Investigation of Icing Effects on Aerodynamic Performance for the High-Lift Configuration of Civil Aircraft

2021 ◽  
Author(s):  
Qimin Wang ◽  
Meihong Zhang ◽  
Jiaming Luo ◽  
Longqian Zheng
Keyword(s):  
Aerodynamic Performance ◽  
High Lift ◽  
Civil Aircraft

scholarly journals Unsteady experimental and numerical investigation of aerodynamic performance in ultra-high-lift LPT

2020 ◽  
Vol 33 (5) ◽  
pp. 1421-1432 ◽  
Author(s):  
Xiao QU ◽  
Yanfeng ZHANG ◽  
Xingen LU ◽  
Junqiang ZHU
Keyword(s):  
Numerical Investigation ◽  
Aerodynamic Performance ◽  
High Lift

scholarly journals Investigation of High Lift Force Generation of Dragonfly Wing by a Novel Advanced Mode in Hover

Fluids ◽  
2020 ◽  
Vol 5 (2) ◽  
pp. 59
Author(s):  
Xiaohui Su ◽  
Kaixuan Zhang ◽  
Juan Zheng ◽  
Yong Zhao ◽  
Ruiqi Han ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Energy Expenditure ◽  
Lift Force ◽  
Lift Coefficient ◽  
Aerodynamic Performance ◽  
Dynamic Stall ◽  
Force Generation ◽  
High Lift ◽  
Dragonfly Wing ◽  
Symmetrical Mode

In the paper, a novel flapping mode is presented that can generate high lift force by a dragonfly wing in hover. The new mode, named partial advanced mode (PAM), starts pitching earlier than symmetric rotation during the downstroke cycle of the hovering motion. As a result, high lift force can be generated due to rapid pitching coupling with high flapping velocity in the stroke plane. Aerodynamic performance of the new mode is investigated thoroughly using numerical simulation. The results obtained show that the period-averaged lift coefficient, CL, increases up to 16% compared with that of the traditional symmetrical mode when an earlier pitching time is set to 8% of the flapping period. The reason for the high lift force generation mechanism is explained in detail using not only force investigation, but also by analyzing vortices produced around the wing. The proposed PAM is believed to lengthen the dynamic stall mechanism and enhance the LEV generated during the downstroke. The improvement of lift force could be considered as a result of a combination of the dynamic stall mechanism and rapid pitch mechanism. Finally, the energy expenditure of the new mode is also analyzed.

scholarly journals High-fidelity simulations of unsteady civil aircraft aerodynamics: stakes and perspectives. Application of zonal detached eddy simulation

2014 ◽  
Vol 372 (2022) ◽  
pp. 20130325 ◽  
Author(s):  
Sébastien Deck ◽  
Fabien Gand ◽  
Vincent Brunet ◽  
Saloua Ben Khelil
Keyword(s):  
Turbulent Flows ◽  
Hybrid Methods ◽  
Landing Gear ◽  
High Fidelity ◽  
Detached Eddy Simulation ◽  
High Lift ◽  
Eddy Simulation ◽  
Civil Aircraft ◽  
Aircraft Aerodynamics ◽  
Transonic Buffet

This paper provides an up-to-date survey of the use of zonal detached eddy simulations (ZDES) for unsteady civil aircraft applications as a reflection on the stakes and perspectives of the use of hybrid methods in the framework of industrial aerodynamics. The issue of zonal or non-zonal treatment of turbulent flows for engineering applications is discussed. The ZDES method used in this article and based on a fluid problem-dependent zonalization is briefly presented. Some recent landmark achievements for conditions all over the flight envelope are presented, including low-speed (aeroacoustics of high-lift devices and landing gear), cruising (engine–airframe interactions), propulsive jets and off-design (transonic buffet and dive manoeuvres) applications. The implications of such results and remaining challenges in a more global framework are further discussed.

1305 Aerodynamic Design Optimization of Low Noise High-Lift Airfoil for Civil Aircraft

2013 ◽  
Vol 2013.23 (0) ◽  
pp. _1305-1_-_1305-10_
Author(s):  
Ryu SHINOMIYA ◽  
Masahiro KANAZAKI ◽  
Mitsuhiro MURAYAMA ◽  
Kazuomi YAMAMOTO
Keyword(s):  
Design Optimization ◽  
Low Noise ◽  
Aerodynamic Design ◽  
High Lift ◽  
Aerodynamic Design Optimization ◽  
Civil Aircraft

The Effect of Belly-Flap on Aerodynamic Performance of Blended Wing Body Civil Aircraft

2013 ◽  
Vol 378 ◽  
pp. 69-73
Author(s):  
Chen Fang Cai ◽  
Yong Ming Qin ◽  
Jiang Hao Wu
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Angle Of Attack ◽  
Aerodynamic Performance ◽  
Design Parameters ◽  
Flight Safety ◽  
Optimized Design ◽  
Flight Condition ◽  
Civil Aircraft ◽  
Blended Wing Body

The effect of Belly-flap on aerodynamic performance of BWB civil aircraft are investigated in take-off and landing by computational fluid dynamics. And the overload of BWB with Belly-flap also is calculated in the same flight condition. Six parameters are discussed as design parameters of the Belly flap. It is shown that the proper combination of design parameters of Belly-flap can increase the maximum of lift and reduce the angle of attack and nose down moment to improve the flight safety in take-off and landing. When the aircraft with Belly-flap encounters the gust, the maximum overload is very close to 2.5 which are requested by FAR. It is suggested the optimized design of Belly-flap should be done if the Belly-flap is applied in BWB civil aircraft.

