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Using commercial aviation information systems in operational support airlift decision support systems /Kubik, Charles Paul. Unknown Date (has links) (PDF)
Thesis (M.S. in Information Technology Management and M.B.A.)--Naval Postgraduate School, 2004. / Thesis Advisor(s): Glenn Cook, Roxanne Zolin. Includes bibliographical references (p. 67-68). Also available online.
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The development of turbojet aircraft in Germany, Britain, and the United States : a multi-national comparison of aeronautical engineering, 1935-1946 /Pavelec, Sterling Michael. January 2004 (has links)
Thesis (Ph. D.)--Ohio State University, 2003. / Vita. Includes bibliographic references (p. 251-262). Also available via the Internet.
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A Monte-Carlo-based simulation of jet exhaust nozzle thermal radiative signatures /Chapman, David D. January 1992 (has links)
Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1992. / Vita. Abstract. Includes bibliographical references (leaves 76-79). Also available via the Internet.
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An experimental and analytical study of noise production and propagation in burnersJones, James D. January 1982 (has links)
Turbulent combustion in burners causes low frequency broadband combustion noise. Before the noise from such burners can be reduced, the generating mechanisms must be understood.
Noise generation by a simple can-type burner has been investigated. Several parameters are varied to study their effect on the far-field noise spectrum. The noise characteristics of the burner observed in this work are generally similar to those updated in the literature.
A combustion noise data base is developed for use with an analytical model in isolating the acoustic source structure within the burner. The source distribution with frequency subject to an assumed spacial distribution is recovered from far-field acoustic pressure measurements used in conjunction with the analytical model for a limited number of the cases investigated experimentally. / Master of Science
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A comparative study on supersonic underexpanded swirling jet noiseSaadani, Salmane B. 01 July 2001 (has links)
No description available.
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Experimental study on counter flow thrust vectoring of a gas turbine engineSantos, Maria Madruga. Krothapalli, Anjaneyulu, January 1900 (has links)
Thesis (Ph. D.)--Florida State University, 2005. / Advisor: Dr. Anjaneyulu Krothapalli, Florida State University, College of Engineering, Dept. of Mechanical Engineering. Title and description from dissertation home page (viewed June 14, 2005). Document formatted into pages; contains xx, 224 pages. Includes bibliographical references.
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The effect of nonlinear propagation on near-field acoustical holography /Shepherd, Micah Raymond, January 2007 (has links) (PDF)
Thesis (M.S.)--Brigham Young University. Dept. of Physics and Astronomy, 2007. / Includes bibliographical references (p. 99-106).
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I. A modified <kappa-epsilon> turbulence model for high speed jets at elevated temperatures. II. Modeling and a computational study of spliced acoustic linersGanesan, Anand. Tam, C. K. W. January 2005 (has links)
Thesis (Ph. D.)--Florida State University, 2005. / Advisor: Dr. Christopher K. W. Tam, Florida State University, College of Arts and Sciences, Dept. of Mathematics. Title and description from dissertation home page (viewed Sept. 21, 2005). Document formatted into pages; contains xv, 118 pages. Includes bibliographical references.
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Development of a compact sound source for the active control of turbofan inlet noiseDungan, Mary E. 30 March 2010 (has links)
The concept of a compact sound source driven by piezoactuators is experimentally investigated, and analytical design tools are developed. The sound source, consisting of a thin, cylindrically curved aluminum panel and a pair of collocated, surface-bonded piezoceramic actuators, was developed with the objective of employing it as a secondary sound source in the active control of turbofan blade interaction inlet noise.
The sound source was fitted in an experimental duct representative of an aircraft engine inlet, and the interior and exterior sound pressure levels generated by the source were measured. The effects of excitation voltage, excitation frequency, duct length, and downstream termination of the duct were investigated. It was found that the source is capable of generating relatively high acoustic levels at its fundamental frequency (over 130 dB at maximum voltage input).
Techniques for analytically predicting the acoustic levels are investigated. A commercial code for numerical modeling of structural-acoustic radiation was utilized. Results show generally good agreement with experimental measurements for the case of the short duct. It is believed that the model accuracy can be further improved through additional refinements in the modeling techniques. / Master of Science
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Suppression of Turbofan and Turbojet Engine Generated NoiseMaster, Harry David 01 January 1972 (has links) (PDF)
Every advance in the transformation of heat energy into mechanical energy has involved a noise problem, and in general it increases with the power production. The jet airplane is a good example: the large-scale turbulence of the exhaust gases in the jet forms an unusually intense source of sound the control of which is quite difficult. The additionally generated fan noises add characteristic fan tones which are particularly noticeable on landing approaches. the human ear is the vulnerable receiver of these noises, and the problem becomes one of deciding how much jet engine noise reduction is required for the comfort or safety of the receiver, and then to devise ways to achieve it.
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