This study presents Two Dimensional Compressible Flow Analysis Over a Generic Cruise Missile Model. The aerodynamics analysis carried out by use of Fluent Software. Here the pertinent Cruise missile geometry data had been chosen is BGM-109 tomahawk missile. Basically the flow problem around this missile model is a three dimensional flow problem. Treating the flow problem in view as two dimensional flow case, since their result will be used as a comparison purposes with the CFD code which currently under development. The aerodynamics analysis of this missile model carried at the free stream Mach number M = 0.7 for three different angle of attacks α = - 50, 0 and α = 50 . Here the flow is treated as an inviscid compressible flow applied to the missile configuration as (1) fuselage alone, (2) a combined configuration as fuselage and tail and (3) as wing body tail configuration. The results obtained by use of fluent software for those three configurations indicate the flow pattern surrounding object in term of flow properties ( pressure, density and Mach number ) change significantly between the missile as fuselage alone and their other combined configurations. As the angle of attack increase the change of flow pattern surrounding the missile become apparently compared to flow pattern at zero angle of attack. In addition to this, a symmetrical solution between the result at angle of attack α = 50 and α = -50 are also found.
The present work focuses on the development of computer code which allow the engine designer investigate the flow behavior through a divergent nozzle. The flow is assumed as quasi one dimensional and steady inviscid compressible flow. In other word the flow is governed by compressible Euler equation depending on the local Mach number. Solving such a mixed type of equation is difficult. The boundary between hyperbolic and elliptic region is not clear. To avoid such difficulty can be done through treating a steady flow problem as unsteady flow problems with the boundary condition is fixed with respect to time. As unsteady flow problem, the Euler equation becomes hyperbolic type of partial differential equation with respect to time. This approach allows one to solve the unsteady flow problem goes to a steady state solution. There are various methods can used for solving hyperbolic type of equation, such as MacCormacks scheme, Steger Warmings scheme, Beam Warmings Scheme and TVD Scheme. The present work used MacCormacks scheme and Steger Warming scheme will be used to investigate the flow behavior through a divergent nozzle. Comparison with analytic solution shows that Steger Warmings scheme gives a better result than MacCormacks scheme.
scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.
hi@scite.ai
10624 S. Eastern Ave., Ste. A-614
Henderson, NV 89052, USA
Copyright © 2024 scite LLC. All rights reserved.
Made with 💙 for researchers
Part of the Research Solutions Family.