Aerodynamics analysis for several fuselage geometries using fluent software and aerodynamics semi empirical method
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 ad...
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| Format: | Thesis |
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2011
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| Online Access: | http://eprints.uthm.edu.my/2415/ http://eprints.uthm.edu.my/2415/1/Hasan_Taher.pdf |
| Summary: | 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. |
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