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Journal articles on the topic 'Droop nose leading edge'

Author: Grafiati

Published: 18 April 2022

Last updated: 30 July 2025

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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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2

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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3

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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4

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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5

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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6

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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7

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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8

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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9

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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10

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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Bashir, Musavir, Simon Longtin-Martel, Ruxandra Mihaela Botez, and Tony Wong. "Optimization and Design of a Flexible Droop-Nose Leading-Edge Morphing Wing Based on a Novel Black Widow Optimization Algorithm—Part I." Designs 6, no. 1 (2022): 10. http://dx.doi.org/10.3390/designs6010010.

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An aerodynamic optimization for a Droop-Nose Leading-Edge (DNLE) morphing of a well-known UAV, the UAS-S45, is proposed, using a novel Black Widow Optimization (BWO) algorithm. This approach integrates the optimization algorithm with a modified Class-Shape Transformation (CST) parameterization method to enhance aerodynamic performance by minimizing drag and maximizing aerodynamic endurance at the cruise flight condition. The CST parameterization technique is used to parameterize the reference airfoil by introducing local shape changes and provide skin flexibility to obtain various optimized mo

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12

Bashir, Musavir, Nicola Zonzini, Ruxandra Mihaela Botez, Alessandro Ceruti, and Tony Wong. "Flow Control around the UAS-S45 Pitching Airfoil Using a Dynamically Morphing Leading Edge (DMLE): A Numerical Study." Biomimetics 8, no. 1 (2023): 51. http://dx.doi.org/10.3390/biomimetics8010051.

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This paper investigates the effect of the Dynamically Morphing Leading Edge (DMLE) on the flow structure and the behavior of dynamic stall vortices around a pitching UAS-S45 airfoil with the objective of controlling the dynamic stall. An unsteady parametrization framework was developed to model the time-varying motion of the leading edge. This scheme was then integrated within the Ansys-Fluent numerical solver by developing a User-Defined-Function (UDF), with the aim to dynamically deflect the airfoil boundaries, and to control the dynamic mesh used to morph and to further adapt it. The dynami

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13

Kintscher, Markus, Johannes Riemenschneider, Hans-Peter Monner, and Martin Wiedemann. "Structural concept of an adaptive shock control bump spoiler." CEAS Aeronautical Journal 12, no. 3 (2021): 509–18. http://dx.doi.org/10.1007/s13272-021-00507-9.

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AbstractDrag reduction technologies in aircraft design are the key enabler for reducing emissions and for sustainable growth of commercial aviation. Laminar wing technologies promise a significant benefit by drag reduction and are, therefore, under investigation in various European projects. However, of the established moveable concepts and high-lift systems thus far most do not cope with the requirements for natural laminar flow wings. To this aim, new leading edge high-lift systems have been the focus of research activities in the last 5 years. Such leading edge devices investigated in proje

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14

BUSH, JOHN W. M. "The anomalous wake accompanying bubbles rising in a thin gap: a mechanically forced Marangoni flow." Journal of Fluid Mechanics 352 (December 10, 1997): 283–303. http://dx.doi.org/10.1017/s0022112097007350.

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A novel wake structure, observed as penny-shaped air bubbles rise at moderate Reynolds number through a thin layer of water bound between parallel glass plates inclined at a shallow angle relative to the horizontal, is reported. The structure of the wake is revealed through tracking particles suspended in the water. The wake completely encircles the rising bubble, and is characterized by a reverse surface flow or ‘edge jet’ which transports fluid in a thin boundary layer along the bubble surface from the tail to the nose at speeds which are typically an order of magnitude larger than the bubbl

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15

Barfknecht, Nils, and Dominic von Terzi. "Aerodynamic interaction of rain and wind turbine blades: the significance of droplet slowdown and deformation for leading-edge erosion." Wind Energy Science 9, no. 12 (2024): 2333–57. https://doi.org/10.5194/wes-9-2333-2024.

