scholarly journals Aerodynamic Analysis on Proton Preve by Experimental

2015 ◽  
Vol 773-774 ◽  
pp. 575-579
Author(s):  
Mohamad Nor Musa ◽  
Samion Syahrullail ◽  
Fairuz Zainal Abidin
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Wind Tunnel ◽  
Shape Optimization ◽  
Air Flow ◽  
Literature Reviews ◽  
Air Speed ◽  
Vehicle Shape ◽  
Low Speed Wind Tunnel ◽  
The Relationship

The purpose of this study is to determine the coefficient drag, CD of the Proton PREVẾ by experimental method using Low Speed Wind Tunnel. All the relevant data are collected through the literature reviews from books and journals. First, the basic thing in aerodynamic is studied. There are two things are concern when studies aerodynamics. They were air flow and vehicle shape which we regard as aerodynamics factor that determine aerodynamic of the vehicle. Fundamental of air flow and vehicle shape is reviewed includes the relationship between air speed with pressure, boundary layer, Reynolds number, drag, lift drag and shape optimization. Wind tunnel is also studied before the experiment. Five selected speed were been tasted during the experiment to determine the CD value.

scholarly journals A Detailed Study: CFD Analysis of NACA 0012 at Varying Angles of Attack

2021 ◽  
Vol 9 (VII) ◽  
pp. 2330-2336
Author(s):  
Vani Sadadiwala
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Wind Tunnel ◽  
Computational Analysis ◽  
Cfd Analysis ◽  
Reliable Source ◽  
Relationship Of ◽  
Naca 0012 ◽  
The Relationship ◽  
Symmetric Profile

This work reflects the study and detailed analysis of NACA 0012 airfoil at different angles of attack with a constant value of Reynolds Number. The geometrical designing of the airfoil is done using FreeCad and the computational analysis is carried out using Simflow 4.0- OpenFoam Interface. The analysis is fully based upon the concepts of FEM and CFD. The velocity is kept constant with various angles of attack. CFD methods are reliable source of analysis and hence can be replaced with the experimental wind tunnel methods. Boundary layer approaches were taken into consideration using the meshing techniques. The main purpose of this work is to study the symmetric profile of NACA 0012 with varying angles and the behaviour of 0012 at specific conditions. At the end, various graphs are plotted depicting the relationship of Angle of Attack with other dimensionless quantities.

scholarly journals Airfoil profile optimization of an air suction equipment with an air duct

2015 ◽  
Vol 19 (4) ◽  
pp. 1217-1222 ◽  
Author(s):  
Li Qiu ◽  
Rui Wang ◽  
Xiao-Dong Chen ◽  
De-Peng Wang
Keyword(s):  
Boundary Layer ◽  
Wind Tunnel ◽  
Critical Angle ◽  
Air Flow ◽  
Operation Mode ◽  
Wind Tunnel Test ◽  
Flow Fields ◽  
External Flow ◽  
Air Speed ◽  
Profile Optimization

On the basis of boundary layer with the airfoil profile, this research attempts to investigate the effect of the angle of spread of the winged air suction equipment on the efficiency of operation. The application of Fluent with the split-middle method under the identical operation mode is expected to optimize the spread angle. The investigated airfoil profile is NACA6413, of which the restrictions on the critical angle of spread suggested in literature will be overcome through the interactions between the internal and external flow fields. As a result, the air speed might increase. The wind tunnel test employed in this research offers the solid evidences to support this hypothesis. The test demonstrates that when the angle of spread is larger than 12?, the effect of accelerating the air flow is still observable. Following the optimization, the air suction effect of the equipment would be optimal when its angle of spread reached 30?.

Air flow quality analysis of an open-circuit boundary layer wind tunnel and comparison with a closed-circuit wind tunnel

2020 ◽  
Vol 32 (12) ◽  
pp. 125120
Author(s):  
María Jiménez-Portaz ◽  
Luca Chiapponi ◽  
María Clavero ◽  
Miguel A. Losada
Keyword(s):  
Boundary Layer ◽  
Wind Tunnel ◽  
Air Flow ◽  
Open Circuit ◽  
Closed Circuit ◽  
Quality Analysis ◽  
Flow Quality

Aerodynamic Shape Optimization of Shenzhen Kingkey Financial Tower

2011 ◽  
Vol 71-78 ◽  
pp. 4005-4008
Author(s):  
Bi Qing Shi ◽  
Zhuang Ning Xie ◽  
Zhen Hua Ni
Keyword(s):  
Boundary Layer ◽  
Wind Tunnel ◽  
Shape Optimization ◽  
Structural Design ◽  
Wind Load ◽  
Experimental Results ◽  
Aerodynamic Shape Optimization ◽  
Aerodynamic Shape ◽  
High Rise ◽  
Building Shape

A study of approach aerodynamic shape optimization of a high-rise building, Shenzhen Kingkey financial tower, was performed in a boundary layer wind tunnel at Shantou University. Building shape has significant effects on the wind load forcing on the structure. The peak overturning moments about x-axis and the peak accelerations at the top of building are presented in this paper. Compared with the experimental results, one case is considered as the optimal case for structural design.

Some Observations on dr. Coleman's Comments

1957 ◽  
Vol 61 (557) ◽  
pp. 361-361
Author(s):  
G. V. Lachmann
Keyword(s):  
Boundary Layer ◽  
Surface Roughness ◽  
Reynolds Number ◽  
Wind Tunnel ◽  
Short Distance ◽  
Wind Tunnel Tests ◽  
Theoretical Methods ◽  
Unit Reynolds Number ◽  
Research Department ◽  
Boundary Layer Profile

The method referred to in Dr. Coleman's notes was developed with the collaboration of my colleague Mr. J. B. Edwards of Handley Page Research Department. The purpose was to obtain a rational estimate of suction quantities and suction distribution, linked up with measurements of boundary layer profiles and suction quantities on wind tunnel models, and also to assess the effect of a certain degree of roughness of the order to be expected on actual wings. Existing theoretical methods ignore roughness which, however, is a most important parameter not only in wind tunnel tests, but also in flight at higher values of the unit Reynolds number; surface roughness obviously limits the intensity of suction which can be applied at a spanwise suction strip.It was intuitively assumed that the removal of fluid by suction was equivalent to cutting off the lower portion of the boundary layer profile at the upstream edge of the suction strip and that a rapid re-adjustment of the boundary layer profile within a short distance took place.

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