Abstract
Numerical and experimental study to evaluate aerodynamic characteristics in supersonic ow over a double wedge airfoil is carried out using Fluent software and a supersonic wind tunnel, respectively. The Schlieren visualization method was also used to develop the experimental step of this study. The supersonic wind tunnel reached a proximately a Mach number of 1.8. The result got showed oblique shock waves visualization on double-wedge airfoil and the numerical simulation, the flow behavior as function of Mach number, pressure, temperature and density in the flow field on the computational model. The simulation allowed to observe the shock wave and the expansion fan in the leading and tailing edge of double-wedge airfoil. From the numerical and experimental comparison, an agreement at the shock wave angle and Mach number was observed, with a difference about 1.17% from the experimental results.
Highlights
It is very relevant to understand the compressible fluid ow and some phenomenon presented in compressible ow turbomachines, blades cascades, aeronautics, aerodynamics and in any fluid motion where exist high ow velocities
Numerical and experimental study to evaluate aerodynamic characteristics in supersonic ow over a double wedge airfoil is carried out using Fluent software and a supersonic wind tunnel, respectively
In Ref. [8] a study on the aerodynamic response of double wedge airfoil in supersonic ow with free stream Mach number is presented, they varied the angle of attack and thickness to chord ratio and performed numerical simulation using adaptive grids on a Comsol Multi-physics model
Summary
It is very relevant to understand the compressible fluid ow and some phenomenon presented in compressible ow turbomachines, blades cascades, aeronautics, aerodynamics and in any fluid motion where exist high ow velocities. [9] an analysis of the incompressible Navier-Stokes and elastodynamics equations in the Lagrangian- Eulerian framework is presented They developed a numerical simulation of the fluid structure interaction effect on a double wedge airfoil. This paper presents a numerical simulation and experimental study about oblique shockwave on symmetrical double-wedge airfoil by mean of Mach number, pressure, temperature and density behavior. The main purpose of this study is to evaluate oblique shock waves characteristics on a double-wedge airfoil by comparing their numerical behaviors and simulation effects with corresponding experimental testing.
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