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Abstract. Leading-edge rain erosion is a severe problem in the wind energy community since it leads to blade damage and a reduction in annual energy production by up to a few percent. The impact speed of rain droplets is a key driver of the erosion rate; therefore, its precise computation is essential. This study investigates the aerodynamic interaction of rain droplets and wind turbine blades. Based on findings from the literature and an analysis of the relevant parameter space, it is found that the aerodynamic interaction leads to a reduction in the impact speed. Additionally, the rain dropl

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16

Ma, Yi-yang, Qi-jun Zhao, and Guo-qing Zhao. "New combinational active control strategy for improving aerodynamic characteristics of airfoil and rotor." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 4 (2019): 977–96. http://dx.doi.org/10.1177/0954410019893193.

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In order to improve the aerodynamic characteristics of rotor, a new active flow control strategy by combining a synthetic jet actuator and a variable droop leading-edge or a trailing-edge flap has been proposed. Their control effects are numerically investigated by computational fluid dynamics (CFD) method. The validated results indicate that variable droop leading-edge and synthetic jet can suppress the formation of dynamic stall vortex and delay flow separation over rotor airfoil. Compared with the baseline state, Cdmax and Cmmax are significantly reduced. Furthermore, parametric analyses on

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17

Li, Congcong, Yongjie SHI, Guohua Xu, and Xingliang Liu. "Research on the forward flight performance of rotor based on variable-droop leading edge." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 39, no. 3 (2021): 668–74. http://dx.doi.org/10.1051/jnwpu/20213930668.

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Aiming at the dynamic stall phenomenon of the retreating side of the rotor in forward flight, the existing flow control method of dynamic leading edge droop was applied to the flow control of forward-flying rotor at three-dimensional scale. A numerical simulation method based on variable droop leading edge is established in this paper. The seesaw rotor is taken as the research object, the moving overset mesh method and RBF grid deformation technology are used, the integral form of Reynolds average N-S equation is the main control equation. The influence of the dynamic leading edge at r/R=0.75~

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18

Ross, Holly M., and John N. Perkins. "Tailoring stall characteristics using leading edge droop modification." Journal of Aircraft 31, no. 4 (1994): 767–72. http://dx.doi.org/10.2514/3.46559.

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19

Park, K., H. Sun, and S. Lee. "The effect of leading-edge droop on the performance of cavitating hydrofoil in an oscillating environment." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 223, no. 10 (2009): 2331–39. http://dx.doi.org/10.1243/09544062jmes1142.

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The hydrodynamics of cavitating hydrofoil in oscillating motion are important in the aspect of the performance and hydro-elasticity of the control surface of the ship. The effect of leading-edge droop is numerically studied in the oscillating hydrofoil with cavitation. A two-phase incompressible Navier—Stokes solver is used to compute the cavitation flow. The hydrodynamic performance of the baseline hydrofoil is compared with that of the fixed droop and the variable droop hydrofoil. The droop models delay the separation behind the sheet cavitation near the maximum angle of attack. When the pit

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20

Tuck, E. O., and A. Dostovalova. "Aerofoil nose shapes delaying leading-edge separation." Aeronautical Journal 104, no. 1039 (2000): 433–37. http://dx.doi.org/10.1017/s0001924000091880.

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Abstract If an aerofoil of chord c has a parabolic nose with radius of curvature r, and is placed at angle-of-attack α to a stream, the laminar boundary layer on its upper surface remains unseparated for α<0.8l8. In the present paper we consider some smooth local modifications to the leading edge. Symmetric modifications of the nature of local sharpening of the nose can improve this result to at least α<0.897. Further improvements are possible for unsymmetrical (e.g. drooped) noses, and an example of a ‘drooped’ nose with α<0.912 is shown.

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21

Rusak, Z. "Transonic flow around the leading edge of a thin airfoil with a parabolic nose." Journal of Fluid Mechanics 248 (March 1993): 1–26. http://dx.doi.org/10.1017/s0022112093000667.

