Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1991. / Vita. Abstract. Includes bibliographical references (leaves 53-56). Also available via the Internet.

An investigation was conducted in the Langley 8-foot transonic tunnels to determine the aerodynamic loading characteristics of a thin conical cambered low-aspect-ratio delta wing in combination with a basic body and a body indented symmetrically for a Mach number of 1.2 in accordance with the supersonic area rule. The tests were conducted at Mach numbers from 0.60 to 1.12 and at 1.43 and at angles of attack generally from -4° to 20°. The wing vas conically cambered over the outboard 15 percent of each semispan. The wing had an aspect ratio of 2.31, 60° sweepback of the leading edge, and had NACA 65A003 airfoil sections parallel to the model plane of symmetry over the uncambered portion. The results of this investigation indicate that a leading-edge separation vortex forms at moderate angles of attack and causes the shape of the span load distribution to change markedly. Significant center of pressure movements are noted at transonic speeds. Indenting the body in accordance with the supersonic area rule had little effect on the aerodynamic loading characteristics. Comparisons with expert mental data for a similar plane wing indicates that the cambered wing is considerably more effective than the plane wing in utilizing the leading edge suction forces to produce thrust. A comparison between experimental and theoretical results indicates fair agreement around sonic speeds. / Master of Science

The capability for experimental assessment of unsteady shock wave effects on turbine blade performance has been developed. A novel shock-generation system utilizing a shotgun blast has been implemented into the Virginia Tech Wind Tunnel Transonic Cascade Facility. Specialized optical systems and high-performance pressure instrumentation were utilized to obtain both qualitative and quantitative information. Shadowgraph photos of the unsteady shock wave propagation through the cascade indicate presence of a vortical region and its movement from the blade surface into the passage flow. A previously unseen distortion of the trailing edge shock wave is also identified. High-frequency blade surface pressure measurements reveal large fluctuations in surface pressure during shock passage. An estimate of unsteady blade lift is made which reveals a 120 percent peak-peak variation. Furthermore, an approximated loss coefficient was determined to fluctuate as much as 40 percent near the blade passage center. Comparisons are made with previously-published experimental and analytical results. / Master of Science