International Research Journal of Engineering and Technology (IRJET)
e-ISSN: 2395 -0056
Volume: 04 Issue: 01 | Jan -2017
p-ISSN: 2395-0072
www.irjet.net
CFD Analysis of conceptual Aircraft body Manikantissar 1, Dr.Ankur geete 2 1 M. Tech scholar in Mechanical Engineering, SD Bansal college of technology, Indore, M.P, India 2 Associate professor in Mechanical Engineering Department, SD Bansal college of technology, Indore, M.P, India
-------------------------------------------------------------------***--------------------------------------------------------------------ABSTRACT INTRODUCTION OF CFD ANALYSIS The delta wing is a wing platform in the form of a triangle. Delta wings are most commonly seen on military aircraft. Delta wings are ideal for supersonic flight, and provide high maneuverability. In spite of its potential application in military aircraft, the understanding of the aerodynamics of such wings is far from complete. In the present paper analyzed delta wing conceptual aircraft model on the parameters of speed at sub sonic speed, angle of attack, drag force, lift force generated, stall angle and turbulences. The result obtained would determine its usability for fighter jets, commercial aircrafts and UAV drones. The technique used to analyze the problem is Computational Fluid Dynamics and software is ANSYS CFX. Keywords: lift and drag force, conceptual aircraft model, CFD analysis, Angle of attack.
CFD is a simulation tool used to predict what will happen, quantitatively when fluids flow, often with the complication of simultaneous flow of heat, mass transfer, phase change (melting, freezing, boiling), chemical reaction (combustion, rusting), mechanical movement of (pistons, fans etc.), stresses in and displacement of immersed or surrounding solids. CFD uses a computer to solve the relevant sciencebased mathematical equation, using information about the circumstances in question. There are three laws that have to be satisfied for the control volume, the conservation laws.
INTRODUCTION
Conservation of momentum
From the development of the first powered flights (1903) to the present time, the study of the aerodynamic design has played an important role in the airplanes optimization. Traditionally it has been in the hands of the designer’s experience, tests of flight and wind tunnel experiments, being this last tool the one that has provided a method of systematic study and the capability of making inexpensive adjustments of control parameters in a design. At the present time, Computational Fluid Dynamics (CFD) has come to complement the experimental studying, reducing the cost in tests and time for the generation of prototypes. The selection of right wing is the most important aspect of airplane design which determines lift force generation, maneuverability stall angle, fuel storage. Delta wings finds its application for flying at supersonic speed and hence used for fighter aircraft and space shuttles. Delta wings also provide benefits of swept wings (decreased drag at supersonic speeds) due to their high sweep, and they are structurally efficient and provide a large internal volume which can be used for fuel tanks. They are also relatively simple and inexpensive to manufacture. At this point in the design process CFD analysis plays a crucial, if not its most important, role. Wind tunnel models are generally very expensive to build, costing perhaps hundreds of thousands of dollars or more, and wind tunnel test time is a significant cost driver during a project. In this work Analysis of aircraft body has done on CFD.
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• Conservation of mass
Conservation of energy
Literature review
Karna S. Patel et al. (1) studied the CFD analysis of the flow over NACA 0012 airfoil and conclude that at the zero degree of AOA there is no lift force generated. The amount of drag force and value of drag coefficient also increased but the amount of increment in drag force and drag coefficient is quite lower compare to lift force. In this study, NACA 2412 airfoil [2] is used to design the wing, in which the first digit is the maximum camber in hundredths of the chord, the second digit is the location of the maximum chamber from the leading edge in tenths of the chord, and the last two digits represent the maximum thickness in hundredths of the chord [3]. The parameters are chosen, such as airfoil chord c = 0.3m, airfoil span l = 1.6m . These dimensions are used to fabricate the experimental wing model, which are also consistent with the open data of a number of test UAVs samples in Vietnam.
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