Thesis (doctoral)--Universität Rostock, 1929. / Includes bibliographical references.

"Submitted in partial fulfillment of the requirements for the degree of Master of Business Administration from the Naval Postgraduate School, June 2009." / Advisor(s): D'Addea Jones, Becky ; Euske, Ken J. "June 2009." "MBA professional report"--Cover. Description based on title screen as viewed on July 14, 2009. Author(s) subject terms: Fleet Readiness Center, Aviation Maintenance Repair and Overhaul, MRO, Aviation enterprise, Military Depots, Aviation Maintenance, FRCSW, NADEP Includes bibliographical references (p. 61-68). Also available in print.

Thesis (Ph. D.)--University of Washington, 1998. / Vita. Includes bibliographical references (leaves [114]-116).

Thesis (M.S. in Mechanical Engineering)--Naval Postgraduate School, Sept. 2004. / Thesis Advisor(s): Raymond Shreeve. Includes bibliographical references (p. 53). Also available online.

Inauguraldissertation : Recht- und wirtschaftwissenschaftliche Fakultät : Rostock : 1929.

Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1993. / Vita. Abstract. Includes bibliographical references (leaf 28). Also available via the Internet.

Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1993. / Vita. Abstract. Includes bibliographical references (leaves 92-94). Also available via the Internet.

Thesis (M.S.)--Washington State University, December 2006. / Includes bibliographical references (p. 80-84).

Thesis (M.S.)--West Virginia University, 2007. / Title from document title page. Document formatted into pages; contains x, 82 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 63-66).

A theory is presented for the calculation of the pressure distribution and lift for arbitrary thick airfoils fitted with normal upper surface spoilers in two dimensional incompressible flow. Airfoil shape and angle of attack and spoiler location and height are arbitrary and unrestricted. The theory uses a sequence of conformal transformations from a basic flow past a circle, with one or two sources on that part of the circle corresponding to the surface of the airfoil and spoiler exposed to the wake. The flow inside the separating streamlines is ignored, and the upper surface pressure downstream of the spoiler is taken as an empirical parameter, assumed constant. The sources in the wake permit satisfaction of Kutta conditions with the desired pressure at the spoiler tip and airfoil trailing edge. Features of the theory include good prediction of loading distribution, a finite wake width and a pressure distribution on the separating streamlines decreasing asymptotically towards the free stream value at infinity. The theoretical predictions are compared with lift and pressure measurements on a Joukowsky airfoil of 11% thickness and 2.L\% camber, and with lift measurements on a 14% thick Clark Y airfoil. Both airfoils were tested through a range of angle of attack with spoilers of 5 and 10% chord height, each at several locations. Good agreement is found. / Applied Science, Faculty of / Mechanical Engineering, Department of / Graduate