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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.
1

Compressible dynamic stall control using microjets

Beahn, James Jay. Shih, Chiang. January 2003 (has links)
Thesis (M.S.)--Florida State University, 2003. / Advisor: Dr. Chiang Shih, Florida State University, College of Engineering, Dept. of Mechanical Engineering. Title and description from dissertation home page (viewed Mar. 2, 2004). Includes bibliographical references.
2

Unsteady boundary layer separation /

Zalutsky, Konstantin E., January 2000 (has links)
Thesis (Ph. D.)--Lehigh University, 2000. / Includes vita. Includes bibliographical references (leaves 186-192).
3

Aircraft departure resistance prediction using structured singular values /

York, Brent W., January 1993 (has links)
Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1993. / Vita. Abstract. Includes bibliographical references (leaves 59-61). Also available via the Internet.
4

An investigation of near wake effects in airfoil dynamic stall

Scruggs, Roy Mac 05 1900 (has links)
No description available.
5

An experimental investigation of active stall control in compression systems

Chowdhury, Subhradeep 05 1900 (has links)
No description available.
6

Numerical simulation of dynamic stall phenomena in axial flow compressor blade rows

Rivera-Cedeno, Carlos J. 05 1900 (has links)
No description available.
7

A two-dimensional model to predict rotating stall in axial-flow compressors /

Nowinski, Matthew C., January 1993 (has links)
Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1993. / Vita. Abstract. Includes bibliographical references (leaves 99-102). Also available via the Internet.
8

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

Malone, John Bruce 12 1900 (has links)
No description available.
9

Modelling stalled airfoils

Yeung, William Wai-Hung January 1990 (has links)
The thesis deals with some new applications of the wake source model, a two-dimensional incompressible potential flow model used for bodies experiencing flow separation. The body contour is conformally mapped to a circle, for which the flow problem is solved using source singularities to create free streamlines simulating the separating shear layers. In common with other inviscid theories, it generally requires the pressure in the separated flow region, and the location of separation if boundary-layer controlled. Different mapping sequences and flow models have been constructed for the following five problems, 1. the trailing-edge stall for single element airfoils, 2. flat plates with separation bubbles, 3. separation bubbles upstream of spoilers with downstream wakes, 4. spoiler/slotted flap combinations, at which the spoiler inclination is arbitrary, and 5. two-element airfoils near (trailing-edge) stall. Predictions of pressure distribution are compared with wind tunnel measurements, and good agreement is found in cases 1 and 5. The initial shape of the separation streamlines also appears to be satisfactory. Results in cases 2 and 3 are promising although more work is needed to improve the bubble shapes and their pressure distributions. Partial success has been achieved on spoiler/ slotted flap configurations, depending on the spoiler inclination. For strong wake effect on the flap (e. g. δ = 90° ), the model predicts a very high suction peak over it. Whereas the experimental data resemble a stalled distribution even though flow visualization indicates the flap to be unstalled. This may be related to a limitation of the method, also noted in the separation-bubble problems, that it cannot specify a complete boundary condition on a free streamline. This discrepancy diminishes as the spoiler angle becomes smaller (e. g. δ = 30° ) in the cases of higher incidences so that the wake boundary tugs away from the flap sooner. / Applied Science, Faculty of / Mechanical Engineering, Department of / Graduate
10

Unsteady drag and dynamic stall as simulated in a varying freestream

Kunz, Donald Lee 05 1900 (has links)
No description available.

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