Computational Fluid Dynamics . Supersonic Wind Tunnel Air Fl Assignment

Computational Fluid Dynamics . Supersonic Wind Tunnel Air Fl Assignment Computational Fluid Dynamics . Supersonic Wind Tunnel Air Fl â€" Assignment Example > YearIntroductionComputational fluid dynamics (CFD) is becoming one of the most sought after skills in both small and large industries. According to Pozrikidis (2009), effective simulation helps reduce cost of design implementations by over 75%. A system analysis software company, ANSYS Inc. is one such a company that is a global in production, training and hence use of CFD. ANSYS CFX is one such software that is extensively applied in analysis of fluids. CFD is important in design on many accounts. Blazek (2005) says, CFD analysis applications are critical in ensuring the success of design and development phases of industrial production. They include, but not limited to internal and external fluid flows, gas or liquid flow with heat transfer, real gases, time dependent flow, heat transfer, transonic/subsonic/supersonic regimes, turbulent/laminar flows, compressible gas and conjugate heat transfer. CFD analysis is complex and needs vast experience and knowledge in thermal and fluid dynamics. Some of the analysis services include the thermal hydraulic analysis, heat transfer analysis structural fluid interaction, industrial fluid dynamic analysis and dynamic mesh analysis. For this particular experiment, CFD is applied in analysis of a supersonic wind tunnel air flowing from a hot reservoir (9000C) to a low temperature test section (400C) and at pressure 9 atmospheres via throat. CFD is particularly important/most reliable simulator for this kind of problem because of because it is used to obtain both the qualitative and quantitative analyses of the fluid study. With this tool, the boundary conditions can be determined. This makes ANSYS the most reliable in carrying out the CFD in our particular case. For a fluid under pressure (the 9 atms)/ compressible fluid dynamics, its speed of motion is compared with that of sound. The comparison is expressed in terms of ratio of the local flow-speed, u, divided by the local speed of sound, a. This is referred to as th e Mach number, M expressed as belowThis number is used in categorizing the compressible flows into different Mach number regimes. To make the Mach number useful, it can be viewed as being directly proportional to the ratio of the Kinetic to the internal energy of the molecules (). If there is no losses involved, then the Mach number is referred to as the Isentropic Mach number. It refers to the ideal Mach number one would get without the losses and walls without friction. In this particular case, these two form the assumptions of the study. With the Isentropic state in mind, and the pressure conditions, the isentropic flow relations Mach number can be computed using the formulaAs the speed of motion increases beyond speed of sound, the fluid/air Mach number is greater than 1 M 1. This happens with supersonic flow. In this case, the density changes faster than the velocity changes by a factor that is equal to M squared. i. e Mach number squared. According to (), for a supersonic sp eed, the Mach number range is given as shown below. The Mach number, if given, can therefore be used to compute speed of flow. The table below summarizes the relationship between regime, Mach and speed.