Validation of Numerical Optimization of High-Lift Multi-Element Airfoils Based on Navier-Stokes-Equations

2002 ◽  
Author(s):  
Jochen Wild
Keyword(s):  
Numerical Optimization ◽  
Stokes Equations ◽  
Navier Stokes ◽  
High Lift ◽  
Navier Stokes Equations

High-lift design optimization using Navier-Stokes equations

1996 ◽  
Vol 33 (3) ◽  
pp. 499-504 ◽  
Author(s):  
S. Eyi ◽  
K. D. Lee ◽  
S. E. Rogers ◽  
D. Kwak
Keyword(s):  
Design Optimization ◽  
Stokes Equations ◽  
Navier Stokes ◽  
High Lift ◽  
Navier Stokes Equations

Multi-element high-lift design using the Navier-Stokes equations

1996 ◽  
Author(s):  
S. Eyi ◽  
K. Chand ◽  
K. Lee ◽  
S. Rogers ◽  
D. Kwak
Keyword(s):  
Stokes Equations ◽  
Navier Stokes ◽  
High Lift ◽  
Navier Stokes Equations

Research of Measurement Method of Two Dimensional Configuration Drag Test in Wind Tunnel in Case of High Lift

2011 ◽  
Vol 301-303 ◽  
pp. 671-676
Author(s):  
Yu Qin Jiao ◽  
Xi Ping Chen ◽  
Zhen Li Zhi
Keyword(s):  
Wind Tunnel ◽  
Stokes Equations ◽  
Wind Tunnel Test ◽  
Flow Characteristics ◽  
Aerodynamic Performance ◽  
Wake Flow ◽  
Navier Stokes ◽  
Two Dimensional ◽  
High Lift ◽  
Navier Stokes Equations

Computational fluid dynamics and wind tunnel test are two main technical means to examine the aerodynamic performance of airfoil and two-dimensional(2-D) configuration. Two dimensional wind tunnel tests use commonly wake flow field measurement to integrate for drag of airfoil or two-dimensional configuration, but the integral formulas are based on certain assumptions and of certain bounds of application. In this paper, based on Navier-Stokes equations numerical simulation and two dimensional wind tunnel testing, the drag measuring technique for high lift configuration in low speed wind tunnel is researched. Navier-Stokes equations is solved for the flow around a multi-element airfoil, the wake flow characteristics behind the multi-element airfoil and the assumptions for conventional drag measuring method are analyzed, then a new more precise drag formula for two dimensional wind tunnel test is put forward; Based on the simulation results of multi-element airfoil flow, it’s aerodynamic performance is obtained respectively by integrating the surface pressure and friction drag, and computing with the information of wake flow according to conventional and newly proposed drag calculation formulas, and the three results are compared to verify the accuracy of the new drag formula; The wind tunnel test is carried out to ascertain the accuracy of the new drag formula. It is shown from the results that in the high-lift case the conventional drag formula with the wake information is of many limitations and must be improved, and the new drag formula presented in this paper is more accurate because of consideration of the wake flow characteristics of airfoil or two-dimensional configuration.

Progress toward CFD for full flight envelope

2005 ◽  
Vol 109 (1100) ◽  
pp. 451-460 ◽  
Author(s):  
E. N. Tinoco ◽  
D. R. Bogue ◽  
T-J. Kao ◽  
N. J. Yu ◽  
P. Li ◽  
...  
Keyword(s):  
High Speed ◽  
Large Scale ◽  
Stokes Equations ◽  
Vortex Generator ◽  
Navier Stokes ◽  
High Lift ◽  
Navier Stokes Equations ◽  
Stability And Control ◽  
Flight Envelope ◽  
And Control

Abstract The value of computational fluid dynamics, CFD, delivered to date has mainly been related to its application to high-speed cruise design. To increase its applicability CFD must apply to the full flight envelope frequently characterised by large regions of separated flows. These flows are encountered by transport aircraft at low speed with deployed high lift devices, at their structural design loads conditions, or subjected to in-flight upsets that expose them to speed and/or angle-of-attack conditions outside the envelope of normal flight conditions to name a few. Such flows can only be characterised by the Navier-Stokes equations. This paper will report the progress toward CFD for full flight envelope. The CFD methods in use at Boeing will be described. Examples presented will address high-lift, loads and stability and control concerns including Reynolds scaling from wind tunnel to flight, vortex generator simulation, spoiler and horizontal tail effectiveness. In general, results shown are in ‘good enough’ agreement with experimental data. Deficiencies and the need for further algorithm and process improvement are noted. The need for automation to enable the large scale use of CFD will also be discussed.

Computational Investigation of the Slat Blowing Control for High-Lift Airfoil

2011 ◽  
Vol 138-139 ◽  
pp. 223-228
Author(s):  
Pei Qing Liu ◽  
Yan Xiang Cui ◽  
Liang Wang ◽  
Qiu Lin Qu
Keyword(s):  
Stokes Equations ◽  
Lift Coefficient ◽  
Lower Surface ◽  
Navier Stokes ◽  
Computational Investigation ◽  
High Lift ◽  
Navier Stokes Equations ◽  
Flow Rates ◽  
Computational Fluid Dynamics Cfd ◽  
A New Technique

Based on the characteristics of blowing control, a new technique was put forward to weaken slat cove separation and reduce noise. The effect of the slat blowing control on lift performance, the flow field and noise with a three-element high lift aerofoil was investigated by using the computational fluid dynamics (CFD) code of Fluent and the Reynolds-averaged Navier-Stokes equations. The blowing apertures were set on the lower surface of the slat. By using the slat blowing technique, the slat cove separation can be controlled efficiently and the lift coefficient increased. The aerodynamic performance varies with different blowing flow rates and angles of attack.

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