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  • About
  • The Global ETD Search service is a free service for researchers to find electronic theses and dissertations. This service is provided by the Networked Digital Library of Theses and Dissertations.
    Our metadata is collected from universities around the world. If you manage a university/consortium/country archive and want to be added, details can be found on the NDLTD website.
161

Measurement of ablation in transient hypersonic flows /

Hunt, Dillon C. January 2001 (has links) (PDF)
Thesis (M.E. Sc.)--University of Queensland, 2002. / Includes bibliographical references.
162

The use of compliant surface for supersonic flow over a compression ramp /

Fletcher, Alex J. P. January 2002 (has links)
Thesis (Ph. D.)--Lehigh University, 2003. / Includes vita. Includes bibliographical references (leaves 175-182).
163

Motion induced aerodynamics of a pitching delta wing

Vaughan, Jon January 1997 (has links)
Current trends in modem combat aircraft design have seen a move towards canard configurations with all moving foreplanes, providing a manoeuvre advantage with reduced stability. At the same time, with rapid advances in the field of assisted flight control and emphasis now placed on computer controlled, fly-by-wire aircraft, there is an unprecedented requirement for detailed knowledge of motion dependent aerodynamics, such as may be experienced on a foreplane undergoing rapid corrective motions. In this study, investigations have been carried out into the rigid body, motion dependent aerodynamics of a 55* delta wing, undergoing small amplitude pitching oscillations. Steady and unsteady surface pressures have been measured on the wing under low speed, pre-stalled conditions, for a range of mean incidence and oscillation frequencies, up to frequencies approximating a full scale foreplane under low speed conditions, such as landing approach. Relationships between the motion of the wing and the unsteady pressures have been identified, and it has been shown that they may not be approximated by a simple quasi-steady model due to significant phase shifts in specific regions of the flow. The lower surface flow is shown to be highly dependent on the effective incidence of the wing. The vortical flow of the upper surface has a more complex response to the pitching motion, with the shear layer and burst motion reacting at different rates. There is also significant attenuation/overshoot and phase in the unsteady loads and moments (obtained by integrating the pressure data) relative to the quasi-steady. These are shown to be highly dependent on the pitching oscillation frequency and the location of the pitch axis. It is suggested that there may be a pitch axis location such that quasi-steady loading may be obtained under oscillatory conditions. Application of the key findings to a simple all moving control surface shows that the stability of the control system is strongly influenced by the pitch axis location.
164

AN INVESTIGATION OF THE INFLUENCE OF A FORWARD EJECTED GAS STREAM IN HYPERSONIC FLOW ABOUT BLUNT-BODIES

Tolle, Frederick Francis, 1921- January 1973 (has links)
No description available.
165

Atmospheric kinetic energy at 500 mb as a function of zonal wave number.

Luistro, Farnacio M. January 1965 (has links)
An adequate portrayal of the global distribution of kinetic energy is fundamental to our understanding of the general circulation of the atmosphere. Since there are insufficient wind observations to carry out direct computations it is customary to supplement them with pressure or geopotential height data and to use space and time continuity to obtain analyzed weather maps. [...]
166

A direct method for calculating the thrust and torque of a helicopter in vertical ascent

Culwell, Fred Blaylock 05 1900 (has links)
No description available.
167

Determination of the design parameters for optimum heavily loaded ducted fans

Wright, Terry 12 1900 (has links)
No description available.
168

A method of computing the potential flow on thick wing tips

Raj, Pradeep 12 1900 (has links)
No description available.
169

An investigation of pressure drag in transonic flow by the method of hydraulic analogy

Stancil, Robert Thomas 08 1900 (has links)
No description available.
170

Application of the hydraulic analogy to study the performance of three airfoils at subsonic and supersonic speeds

Ryle, Dallas Marlin 08 1900 (has links)
No description available.

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