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Transonic potential flow around the leading edge of a thin two-dimensional general airfoil with a parabolic nose is analysed. Asymptotic expansions of the velocity potential function are constructed at a fixed transonic similarity parameter (K) in terms of the thickness ratio of the airfoil in an outer region around the airfoil and in an inner region near the nose. These expansions are matched asymptotically. The outer expansion consists of the transonic small-disturbance theory and it second-order problem, where the leading-edge singularity appears. The inner expansion accounts for the flow a

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22

Ross, H. M., L. P. Yip, J. N. Parkins, R. J. Vess, and D. B. Owens. "Wing leading-edge droop/slot modification for stall departure resistance." Journal of Aircraft 28, no. 7 (1991): 436–42. http://dx.doi.org/10.2514/3.46046.

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23

Bain, Jeremy J., Lakshmi N. Sankar, J. V. R. Prasad, Oliver A. Bauchau, David A. Peters, and Chengjian He. "Computational Modeling of Variable-Droop Leading Edge in Forward Flight." Journal of Aircraft 46, no. 2 (2009): 617–26. http://dx.doi.org/10.2514/1.39174.

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24

Hammerton, P. W., and E. J. Kerschen. "Boundary-layer receptivity for a parabolic leading edge." Journal of Fluid Mechanics 310 (March 10, 1996): 243–67. http://dx.doi.org/10.1017/s0022112096001796.

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The effect of the nose radius of a body on boundary-layer receptivity is analysed for the case of a symmetric mean flow past a body with a parabolic leading edge. Asymptotic methods based on large Reynolds number are used, supplemented by numerical results. The Mach number is assumed small, and acoustic free-stream disturbances are considered. The case of free-stream acoustic waves, propagating obliquely to the symmetric mean flow is considered. The body nose radius, rn, enters the theory through a Strouhal number, S = ωrn/U, where ω is the frequency of the acoustic wave and U is the mean flow

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25

Chandrasekhara, M. S., P. B. Martin, and C. Tung. "Compressible Dynamic Stall Control Using a Variable Droop Leading Edge Airfoil." Journal of Aircraft 41, no. 4 (2004): 862–69. http://dx.doi.org/10.2514/1.472.

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26

Rusak, Z. "Subsonic flow around the leading edge of a thin aerofoil with a parabolic nose." European Journal of Applied Mathematics 5, no. 3 (1994): 283–311. http://dx.doi.org/10.1017/s0956792500001479.

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Subsonic potential flow around the leading edge of a thin two-dimensional general aerofoil with a parabolic nose at small angles of attack is analysed. Asymptotic expansions of the velocity potential function are constructed at a fixed Mach number in terms of the thickness ratio of the aerofoil in an outer region around the aerofoil and in an inner region near the nose. These expansions are matched asymptotically. The outer expansion consists of linearized aerofoil theory and its second-order problem, where the leading-edge singularity appears. The inner expansion accounts for the flow around

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27

Ashill, P. R., G. L. Riddle, and M. J. Stanley. "Separation control on highly-swept wings with fixed or variable camber." Aeronautical Journal 99, no. 988 (1995): 317–27. http://dx.doi.org/10.1017/s0001924000028566.

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AbstractThis paper describes an experimental investigation into the effect of miniature vortex generators (VGs) on the longitudinal aerodynamic characteristics of a highly-swept wing with drooped leading edges. The experiments were performed in a low-speed windtunnel on a wing of the same delta planform as that used in a previous study. The latter wing was of fixed camber, while the subject of the present study was a wing with three different leading edge droop angles. The maximum reduction in drag due to the VGs was found to be about half that for the fixed-camber wing. This is reconciled wit

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Raj Mohamed, Mohamed Arif, Rajesh Yadav, and Ugur Guven. "Flow separation control using a bio-inspired nose for NACA 4 and 6 series airfoils." Aircraft Engineering and Aerospace Technology 93, no. 2 (2021): 251–66. http://dx.doi.org/10.1108/aeat-08-2019-0170.