Esso Energy Award Lecture, 1987 - Application of aerodynamic research and development to civil aircraft wing design

1988 ◽  
Vol 416 (1850) ◽  
pp. 43-62
Keyword(s):  
Technological Progress ◽  
Computational Fluid Mechanics ◽  
Aerodynamic Design ◽  
Wing Design ◽  
High Lift ◽  
Business Jet ◽  
Civil Aircraft ◽  
Research Programmes ◽  
The Government

In the late 1950s the aerodynamicists at what is now the Hatfield site of British Aerospace accepted the challenge and met British European Airways’ demand for a 600 m. p. h. ( ca . 966 km h -1 ) short-haul jet airliner (the Trident). The experience and organization resulting from that project was the cornerstone on which the subsequent success story of civil wing design has been built. The substantial advances in efficiency achieved by the Hatfield team in the following designs for the 125 Business Jet, the 146 Feederliner and for the Airbus Industrie family of Wide-Body Mainline aircraft, has been supported by research programmes in the government establishments and universities as well as industry itself. Each project had its individual demands for fuel economy, high lift capability and structural efficiency, with commercial competition continually driving technological progress. The major highlights and achievements of the aerodynamic development programmes for these projects are reviewed. Turning to the present, the Hatfield team are currently working on the aerodynamic design for the combined Airbus A330/340 project. Technological progress continues apace with major investment in computational fluid mechanics, but the still essential role of experimental test techniques and facilities is emphasized.

Aerodynamic Performance of a Very High Lift Low Pressure Turbine Airfoil (T106C) at Low Reynolds and High Mach Number With Effect of Free Stream Turbulence Intensity

2012 ◽  
Vol 134 (6) ◽  
Author(s):  
Jan Michálek ◽  
Michelangelo Monaldi ◽  
Tony Arts
Keyword(s):  
Mach Number ◽  
Turbulence Intensity ◽  
Free Stream ◽  
Separated Flow ◽  
Aerodynamic Performance ◽  
Flow Transition ◽  
High Lift ◽  
Free Stream Turbulence ◽  
Low Pressure Turbine ◽  
Very High

A detailed experimental analysis of the effects of the Reynolds number and free-stream turbulence intensity on the aerodynamic performance of a very high-lift, mid-loaded low-pressure turbine blade (T106C) is presented in this paper. The study was carried out on a large scale linear cascade in the VKI S1/C high-speed wind tunnel, operating at high exit Mach number (0.65) with a range of low Reynolds numbers (80,000–160,000) and three levels of free-stream turbulence intensity (0.8–3.2%). In the first part of the paper, the overall aerodynamic performance of the airfoil is presented, based on mid-span measurements performed by means of static pressure taps, hot-film sensors and a five-hole probe traversing downstream of the cascade. Some specific features of separated flow transition are also discussed for selected cases. The second part presents the analysis of the results in terms of correlations derived for the characteristic points of boundary layer separation and transition. A comparison with some previously published prediction models is shown. The large variety of boundary conditions provides a unique database for validating codes dealing with separated flow transition in turbomachinery.

scholarly journals Computational Analysis of High Lift Generating Airfoils for Diffuser Augmented Wind Turbines

2019 ◽  
Author(s):  
Anhad Singh Bajaj ◽  
Jayakrishnan Radhakrishnan ◽  
Raahil Nayak
Keyword(s):  
Fluid Dynamics ◽  
Computational Analysis ◽  
Aerodynamic Performance ◽  
Rotor Blades ◽  
Navier Stokes ◽  
Cfd Analysis ◽  
High Lift ◽  
Actuator Disk ◽  
Computational Fluid Dynamics Cfd ◽  
Flow Through

The present study aims to asses the aerodynamic performance of Diffuser Augmented Wind Turbine (DAWT) using high lift generating airfoils in the construction of the shroud/diffuser. The study is a Computational Fluid Dynamics (CFD) analysis which is carried out using Reynolds Averaged Navier-Stokes (RANS) simulations. The flow across the duct and rotor blades, which are modeled as an actuator disk (AD), is analyzed. Various High-Lift generating airfoils and their geometries were taken into consideration and analyzed with additional geometric modifications, such as a flange, to improve flow through the AD and increase the augmentation factor

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