No description available.

Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1993. / Vita. Abstract. Includes bibliographical references (leaves 72-74). Also available via the Internet.

Supersonic inlet starting by mass spillage is studied theoretically and numerically in the present thesis. A quasi-one-dimensional, quasi-steady theory is developed for the analysis of flow inside a perforated inlet. The theory results in closed-form relations applicable to flow starting by the mass spillage technique in supersonic and hypersonic inlets. / The theory involves three parameters to incorporate the multi-dimensional nature of mass spillage through a wall perforation. Mass spillage through an individual slot is studied to determine these parameters; analytical expressions for these parameters are derived for both subsonic and supersonic flow conditions. In the case of mass spillage from supersonic flows, the relations are exact. However, due to the complexity of flow field, the theory is an approximation for subsonic flows. Therefore, a correction factor is introduced which is determined from an empirical relation obtained from numerical simulations. / A methodology is also proposed to determine perforation size and distribution to achieve flow starting for a given inlet at a desired free-stream Mach number. The problem of shock stability inside a perforated inlet designed with the proposed method is also discussed. / The method is demonstrated for some test cases. Time-realistic CFD simulations and experimental results in the literature confirm the accuracy of the theory and the reliability of the proposed design methodology.

Thesis (Ph. D.)--University of Chicago, Department of Chemistry, August 2002. / Includes bibliographical references. Also available on the Internet.

No description available.

An analysis was presented for predicting lift and drag characteristics of flat-top wing-body combinations at supersonic speeds. These combinations consist of a wing mounted above an expanding body with their apexes being coincident. The assumptions with which the analysis was made are the following: 1. The linear theory was applicable. 2. The leading edge or the wing was coincident or ahead of the body shock. 3. Condition of zero base drag (static pressure at the base equal to the stream static pressure). The analysis was carried out by considering the individual terms which appear in the lift-drag relations separately, and utilizing the most recent theoretical methods to determine them. The analysis was applied to two flat-top wing-body combinations; namely, a semiconical body with an arrow planform wing, and a 3/4 power semibody with a diamond planform wing. For these combinations a free-stream Mach number of 3.35 satisfied the condition for the wing leading edge and the body bow shock to be coincident. To obtain a check on the analysis, the results were compared with experimental data at a Mach number of 3.35. / Master of Science

Tangential supersonic slot injection (M = 1.7) of air into a supersonic air stream (M = 2.91) was studied with a dual hot wire probe. This probe was used to simultaneously determine total temperature and mass flux. Mean profiles across the entire flow field at three axial stations (x/h = 4, 10, 20) were obtained, as well as the temperature and mass flux turbulence intensities. The probe can be used anywhere except at locations where features of the flow are smaller than the separation between the wires (0.18 mm). The calibration of the probe can be repeated with less than a three percent change in calculated Nusselt number. The hot wire probe can also be tuned to obtain a high frequency response. The interaction of a shock wave, caused by a wedge placed on the upper tunnel wall, with the mixing region was investigated. Little change in the mean profiles was observed, but there was a significant increase in turbulence levels. / Master of Science

This theoretical and experimental investigation has proven that accurate results can be obtained by using the hydraulic analogy. The analogy can be used in either the subsonic, transonic or supersonic range. The theory was intended to be general and showed that an exact analogy exists between free surface water flow and two dimensional gas flow. By theoretical investigation, a new channel was proposed and experiments were conducted. Remarkable correlation between theory and experiment was found and it is believed that the method presented in this thesis represents a closer approximation to the actual flow of air than any of the other present day analogies. It has been shown that by using the analogy, the pressure, density, and temperature can be easily obtained. In addition, the shock wave phenomenon can be easily observed. This analogy would be an excellent took in demonstrating the different types of flow around bodies. Analogy research in the field of supersonic aerodynamics is not only justified, but also necessary since the present day experimental technique in wind tunnels present economical and scientific difficulties. A large amount of knowledge can be obtained from analogy research in this field. The analogy described in the paper gives accurate results; the proposed apparatus is inexpensive, and experiments can be performed in a very short time. / Master of Science

No description available.

Thesis (Ph. D.)--Florida State University, 2005. / Advisor: Dr. Christopher K. W. Tam, Florida State University, College of Arts and Sciences, Dept. of Mathematics. Title and description from dissertation home page (viewed Sept. 21, 2005). Document formatted into pages; contains xv, 118 pages. Includes bibliographical references.