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Purpose This paper aims to achieve an optimum flow separation control over the airfoil using a passive flow control method by introducing a bio-inspired nose near the leading edge of the National Advisory Committee for Aeronautics (NACA) 4 and 6 series airfoil. In addition, to find the optimised leading edge nose design for NACA 4 and 6 series airfoils for flow separation control. Design/methodology/approach Different bio-inspired noses that are inspired by the cetacean species have been analysed for different NACA 4 and 6 series airfoils. Bio-inspired nose with different nose length, nose dep

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29

Zhao, Kun, Yong Liang, Tingrui Yue, Zhengwu Chen, and Gareth J. Bennett. "Characterization of the aircraft bay/landing gear coupling noise at low subsonic speeds and its suppression using leading-edge chevron spoiler." Advances in Mechanical Engineering 11, no. 8 (2019): 168781401987143. http://dx.doi.org/10.1177/1687814019871431.

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When the aircraft opens the bay door to let the landing gear either drop or retract, the incoming flow will result in a significant amount of coupling noise from the bay and the landing gear. Here, an experimental study was reported to characterise the acoustic performance and flow field at low subsonic speeds. Also, we examined a passive control method leading-edge chevron spoiler to suppress the noise. The experiment was performed in a low-speed aeroacoustic wind, the bay was simplified as a rectangular cavity and the spoiler was mounted to the leading edge. Both acoustic and aerodynamic mea

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30

Su, Erlong, Ryan Randall, Lee Wilson, and Sergey Shkarayev. "Visualization of vortical flows around a rapidly pitching wing and propeller." International Journal of Micro Air Vehicles 9, no. 1 (2017): 25–43. http://dx.doi.org/10.1177/1756829316685189.

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This study was conducted to visually investigate flows related to fixed-wing vertical-takeoff-and-landing micro air vehicles, using the smoke-wire technique. In particular, the study examines transition between forward flight and near-hover. The experimental model consists of a rigid Zimmerman wing and a propulsion system with contra-rotating propellers arranged in a tractor configuration. The model was pitched about the wing’s aerodynamic center at approximately constant rates using a five-axis robotic arm. Constant-rate pitching angles spanned 20° to 70°. No-pitching and four pitching-rates

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Zhao, Guo-qing, and Qi-jun Zhao. "Dynamic stall control optimization of rotor airfoil via variable droop leading-edge." Aerospace Science and Technology 43 (June 2015): 406–14. http://dx.doi.org/10.1016/j.ast.2015.03.022.

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Rusak, Zvi, Wallace J. Morris, and Yoav Peles. "Prediction of Leading-Edge Sheet Cavitation Inception on Hydrofoils at Low to Moderate Reynolds Number Flows." Journal of Fluids Engineering 129, no. 12 (2007): 1540–46. http://dx.doi.org/10.1115/1.2801350.

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The inception of leading-edge sheet cavitation on two-dimensional smooth thin hydrofoils at low to moderately high Reynolds number flows is investigated by an asymptotic approach and numerical simulations. The asymptotic theory is based on the work of Rusak (1994, “Subsonic Flow Around Leading Edge of a Thin Aerofoil With a Parabolic Nose,” Eur. J. Appl. Mech., 5, pp. 283–311) and demonstrates that the flow about a thin hydrofoil can be described in terms of an outer region, around most of the hydrofoil chord, and an inner region, around the nose, which asymptotically match each other. The flo

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33

Ayton, Lorna J., and Paruchuri Chaitanya. "Analytical and experimental investigation into the effects of leading-edge radius on gust–aerofoil interaction noise." Journal of Fluid Mechanics 829 (September 26, 2017): 780–808. http://dx.doi.org/10.1017/jfm.2017.594.

