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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.
261

Application of finite-state inflow to flap-lag-torsion damping in hover

de Andrade, Donizeti 05 1900 (has links)
No description available.
262

Helicopter blade-tip stability in forward flight

Shipman, Keith Waldo 08 1900 (has links)
No description available.
263

Dynamic stall characteristics of an oscillating airfoil in a harmonically varying freestream velocity

Malone, John Bruce 12 1900 (has links)
No description available.
264

A method of computing the aerodynamic interactions of a rotor-fuselage configuration in forward flight

Berry, John D. 05 1900 (has links)
No description available.
265

The effect of wake dynamics on rotor eigenvalues in forward flight

Wang, Yi-Ren 05 1900 (has links)
No description available.
266

Virtual aero-shaping of a clark-y airfoil at low angles of attack

Chatlynne, Etan Solomon 05 1900 (has links)
No description available.
267

Application of a state-space wake model to a servo flap controlled rotor in hover

Stettner, Martin 12 1900 (has links)
No description available.
268

An actively cooled floating element skin friction balance for direct measurement in high enthalpy supersonic flows /

Chadwick, Kenneth Michael, January 1992 (has links)
Thesis (Ph. D.)--Virginia Polytechnic Institute and State University, 1992. / Vita. Abstract. Includes bibliographical references (leaves 67-71). Also available via the Internet.
269

Aerodynamic performance enhancement of a NACA 66-206 airfoil using supersonic channel airfoil design a thesis /

Giles, David Michael. Marshall, David D., January 1900 (has links)
Thesis (M.S.)--California Polytechnic State University, 2009. / Title from PDF title page; viewed on Nov. 16, 2009. "September 2009." "In partial fulfillment of the requirements for the degree [of] Master of Science in Aerospace Engineering." "Presented to the faculty of California Polytechnic State University, San Luis Obispo." Major professor: David D. Marshall, Ph.D. Includes bibliographical references (p. 85-87).
270

Aerodynamic drag of a two-dimensional external compression inlet at supersonic speed

Esterhuyse, JC January 1997 (has links)
Thesis (DTech (Mechanical engineering))--Cape Technikon, 1997 / This study forms the basis from which the aerodynamic drag of a practical supersonic inlet can be predicted. In air-breathing propulsion systems, as used in high performance flight vehicles, the fuel is carried onboard and the oxygen required for combustion is ingested from the ambient atmosphere. The main function of the inlet is to compress the air from supersonic to subsonic conditions with as little flow distortion as possible. When the velocity of the vehicle approaches or exceeds sonic velocity (M = 1,0) a number of considerations apply to the induction system. The reason for this is that the velocity of the ingested air has to be reduced to appreciably less than sonic velocity, typically to M = 0,3. Failure to do so will cause the propulsion system to be inoperative and cause damage. In the process of compressing the air from supersonic to subsonic conditions a drag penalty is paid. The drag characteristics are a function of the external geometry and internal flow control system of the inlet. The problem which was investigated dealt with drag of a specific type of inlet, namely a two-dimensional external compression inlet. This study is directed at formulating definitive relationships which can be used to design functional inlet systems. To this effect the project was carried out over three phases, a theoretical investigation where a fluid-flow analysis was done of the factors influencing drag. The second phase covered a comprehensive experimental study where intensive wind-tunnel tests were conducted for flight Mach numbers of M = 1,8; M = 2,0; M = 2,2; M = 2,3 and M = 2,4. During the third phase a comparison, between the theoretical values and experimental data was done, for validating the predicted aerodynamic drag figures. The following findings are worth recording: • the increase in total drag below the full flow conditions is more severe than predicted due to the contribution of spillage drag; • the range for subcritical mode of operation is smaller than expected due to boundary layer effects. The study has shown that reasonably good correlation could be achieved between the theoretical analysis and empirical test at low subcritical modes of operation. This suggests that the study has achieved its primary objective.

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