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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.
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Showing 11 to 20 of 132 (0.032 seconds)Spelling suggestions: "subject:"aerofoil""
| 11 |
A method of computing the potential flow on thick wing tipsRaj, Pradeep 12 1900 (has links)
No description available.
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| 12 |
Application of the hydraulic analogy to study the performance of three airfoils at subsonic and supersonic speedsRyle, Dallas Marlin 08 1900 (has links)
No description available.
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| 13 |
Numerical study of separated turbulent flow over airfoilsSugavanam, Ananthanarayanan 08 1900 (has links)
No description available.
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| 14 |
Notes on theoretical aerodynamics and airfoil theoryJohns, William Ben 05 1900 (has links)
No description available.
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| 15 |
Application of the hydraulic analogy to study the performance of two airfoils in compressible flowCatchpole, Eric John 12 1900 (has links)
No description available.
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| 16 |
Viscous modeling of ground effect aerodynamics of airfoil and jetOckfen, Alex Earle, January 2008 (has links) (PDF)
Thesis (M.S. in mechanical engineering)--Washington State University, December 2008. / Title from PDF title page (viewed on Dec. 31, 2008). "School of Mechanical and Materials Engineering." Includes bibliographical references (p. 149-154).
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| 17 |
Experimental investigation of the flow field about sharp-edged delta and rectangular wingsSun, Yung-chiun January 1961 (has links)
When a thin delta wing with high leading-edge sweep is placed at incidence in a stream, the fluid separates from the surface at the leading edges and coils up to form a pair of symmetrically placed vortices above the upper surface of the wing. This flow pattern is stable up to high incidence, but at extreme high incidence, the stable vortex core appears to burst or rapidly diffuse. The present research was done as part of a general program to study the vortex bursting phenomenon about sharp-edged delta wings. The aim was to determine the bursting position at different angles of attack and the effect on the wing performance. It was found that the bursting occurs first downstream of the trailing edge and then moves rapidly upstream with increasing incidence. The wing stalls when the bursting point occurs at a position upstream of the wing's trailing edge.
The pressure distributions on a sharp-edged rectangular wing were also measured in the present research and the overall normal force coefficient was obtained by the graphical integration of surface pressures. It was found from the pressure distributions that the flow pattern changes from one type to another in the range from ∝= 10° to ∝= 15°. The overall normal force coefficient reaches its first maximum value at 17° incidence. / Applied Science, Faculty of / Mechanical Engineering, Department of / Graduate
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| 18 |
An experimental investigation of the effects of massive film cooling on the aerodynamics of a turbine airfoil /Hartsel, James Edward January 1970 (has links)
No description available.
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| 19 |
The influence of delta plan wing vortex generators upon room air movementMissenden, J. F. January 1987 (has links)
No description available.
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| 20 |
Computational study of shock control at transonic speedZhu, Yu Ping January 2000 (has links)
No description available.
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