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This paper investigates the effects of local leading-edge geometry on unsteady aerofoil interaction noise. Analytical results are obtained by extending previous work for parabolic leading edges to leading edges of the form $x^{m}$ for $0<m<1$. Rapid distortion theory governs the interaction of an unsteady vortical perturbation with a rigid aerofoil in compressible steady mean flow that is uniform far upstream. For high-frequency gusts interacting with aerofoils of small total thickness this allows a matched asymptotic solution to be obtained. This paper mainly focusses on obtaining the a

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34

RUSAK, ZVI, and CHUN-WEI WANG. "Transonic flow of dense gases around an airfoil with a parabolic nose." Journal of Fluid Mechanics 346 (September 10, 1997): 1–21. http://dx.doi.org/10.1017/s0022112097006411.

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Transonic potential flow of dense gases of retrograde type around the leading edge of a thin airfoil with a parabolic nose is studied. The analysis follows the approach of Rusak (1993) for a perfect gas. Asymptotic expansions of the velocity potential function are constructed in terms of the airfoil thickness ratio in an outer region around the airfoil and in an inner region near the nose. The outer expansion consists of the transonic small-disturbance theory for dense gases, where a leading-edge singularity appears. Analytical expressions are given for this singularity by constructing similar

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35

Lan, C. Edward, and Ingchung Su. "Effect of a round airfoil nose on leading-edge suction." Journal of Aircraft 24, no. 7 (1987): 472–74. http://dx.doi.org/10.2514/3.45504.

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36

Rossignol, K.-S., A. Suryadi, M. Herr, J. Schmidt, and J. Tychsen. "Experimental investigation of porous materials for trailing-edge noise reduction." International Journal of Aeroacoustics 19, no. 6-8 (2020): 365–84. http://dx.doi.org/10.1177/1475472x20954421.

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The introduction of quiet short take-off and landing for civil aircraft operations in close proximity to the population poses important technological challenges. One critical aspect is the realization of extreme lift augmentation at low acoustic emissions. The aircraft concept selected to achieve this goal is a high-lift system equipped with an active flow-control non-slotted flap and a droop nose. For this specific configuration, trailing edge noise becomes a dominant noise source. Porous materials as a passive means for trailing-edge noise reduction are selected and characterized. Results of

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37

Raj Mohamed, Mohamed Arif, Ugur Guven, and Rajesh Yadav. "Flow separation control of NACA-2412 airfoil with bio-inspired nose." Aircraft Engineering and Aerospace Technology 91, no. 7 (2019): 1058–66. http://dx.doi.org/10.1108/aeat-06-2018-0175.

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Purpose The purpose of this paper is to achieve an optimum flow separation control over the airfoil using passive flow control method by introducing bio-inspired nose near the leading edge of the NACA 2412 airfoil. Design/methodology/approach Two distinguished methods have been implemented on the leading edge of the airfoil: forward facing step, which induces multiple accelerations at low angle of attack, and cavity/backward facing step, which creates recirculating region (axial vortices) at high angle of attack. Findings The porpoise airfoil (optimum bio-inspired nose airfoil) delays the flow

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Walraevens, R. E., and N. A. Cumpsty. "Leading Edge Separation Bubbles on Turbomachine Blades." Journal of Turbomachinery 117, no. 1 (1995): 115–25. http://dx.doi.org/10.1115/1.2835626.

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Results are presented for separation bubbles of the type that can form near the leading edges of thin compressor or turbine blades. These often occur when the incidence is such that the stagnation point is not on the nose of the aerofoil. Tests were carried out at low speed on a single aerofoil to simulate the range of conditions found on compressor blades. Both circular and elliptic shapes of leading edge were tested. Results are presented for a range of incidence, Reynolds number, and turbulence intensity and scale. The principal quantitative measurements presented are the pressure distribut

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Chandrasekhara, M. S., P. B. Martin, and C. Tung. "Compressible Dynamic Stall Performance of a Variable Droop Leading Edge Airfoil with a Gurney Flap." Journal of the American Helicopter Society 53, no. 1 (2008): 18. http://dx.doi.org/10.4050/jahs.53.18.

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Jiao, Jin, Cheng Chen, Bo Wang, Pei Ying, Qiong Wei, and Shengyang Nie. "Active Flow Control Technology Based on Simple Droop Devices and a Co-Flow Jet for Lift Enhancement." Aerospace 12, no. 3 (2025): 198. https://doi.org/10.3390/aerospace12030198.

