W., and E. J. Kerschen. "Effect of Nose Bluntness on Leading-Edge Receptivity." In Instability, Transition, and Turbulence. Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2956-8_43.

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Watkins, Tyler, Jesse Redford, Franklin Green, Jerry Dahlberg, Peter Tkacik, and Russell Keanini. "Hypersonic Flow over Closed and Open Nose Missile Bodies: Raw and SVD-Enhanced Schlieren Imaging, Numerical Modeling, and Physical Analysis." In Boundary Layer Flows - Modelling, Computation, and Applications of Laminar, Turbulent Incompressible and Compressible Flows [Working Title]. IntechOpen, 2022. http://dx.doi.org/10.5772/intechopen.105617.

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Understanding and mitigating against high heat loads at leading and blunt aerodynamic surfaces during hypersonic flight represents an ongoing technological challenge. Recent work has shown that the commercial software package, STAR CCM+, can provide reliable predictions of hypersonic aerothermodynamic flow and heating, under a wide range of complex, but common conditions. This chapter presents a preliminary experimental and numerical investigation of hypersonic flow over closed- and open-nose missile bodies, where the latter have been proposed as a means of reducing leading edge heat transfer.
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Conference papers on the topic "Droop nose leading edge"

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Zhao, Guo-qing, and Qi-jun Zhao. "Dynamic Stall Control on Rotor Airfoil via Combination of Synthetic Jet and Droop Leading-Edge." In Vertical Flight Society 71st Annual Forum & Technology Display. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10097.

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A novel strategy of dynamic stall control for rotor airfoil via combinational method by using variable-droop leading edge (VDLE) and synthetic jet is numerically investigated. As foundations, body-fitted grids around oscillatory rotor airfoil with VDLE are regenerated by reconstruction of airfoil and solution of Poisson equations, and the unsteady flowfield around airfoil is simulated by solving RANS equations. To improve the computational accuracy and efficiency, the ROE-MUSCL scheme, k-ε SST turbulence model and implicit LU-SGS scheme are adopted. Additional, a suction/blowing type boundary
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Halder, Atanu, and Moble Benedict. "Nonlinear Aeroelastic Coupled Trim Analysis of a Twin-Cyclocopter in Forward Flight." In Vertical Flight Society 74th Annual Forum & Technology Display. The Vertical Flight Society, 2018. http://dx.doi.org/10.4050/f-0074-2018-12840.

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In this paper, detailed development of a nonlinear aeroelastic coupled trim model of a twin-cyclocopter in forward flight is presented. Twin-cyclocopter consists of two cycloidal rotors as main thrusters and a conventional nose rotor for pitch-torque balance. It is shown that five control inputs (mean and differential rpm, mean and differential phase offset of cyclorotors, rpm of nose rotor) are needed to balance three moments and two forces on cyclocopter in forward flight while forces along lateral direction remain balanced at all stages. In this coupled trim procedure, blade aeroelastic res
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Niemiec, Robert, Farhan Gandhi, and George Jacobellis. "Reversible Airfoil for Stopped Rotors in High Speed Flight." In Vertical Flight Society 70th Annual Forum & Technology Display. The Vertical Flight Society, 2014. http://dx.doi.org/10.4050/f-0070-2014-9426.

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This study starts with the design of a reversible airfoil rib for stopped-rotor applications, where the sharp trailing-edge morphs into the rounded leading-edge, and vice-versa. A NACA0012 airfoil is approximated in a piecewise linear manner and straight, rigid outer profile links used to define the airfoil contour. The end points of the profile links connect to control links, each set on a central actuation rod via an offset. Chordwise motion of the actuation rod moves the control and the profile links and reverses the airfoil. The paper describes the design methodology and evolution of the f
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Jirasek, Adam, and Olivier Amoignon. "Design of a High Lift System with a Leading Edge Droop Nose." In 27th AIAA Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-3614.

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Vasista, Srinivas, Johannes Riemenschneider, Hans P. Monner, Felix Nolte, and Peter Horst. "Manufacture and Testing of a Large-displacement Droop-Nose Morphing Wing Leading Edge." In AIAA Scitech 2019 Forum. American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-1858.

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Riemenschneider, Johannes, Martin Radestock, Srinivas Vasista, Oliver Huxdorf, and Hans Peter Monner. "Droop Nose With Elastic Skin." In ASME 2016 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/smasis2016-9130.

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Morphing is a technology with high potential to reduce emissions in aviation by adapting the shape of the wings to varying external operating conditions. This paper is presenting results from the EU FP7 funded CHANGE project, where different concepts to adapt a UAV wing airfoil to different demands were investigated. The paper is concentrating on the design and experimental testing of a droop nose, which transforms the leading edge part of the 60 cm chord airfoil from a NACA 6510 shape for loiter and low speed to a NACA 2510 shape for a high speed mission. This paper is presenting the use of a
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Monner, Hans, Markus Kintscher, T. Lorkowski, and S, Storm. "Design of a Smart Droop Nose as Leading Edge High Lift System for Transportation Aircrafts." In 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-2128.

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Bashir, Musavir, Ruxandra M. Botez, and Tony Wong. "Design and Optimization of Droop Nose Leading Edge (DNLE) Morphing Wing Skin for the UAS-S45." In AIAA SCITECH 2024 Forum. American Institute of Aeronautics and Astronautics, 2024. http://dx.doi.org/10.2514/6.2024-2150.

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Riemenschneider, Johannes, Srinivas Vasista, Bram van de Kamp, and Hans Peter Monner. "Bench Top Test of a Droop Nose With Compliant Mechanism." In ASME 2015 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/smasis2015-8853.

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Morphing is a technology with high potential to reduce emissions in aviation, since it enables wings to adapt their shape to operate at a higher efficiency over the full range of flight conditions. This paper is presenting a concept to adapt camber by drooping the nose. The scope is the setup and bench top testing of a full scale wing tip leading edge wind tunnel model with a morphing droop nose. The complete model features a span of 1.3 m and a strong taper from the root to the tip. For completeness, the design approach is covered as well. The design comprises a GFRP skin to be drooped by two
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Radestock, Martin, Alexander Falken, Johannes Riemenschneider, and Markus Kintscher. "Hybrid Skin Design of the Transition Region Between Morphing Wing and Fixed Wing." In ASME 2018 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/smasis2018-7976.

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The adaptation of a wing contour is important for most aircraft, because of the different flight states. That’s why an enormous number of mechanisms exists and reaches from conventional slats and flaps to morphing mechanisms, which are integrated in the wing. Especially integrated mechanisms reduce the number of gaps at the wing skin and produce less turbulent flow. However these concepts are located at a certain section of the wing. This leads to morphing and fixed wing sections, which are located next to each other. Commonly, the transition between these sections is not designed or a wing fe
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