Airfoil Flow Analysis of a High Lift System with the Vortex Blob Method

2011 ◽  
Author(s):  
Carmine Golia ◽  
Antonio Viviani
Keyword(s):  
Flow Analysis ◽  
High Lift ◽  
Airfoil Flow

Flow Analysis of the DLR-F11 High-Lift Model Using the Galatea-I Code

2018 ◽  
Vol 55 (1) ◽  
pp. 355-372
Author(s):  
Sotirios S. Sarakinos ◽  
Georgios N. Lygidakis ◽  
Ioannis K. Nikolos
Keyword(s):  
Flow Analysis ◽  
High Lift

A Zone-Interaction Method for the Outer Flow Analysis of a Separated Airfoil

1980 ◽  
Vol 24 (02) ◽  
pp. 123-127
Author(s):  
James W. White
Keyword(s):  
Solution Method ◽  
Pressure Field ◽  
Flow Analysis ◽  
Separated Flow ◽  
Outer Flow ◽  
Free Streamlines ◽  
Principal Value ◽  
Airfoil Flow ◽  
Parallel Strips ◽  
Massive Separation

The pressure distribution over a subsonic airfoil experiencing massive separation is analyzed by a zonal modeling approach. Important physics are included in the mathematical description of each zone, and the zones are allowed to interact until convergence of the overall flow is obtained. The separated region is modeled as a zone of uniform pressure, the magnitude of which is determined by the solution method. The elliptic effect of the separated flow on the pressure field over the airfoil is included by bounding the stalled zone by two free streamlines which are iteratively located. Influence of the wake on the airfoil flow is modeled by two parallel strips which allow the subambient pressure in the stalled zone to adjust continuously black to freestream conditions. A Cauchy principal-value integral equation is used to compute the potential flow with no restrictions on the airfoil contour. Unlike most complex-variable methods, no mappings are required and the numerical solution is obtained entirely in the physical (Z) plane.

The Effects of Wake Mixing on Compressor Aerodynamics

1991 ◽  
Vol 113 (4) ◽  
pp. 600-607 ◽  
Author(s):  
R. P. Dring ◽  
D. A. Spear
Keyword(s):  
Experimental Data ◽  
Secondary Flow ◽  
Flow Analysis ◽  
Strong Impact ◽  
Corner Separation ◽  
Pressure Distributions ◽  
Compressor Aerodynamics ◽  
Airfoil Flow

A methodology based on wake mixing has been developed that enables more accurate predictions of compressor airfoil pressure distributions when the airfoil is operating downstream of an airfoil row that has strong wakes. The methodology has an impact on throughflow analysis, on airfoil-to-airfoil flow analysis, and on the interpretation of experimental data. It is demonstrated that the flow in the endwall region is particularly sensitive to mixing due to the strong wakes caused by the secondary flow and corner separation that commonly occur in this region. It is also demonstrated that wake mixing can have a strong impact on both airfoil incidence and deviation as well as on loading. Differences of up to 13 deg and 30 percent in loading are demonstrated.

Viscous Flow Analysis of a Twin-engine Commercial Transport Aircraft in High Lift Landing Configuration

2011 ◽  
Author(s):  
Anutosh Moitra ◽  
Rajesh Ranjan ◽  
Abhishek Khare ◽  
Stimit Shah ◽  
Kishor Nikam
Keyword(s):  
Viscous Flow ◽  
Flow Analysis ◽  
High Lift ◽  
Transport Aircraft

Visualization of Flow Field and Wake over Clean and Under-Loaded Wings

2014 ◽  
Vol 629 ◽  
pp. 24-29
Author(s):  
Hussain H. Al-Kayiem
Keyword(s):  
Numerical Simulation ◽  
Reynolds Number ◽  
Flow Field ◽  
Visualization Technique ◽  
High Lift ◽  
Laminar To Turbulent Transition ◽  
Turbulent Transition ◽  
Wake Interaction ◽  
Airfoil Flow ◽  
External Body

Experimental details of the flow field and wake over airfoils and 2-D wings are time and cost consumption. In this study, the flow visualization technique was adopted to investigate the flow field surrounding NACA4412 airfoil. The investigations were carried out in smoke tunnel, operating at low Reynolds number in a range of 105. The airfoil was tested in two operational cases: first as clean wing and the second as under-loaded wing by attached missile model. The experiments were conducted at various angles of attack as 00, 50,100, 150and 200. It was found that the under-load of external body under the wing is influencing the flow structure over the wing. Also, the wake after the external body is swirling, leading to very complicated wake interaction. The results from the work can support the numerical simulation and the prediction of the laminar to turbulent transition and the separation and wake interaction of high lift airfoil flow fields.

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