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The missions of modern aircraft require multiple abilities, such as highly efficient taking-off and landing, fast arrival, and long-endurance hovering. It is difficult to achieve all technical objectives using traditional aircraft design technology. The active flow control technology using the concept of a co-flow jet (CFJ) is a flow control method without a mass source that does not require air from the engine. It has strong flow control ability in low-speed flow, can greatly improve the stall angle of the aircraft, and can obtain large lift enhancement. At transonic conditions, it can lead t

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Antoniou, Spyridon, Stavros Kapsalis, Pericles Panagiotou, and Kyros Yakinthos. "Parametric Investigation of Leading-Edge Slats on a Blended-Wing-Body UAV Using the Taguchi Method." Aerospace 10, no. 8 (2023): 720. http://dx.doi.org/10.3390/aerospace10080720.

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The current study investigated the effect of leading-edge slats on the longitudinal stability at high angles of attack of a Blended-Wing-Body (BWB) Unmanned Air Vehicle (UAV). Using a Design of Experiments (DOE) approach and, specifically, the Taguchi method, four leading-edge slat design parameters were investigated on three different levels. These parameters were the slat semi-span, the rotation of the slat element, the extension forward of the leading edge and the downward drop below the leading edge. An L9 orthogonal array (OA) was used to investigate the influence of these key design para

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Cui, Pengcheng, Guiyu Zhou, Yaobing Zhang, et al. "Improved Delayed Detached-Eddy Investigations on the Flow Control of the Leading-Edge Flat Spoiler of the Cavity in the Low-Aspect-Ratio Aircraft." Aerospace 9, no. 9 (2022): 526. http://dx.doi.org/10.3390/aerospace9090526.

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The internal weapon bay is widely used in modern aircraft; however, because the unsteady flows of the cavity would cause dangerous store separation and intense aerodynamic noise, the leading-edge spoiler is an easy and efficient passive flow-control method. The flow control of the leading-edge flat spoiler before the cavity of a low-aspect-ratio flying-wing aircraft is investigated based on numerical simulation. Numerical results show that the leading-edge flat spoiler completely changes the cavity flow; it obviously lifts up the shear layer and reduces the pressure inside the cavity. For the

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Kumar, D., and J. L. Stollery. "Hypersonic control flap effectiveness." Aeronautical Journal 100, no. 996 (1996): 197–208. http://dx.doi.org/10.1017/s0001924000067154.

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SummaryThe effects of flap deflection, configuration incidence and leading edge bluntness on boundary layer separation and transition have been studied experimentally. A quasi two-dimensional flat plate equipped with a full span trailing edge control flap has been employed for these tests.The studies have been carried out in a hypersonic gun tunnel at M∞ = 8·2 and Re∞/cm = 9·0 × 104. The flap deflection angles studied were in the range 0° ≤ β ≤ 30°. The incidence range was from zero to α = 10° (positive α is nose down). Leading edge bluntness effects were simulated by the introduction of a hem

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Niu, Jianping, Juanmian Lei, and Tianyu Lu. "Numerical research on the effect of variable droop leading-edge on oscillating NACA 0012 airfoil dynamic stall." Aerospace Science and Technology 72 (January 2018): 476–85. http://dx.doi.org/10.1016/j.ast.2017.11.030.

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ERTURK, ERCAN, and THOMAS C. CORKE. "Boundary layer leading-edge receptivity to sound at incidence angles." Journal of Fluid Mechanics 444 (September 25, 2001): 383–407. http://dx.doi.org/10.1017/s0022112001005456.

