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A comparison of flight input techniques for parameter estimation of highly-augmented aircraft /Gates, Russell J. January 2003 (has links)
Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, September 1995. / Thesis advisor(s): Daniel J. Collins, Rocjard M. Howard. Includes bibliographical references (p. 83-84).
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332 |
Cold flow drag measurement and numerical performance prediction of a miniature ramjet at Mach 4 /Wee, Teik Khoo. January 2003 (has links) (PDF)
Thesis (M.S. in Engineering Science (Mechanical Engineering))--Naval Postgraduate School, December 2003. / Thesis advisor(s): Garth V. Hobson, Rayomnd P. Shreeve. Includes bibliographical references (p. 67). Also available online.
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Design and optimization of a hypersonic test facility for sub-scale testing /O'Kresik, Stephen R. January 2003 (has links) (PDF)
Thesis (M.S. in Astronautical Engineering)--Naval Postgraduate School, December 2003. / Thesis advisor(s): Jose O. Sinibaldi, Garth V. Hobson. Includes bibliographical references (p. 69). Also available online.
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Unsteady separation point injection for pressure recovery improvement in high subsonic diffusers /McElwain, Brian D. January 2002 (has links)
Thesis (M.S. in Aeronautics and Astronautics and Engineer in Aeronautics and Astronautics)--Massachusetts Institute of Technology, 2002. / Includes bibliographical references (p. 155-156). Also available online.
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Flow structure of annular jets.Chan, Wai-tin, January 1900 (has links)
Thesis--M. Phil., University of Hong Kong, 1978.
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Flow structures of coaxial jets /Au, Hom. January 1983 (has links)
Thesis--Ph. D., University of Hong Kong, 1984.
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A theoretical and experimental investigation on the aerodynamic behaviour of two dimensional cascade flow.Lee, Lan-yee, Francis. January 1968 (has links)
Thesis--M. Sc. (Eng.), University of Hong Kong. / Mimeographed.
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Upgrade of a LabVIEW based data acquisition system for wind tunnel test of a 1/10 scale OH-6A helicopter fuselage /Lines, Philipp A. January 2003 (has links) (PDF)
Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, June 2003. / Thesis advisor(s): E. Roberts Wood, Richard M. Howard. Includes bibliographical references (p. 53-54). Also available online.
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A study of direct-current surface discharge plasma for a Mach 3 supersonic flow controlShin, Jichul, 1971- 28 August 2008 (has links)
A direct-current, non-equilibrium surface glow discharge plasma in the presence of a Mach 2.85 flow is studied experimentally for flow control applications. The discharge is generated with pin-like electrodes flush mounted on a ceramic plate with sustaining currents from 25 mA to 300 mA. In the presence of a supersonic flow, two distinct discharge modes - diffuse and constricted - are observed depending on the flow and discharge operating conditions. In cathode upstream location, both diffuse and constricted discharges are observed while in cathode downstream location, the discharge mostly exhibits either constricted mode or bistable mixed mode. The effect of the discharge on the flow ("plasma actuation") is characterized by the appearance of a weak shock wave in the vicinity of the discharge. The shock is observed at low powers (~10 W) for the diffuse discharge mode but is absent for the higher power (~100 W) constricted mode. High speed laser schlieren imaging suggests that the diffuse mode plasma actuation is rapid as it occurs on a time scale that is less than 100 [mu]sec. Rotational (gas) and vibrational temperatures within the discharge are estimated by emission spectral line fits of N₂ and N⁺₂ rovibronic bands near 365-395 nm. The electronic temperatures are estimated by using the Boltzmann plot method for Fe(I) atomic lines. Rotational temperatures are found to be high (~1500 K) in the absence of a flow but drop sharply (~500 K) in the presence of a supersonic flow for both the diffuse and constricted discharge modes. The vibrational and electronic temperatures are measured to be about 3000 K and 1.25 eV (14500 K), respectively, and these temperatures are the same with and without flow. The gas (rotational) temperature spatial profiles above the cathode surface are found to be similar for the diffuse and constricted modes indicating that dilatational effects due to gas heating are similar. However, complete absence of flow actuation for the constricted mode suggests that electrostatic forces may also play an important role in supersonic plasma-flow actuation phenomena. Analytical estimates using cathode sheath theory indicates that ion pressure within the cathode sheath can be significant resulting in gas compression in the sheath and a corresponding expansion above it. The expansion in turn may fully negate the dilatational effect in the constricted case resulting in an apparent absence of forcing in the constricted case. Plasma-induced flow velocity reaches about 1 m/s in stagnant air at the discharge current of order tens of milliamps. This electrostatic forcing in the direction from anode to cathode can play an important role in the boundary layer of supersonic flow. / text
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Flow structure of annular jetsChan, Wai-tin, 陳維田 January 1977 (has links)
published_or_final_version / Mechanical Engineering / Master / Master of Philosophy
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