Aerodynamics analysis for several fuselage geometries using fluent software and aerodynamics semi empirical method

M.Elkamel, Hasan Taher (2011) Aerodynamics analysis for several fuselage geometries using fluent software and aerodynamics semi empirical method. Masters thesis, Universiti Tun Hussein Onn Malaysia.

[img]
Preview
PDF
640Kb

Abstract

This study presents aerodynamics analysis over several generic fuselage geometries. The aerodynamics analysis carried out by use of DATCOM Software, Fluent and own developed computer code. The own developed computer code is computer code which developed based on semi empirical aerodynamics method adopted according to Roskam[1.2] and Datcom Handbook[3.4]. There are various possible fuselage shapes. Basically the size and helage shape determined by payload requirement, and also the related design objectives of that flying vehicle. However the present work focuses on symmetrical fuselage having uniform cross sections may in the form: circular, elliptic or rectangular cross section which suit for missiles. It had been known that a missile design goes through several steps, where the aerodynamic calculation one of the most important stage in missile design. Missiles as flying vehicles which are usually expendable and uninhabited, have provided an opportunity for designers to increase the ranges of speed, altitude, and maneuvering accelerations. Unfortunately such opportunity has created new aerodynamic problems and represent a challenge for the designers in order to maintain the flight path of the missile. In respect to the aerodynamics analysis on fuselage suited for missile. Here the pertinent fuselage geometry data had been chosen is in accordance to typical missile currently used in military operation, such as AGM - 129, AGM-86 , BGM - 109 and Exocet cruise. Such kind missiles have a fineness ratio around 10. The [uselage geomelry defined accordmg to several fuselage model available from various model such as Fuselage Agard Model 1, Agard Model 2, Parabolic Spindle, Ellipsoid of revolution ect. The aerodynamics analysis carried out at different Mach number in the range below Mach number 0.6 from angle of attack a = -5' to a = 20'. The comparison result in term of lift and pitching moment coefficients for various angles of attack between DATCOM and The Developed computer code are in a good agreement.

Item Type:Thesis (Masters)
Subjects:T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL500-778 Aeronautics. Aeronautical engineering
ID Code:2415
Deposited By:Normajihan Abd. Rahman
Deposited On:20 Apr 2012 11:42
Last Modified:20 Apr 2012 11:42

Repository Staff Only: item control page