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The leading-edge receptivity to acoustic waves of two-dimensional parabolic bodies was investigated using a spatial solution of the Navier–Stokes equations in vorticity/streamfunction form in parabolic coordinates. The free stream is composed of a uniform flow with a superposed periodic velocity fluctuation of small amplitude. The method follows that of Haddad & Corke (1998) in which the solution for the basic flow and linearized perturbation flow are solved separately. We primarily investigated the effect of frequency and angle of incidence (−180° [les ] α2 [les ] 180°) of the acoustic wa

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Dancuo, Zorana, Ivan Kostic, Olivera Kostic, Aleksandar Bengin, and Goran Vorotovic. "Initial development of the hybrid semielliptical-dolphin airfoil." Thermal Science, no. 00 (2021): 234. http://dx.doi.org/10.2298/tsci210515234d.

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Iosif Taposu has formulated a mathematical model and generated a family of airfoils whose geometry resembles the dolphin shape. These airfoils are characterized by a sharp leading edge and experiments have proven that they can achieve better aerodynamic characteristics at very high angles of attack than certain classical airfoils, with the nose geometry inclined downwards. On the other hand, they have not been applied to any commercial general aviation aircraft. The authors of this paper have been motivated to compare the aerodynamic characteristics of widely used NACA 2415 airfoil with Taposu

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ZHONG, XIAOLIN. "Leading-edge receptivity to free-stream disturbance waves for hypersonic flow over a parabola." Journal of Fluid Mechanics 441 (August 15, 2001): 315–67. http://dx.doi.org/10.1017/s0022112001004918.

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The receptivity of hypersonic boundary layers to free-stream disturbances, which is the process of environmental disturbances initially entering the boundary layers and generating disturbance waves, is altered considerably by the presence of bow shocks in hypersonic flow fields. This paper presents a numerical simulation study of the generation of boundary layer disturbance waves due to free-stream waves, for a two-dimensional Mach 15 viscous flow over a parabola. Both steady and unsteady flow solutions of the receptivity problem are obtained by computing the full Navier–Stokes equations using

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TURNER, M. R., and P. W. HAMMERTON. "Analysis of the unstable Tollmien–Schlichting mode on bodies with a rounded leading edge using the parabolized stability equation." Journal of Fluid Mechanics 623 (March 6, 2009): 167–85. http://dx.doi.org/10.1017/s0022112008005260.

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The interaction between free-stream disturbances and the boundary layer on a body with a rounded leading edge is considered in this paper. A method which incorporates calculations using the parabolized stability equation in the Orr–Sommerfeld region, along with an upstream boundary condition derived from asymptotic theory in the vicinity of the leading edge, is generalized to bodies with an inviscid slip velocity which tends to a constant far downstream. We present results for the position of the lower branch neutral stability point and the magnitude of the unstable Tollmien–Schlichting (T-S)

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Ayton, Lorna J., and N. Peake. "Interaction of turbulence with the leading-edge stagnation point of a thin aerofoil." Journal of Fluid Mechanics 798 (June 3, 2016): 436–56. http://dx.doi.org/10.1017/jfm.2016.326.

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An asymptotic model is constructed to analyse the interaction of turbulence generated far upstream with a thin elliptic-nosed solid body in uniform flow. The leading-edge stagnation point causes significant deformation of incident vorticity, and hence our analysis focuses on the region of size scaling with the nose radius close to the stagnation point. Rapid distortion theory is used to separate the flow field generated by a single unsteady gust perturbation into a convective non-acoustic part, containing the evolution of the upstream vortical disturbance, and an acoustic part generated by the

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Taslim, M. E., and A. Khanicheh. "Experimental and Numerical Study of Impingement on an Airfoil Leading Edge With and Without Showerhead and Gill Film Holes." Journal of Turbomachinery 128, no. 2 (2005): 310–20. http://dx.doi.org/10.1115/1.2137742.

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This experimental investigation deals with impingement on the leading edge of an airfoil with and without showerhead film holes and its effects on heat transfer coefficients on the airfoil nose area as well as the pressure and suction side areas. a comparison between the experimental and numerical results are also made. the tests were run for a range of flow conditions pertinent to common practice and at an elevated range of jet Reynolds numbers (8000–48,000). The major conclusions of this study were: (a) The presence of showerhead film holes along the leading edge enhances the internal imping

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