![]() The static pressure used to compute the Mach number, temperature and density in the wind tunnel test section. On the other hand, with the aim to know the flow behavior in the double-wedge airfoil, an experiment was realized at 1.6 Mach number and the static pressure data were registered at this condition. In Figure 1, circle containing double wedge airfoil represents the Schlieren window.įigure 2.The double-wedge airfoil: (a) experimental setup (b) dimensions (mm). The double-wedge airfoil is showed in Figure 2. ![]() The double-wedge airfoil dimensions are 38.10 by 25.40 mm with the angle of 6.60. The test section has a rectangular shape, the top wall has the convergent-divergent profile and the bottom wall plate has 25 pressure taps, see Figure 1. Finally, Section 5 outlines some concluding remarks of this comparison.Įxperimentation was carried out in a supersonic wind tunnel. Section 4 presents the results numerical results are compared with the experimental data to show the validity of the computational model. In Section 3, the aim is focused on the simulation model, by describing the computational model and boundary conditions implemented in the commercial software. Section 2 presents the experimental development that includes the procedure of oblique shock wave visualization on the double-wedge airfoil by means of the Schlieren method. 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. Frequently, it is time consuming and expensive to test supersonic airfoils for extracting supercritical ow characteristics. The numerical simulation and experimentation were made using the fluent software and a supersonic tunnel, respectively. 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. In most studies, researchers have combined analytical-experimental and numerical methods to address this class of problems, see for example. They developed a numerical simulation of the fluid structure interaction effect on a double wedge airfoil. an analysis of the incompressible Navier-Stokes and elastodynamics equations in the Lagrangian- Eulerian framework is presented. 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. In fact, this type of wing profiles performs quite excellent in the supersonic flight regime but would lead to disastrous performance at low speed due to those singularities. Recently, double wedge airfoils are designed to have a better lift to drag ratio when compared to subsonic profiles in supersonic flight. The linear stability of oblique shock waves has been studied in, the author studied the stability with respect to small perturbation in the incoming ow and in the solid surface. The oblique shock wave produced by a three dimensional wing has been analyzed in. If the flying object is a long with sharp wedge front, a steady oblique shock wave will be generated. Although the shock waves thickness is about 2 µm, there are accelerations and sudden changes in fluid properties like velocity, pressure, temperature and density. These singularities increase the drag which is undesirable in the supersonic flow field. ![]() The shock waves generate irreversibilities and discontinuities in the flow, vibration and aeroacoustics noise. In internal and external flows at high velocities, normal and oblique shock waves formation are presented. Traditionally, supersonic airfoils are classified into two types, namely double wedge and bi-convex airfoils. NCTAM2003, 2003.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. Visualization of a Double Wedge Airfoil Model in a Transonic Shock Tube Flow. Shock Tube as a Device for Testing Transonic Airfoils at High Reynolds Numbers. Theoretical and Applied Mechanics, 2000, 49: 249–255Ĭook, W J, Presley, L L, Chapman, G T. Observation of Shock Tube Airfoil Flow with a Sharp Focusing Schlieren Method. Quantitative Results from the Focusing Schlieren Technique. Aerodynamic Investigation with Focusing Schlieren in Cryogenic Wind Tunnel. Gartenberg, E, Weinstein, L M, Lee, Jr., E. An Improved Large-Field Focusing Schlieren System. Aerodynamics Performance of Delta Wing at Supersonic Speeds. New York: The Ronald Press Company, 1980, 445–447 The Dynamics and Thermodynamics of Compressible Fluid Flow.
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