Interaction of Three-Dimensional Disturbances with the Flow Around a Two-Element High-Lift Airfoil

2015 ◽  
pp. 55-73
Author(s):  
Simon Klein ◽  
Peter Scholz ◽  
Rolf Radespiel
Keyword(s):  
Three Dimensional ◽  
High Lift

scholarly journals Aeroelastic behaviour of a wing with over-the-wing mounted UHBR engine

2020 ◽  
Vol 11 (4) ◽  
pp. 1045-1055 ◽  
Author(s):  
N. Neuert ◽  
D. Dinkler
Keyword(s):  
Three Dimensional ◽  
High Lift ◽  
Reduced Order ◽  
Aerodynamic Loads ◽  
Flow Simulations ◽  
Dimensional Effects ◽  
Line Theory ◽  
Lifting Line ◽  
Bypass Ratio ◽  
Lifting Line Theory

Abstract The aeroelastic behaviour of a wing with an over-the-wing pylon-mounted ultra-high bypass ratio engine and high-lift devices is studied with a reduced-order model. Wing, pylon and engine structures are reduced separately using the modal approach and described by their natural frequencies and modes. The characteristic aerodynamic loads are investigated with steady and unsteady flow simulations of a two-dimensional profile section. These results indicate possible heave instabilities at strongly negative angles of attack. Three-dimensional effects are taken into account using an adapted lifting line theory according to Prandtl. Due to high circulations resulting from the high-lift systems, the effective angles of attack are in the range of the potential instabilities. The substructures and aerodynamic loads are coupled in modal space. For the wing without three-dimensional effects, the bending instability occurs at the corresponding negative angles of attack. Even though there is potential for improvement, including the three-dimensional effects shifts the endagered area to possible operation points.

Large-Scale Parallel Unstructured Mesh Computations for Three-Dimensional High-Lift Analysis

1999 ◽  
Vol 36 (6) ◽  
pp. 987-998 ◽  
Author(s):  
D. J. Mavriplis ◽  
S. Pirzadeh
Keyword(s):  
Large Scale ◽  
Unstructured Mesh ◽  
Three Dimensional ◽  
High Lift

Control of Separated Boundary-Layer on Subsonic Airfoil Using Vortex Generator Jet Devices

2006 ◽  
Author(s):  
A. Kourta ◽  
G. Petit ◽  
J. C. Courty ◽  
J. P. Rosenblum
Keyword(s):  
Boundary Layer ◽  
Friction Coefficient ◽  
Skin Friction ◽  
Three Dimensional ◽  
Vortex Generator ◽  
Leading Edge ◽  
Skin Friction Coefficient ◽  
Synthetic Jets ◽  
High Lift ◽  
Longitudinal Vortices

The control of subsonic high lift induced separation on airfoil may improve the flight envelope of current aircraft or even simplify the complex and heavy high-lift devices on commercial airframes. Until now, synthetic jets have proved a really interesting efficiency to delay or remove even leading-edge located separated areas on high-lift configuration but are not efficient for real scale aircrafts. In case of pressure-like separation (i.e. from trailing-edge), synthetic jets can be replaced by so the called “Vortex Generator Jets” which create strong longitudinal vortices that increase mixing in inner boundary layer and consequently the skin friction coefficient is increased to prevent separation. In this study, numerical simulations were undertaken on a generic three dimensional flat plate in order to quantify the effect of the longitudinal vortices on the natural skin friction coefficient. Both counter and co-rotative devices were tested at different exhaust velocities and distances between each others. Finally co-rotative vortex generators jets were tested on a three dimensional generic airfoil ONERA D. Results show a delay of the separation occurence but this solution does not seem to be as robust as synthetic jets. The study of jets spacing with respect to the efficiency of the devices shows a maximum for a given ratio of spacing to exhaust velocity.

Parametric Optimization of a High-Lift Turbine Vane

2004 ◽  
Author(s):  
Andrea Arnone ◽  
Duccio Bonaiuti ◽  
Antonio Focacci ◽  
Roberto Pacciani ◽  
Alberto Scotti Del Greco ◽  
...  
Keyword(s):  
Parametric Design ◽  
Thickness Distribution ◽  
Three Dimensional ◽  
Optimization Procedure ◽  
Design Tool ◽  
Optimization Techniques ◽  
High Lift ◽  
Profile Losses ◽  
Turbine Vane ◽  
Cfd Analyses

Numerical optimization techniques are increasingly used in the aerodynamic design of turbomachine blades. In the present paper, an existing three-dimensional high-lift turbine cascade was redesigned by means of CFD analyses and optimization techniques, based on the blade geometrical parameterization. A new parametric design tool was developed for this purpose. Blade geometry was handled in a fully three dimensional way, using Be´zier curves and surfaces for both camber-surface and thickness distribution. In the optimization procedure different techniques were adopted: a Genetic Algorithm (GA) strategy made it possible to considerably reduce two-dimensional profile losses, while the optimal stacking line was found based on a successive Design of Experiments (DOE) analysis. As a result, a new high-lift blade with higher performance was obtained; in addition, the effect of hub/tip leaning was presented and discussed.

High-Lift Aerodynamics Design for Large Civil Aircraft in Fudan University

2011 ◽  
Vol 52-54 ◽  
pp. 1382-1387
Author(s):  
Gang Sun ◽  
Kang Le Xu ◽  
Ying Chun Chen
Keyword(s):  
Cfd Simulation ◽  
Three Dimensional ◽  
The Self ◽  
Design Team ◽  
Cfd Simulations ◽  
High Lift ◽  
Design Efficiency ◽  
Geometry Modeling ◽  
Civil Aircraft ◽  
Calculation Software

Part of work on CFD simulations by the high-lift system design team in Fudan university for large civil aircraft is presented. The research on CFD simulation of the high-lift systems and some concepts and experience in three-dimensional geometry modeling are also presented, which are done on the self-developed platform of high-lift device aerodynamic calculation software and programs. For which, the design efficiency is substantially improved.

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