Thesis--California Institute of Technology. / Includes bibliographical references.

Thesis--California Institute of Technology. / Includes bibliographical references.

No description available.

Thesis (MEng (Mechanical engineering))-University of Pretoria, 2008. / Includes bibliographical references.

Thesis (M.E. (Res.))--University of Sydney, 2003. / Title from title screen (viewed Apr. 28, 2008). Submitted in fulfilment of the requirements for the degree of Master of Engineering (Research) to the School of Aerospace, Mechanical and Mechatronic Engineering. Includes bibliography. Also available in print form.

Thesis (M.S.)--Brigham Young University. Dept. of Mechanical Engineering, 2005. / Includes bibliographical references (p. 97-98).

Thesis (M.S.)--Brigham Young University. Dept. of Mechanical Engineering, 2007. / Includes bibliographical references (p. 113-116).

Thesis (M.S.) -- University of Tennessee, Knoxville, 2006. / Title from title page screen (viewed on Feb. 5, 2007). Thesis advisor: Ralph D. Kimberlin. Vita. Includes bibliographical references.

Existing subsonic wind tunnel methods for obtaining dynamic stability derivatives for aircrafts at high angle of attack are described. From the general equations of motion of an aircraft in space, the perturbation equations of motion are derived for applying to a wind tunnel aircraft model. Data Reduction and test procedures for important dynamic tests are evolved systematically from the restrained perturbed equations of motion. Emphasis is given to the typical single degree of freedom apparatuses and associated data reduction for routine measurement of dynamic stability derivatives due to pitching, rolling and yawing of the model. The translational and snaking motion apparatuses from which the derivatives, α, β, and p, q, r are measured separately, are also presented. Finally, for the purpose of increasing the capabilities of the Virginia Tech dynamic test systems, a single degree of freedom forced oscillatory rig, which gives the exact sinusoidal displacement of the model and also adjustable to the existing curved and rolling flow facilities, is described with its data acquisition/reduction. / Master of Science

This paper gives the derivation of a method for determining the forces to be applied to these points which will simulate the load distributed over all the airplane.