Fuselage aerodynamics analysis through semi empirical method and computational aerodynamics

Abu Bakar, Mohd Ridhwan (2014) Fuselage aerodynamics analysis through semi empirical method and computational aerodynamics. Masters thesis, Universiti Tun Hussein Onn Malaysia.

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Abstract

To fulfil the need of civilian and military purposes, there may be more than millions of aircrafts that had been built so far. In year of 2010, The Federal Aviation Administration (FAA) recorded that there were 223,370 aircraft under the category of General Aviation Aircraft is in operation around the world. This type of aircraft serves in the unscheduled flight for various reasons. Other aircrafts which are designed to support scheduled flight used by airlines such as the aircraft produced by aircraft manufacturer such as Boeing, McDonnell Douglas, Airbus, Fokker, Lockheed etc, may already contributed more than 100,000 aircrafts. Strictly speaking hundred thousand aircrafts have already built and each having its own fuselage shape and most of them had been tested under wind tunnel test. Unfortunately, their aerodynamics data kept in a confidential manner by the most aircraft manufacturers. The present work focused on the development of computer code for allowing one to carry out the aerodynamic characteristics over an arbitrary fuselage geometry. The computer code was developed by using semi empirical aerodynamics method in obtaining the overall aerodynamic characteristics and using Three Dimensional Panel Method for their pressure distribution over the fuselage surface. The aerodynamic characteristics analysis was carried out over various shape models and compared with the results provided by DATCOM software. In term of lift and pitching moment coefficient for various angle of attacks, the result of the developed software is in a good agreement with DATCOM software, but totally differ with DATCOM software is in term of drag coefficient. However if the component of base drag is ignored both two computer codes give close results. The effect of cambered fuselage was investigated by modelling the fuselage geometry developed based on NACA series. The result indicates that the maximum camber and the position of the maximum camber give strong influence to the pitching moment. The result of pressure distribution over the fuselage surface indicates that there are significant pressure variation over the body surface due to angle of attack. In addition to this, the research also found that the fuselage nose, fuselage camber line, and fuselage cross section give a strong influence to the overall aerodynamic characteristics.

Item Type:Thesis (Masters)
Subjects:T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL500-778 Aeronautics. Aeronautical engineering
ID Code:6322
Deposited By:Normajihan Abd. Rahman
Deposited On:30 Mar 2015 16:01
Last Modified:30 Mar 2015 16:01

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