CaltechTHESIS committee: Monograph
https://feeds.library.caltech.edu/people/Cole-J-D/combined_committee.rss
A Caltech Library Repository Feedhttp://www.rssboard.org/rss-specificationpython-feedgenenWed, 26 Jun 2024 12:54:27 -0700Investigation into the Flow of a Viscous Heat Conducting Compressible Fluid
https://resolver.caltech.edu/CaltechETD:etd-12242008-101248
Year: 1948
DOI: 10.7907/14DR-5V68
NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document.
The present investigation is concerned with the effect of a small viscosity and heat conduction coefficient on the flow of a compressible fluid. It is well known that, in the case of an incompressible fluid, such an investigation leads to the boundary layer theory.
The chief purpose of this paper is to determine whether the main result of boundary layer theory, namely, that viscosity plays a negligible part in the flow outside a very narrow region in the immediate vicinity of any solid boundary in the fluid, is still valid for a compressible fluid. To investigate that point, a very simple type of flow is selected: the flow past a semi-infinite two-dimensional flat plate parallel to the main stream direction. The problem is further simplified as follows: on the basis of experimental results, the existence of a layer influenced by viscosity is assumed, and the boundary conditions are applied near the outer edge of this layer. This allows a linearization of the equation of motion, and gives information on the interaction between the outer edge of this layer and the main field of flow.
The analysis is carried out by the methods based on the theory of the Laplace Transformation. The results are essentially, that if the flow is subsonic, the boundary layer theory developed for incompressible fluids may be extended without qualitative changes. However, in a supersonic flow, one must expect two related effects: one finds the boundary layer, which, as a first approximation, in similar to the boundary layer of an incompressible fluid, and a shock-wave along the Mach line which starts at the leading edge of the flat palate, and whose strength is given by the expression:
[...] where [...] is the normal velocity across the shock, M is the free stream Mach number, [...] is the distance from the leading edge of the flat plate along the shock, [...] is the distance normal to the shock, [...] is sonic velocity of the free stream and [...] is the mean effective free stream kinematic viscosity of the fluid.https://resolver.caltech.edu/CaltechETD:etd-12242008-101248The Burning of Single Drops of Fuel in Oxidizing Atmospheres
https://resolver.caltech.edu/CaltechETD:etd-12182003-091848
Year: 1955
DOI: 10.7907/E4YT-5B12
<p>The burning of single, isolated drops of fuel in a quiescent oxidizing atmosphere has been investigated theoretically and experimentally. Two theories are presented. The first, called the diffusion theory, rests on the assumption that the rate of burning is determined by the rate at which the reactants are delivered by diffusion to the flame front surrounding the liquid drop. The second, or thermal theory is based on the assumption that chemical reaction rates govern the rate of burning of the droplet.</p>
<p>The effects on droplet burning rate of changes in the composition, temperature, and pressure of the surrounding oxidizing atmosphere have been investigated experimentally. A preliminary study has also been made of the effect of forced convection on droplet burning.</p>
<p>It is found that the thermal theory of droplet burning does not adequately explain the observed variations in droplet burning rate as the composition and temperature of the surrounding atmosphere are varied. On the other hand, substantial agreement is found between the results of the diffusion theory and experimental data.</p>https://resolver.caltech.edu/CaltechETD:etd-12182003-091848Linearized Transonic Flow About Non-Lifting, Thin Symmetric Airfoils
https://resolver.caltech.edu/CaltechETD:etd-12072005-135856
Year: 1963
DOI: 10.7907/3ZC0-7Y26
Transonic flow about symmetric, non-lifting airfoils is treated by solving an approximate linear differential equation of mixed type in place of the exact small-perturbation equations. The pressure distribution and drag coefficient are obtained in closed form for power series airfoils. The technique of local linearization is also applied to improve the accuracy of the results, particularly near the leading edge where the linearizing approximation is found to be invalid. Numerical results are obtained for the parabolic arc and single wedge airfoils and are found to compare favorably with experimental data and with previous theoretical results.
https://resolver.caltech.edu/CaltechETD:etd-12072005-135856Aligned fields, magneto-fluid dynamic flow past bodies
https://resolver.caltech.edu/CaltechETD:etd-09122002-094628
Year: 1966
DOI: 10.7907/XGWS-3X78
NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document.
The drag of spheres and disks has been measured in a flow of liquid sodium with an aligned magnetic field. The experiments were carried out for 10[superscript 4] < Re < 25 x 10 [superscript 4] and N , the interaction parameter, satisfying 0.1 < N < 80 . The sphere C[subscript D] was not a function of N for N < or = 0.3, began to increase appreciably for N ~ 1.0 , and reached an asymptotic dependence proportional to [square root]N for N > 10 . The disk gave a C[subscript D] which was relatively unchanged for N< 10 , began to increase for N~10 , and had approximately the same value as for spheres for N > 20 . We conclude, that for high N , flows are characterized by C[subscript D] insensitive to body shape and emphasize this range in our discussion. A physical model is presented which involves stagnant regions which grow in length as N increases, and are separated from the outer flow by thin dissipation layers. A singular perturbation technique is suggested for the theoretical treatment of such layers.https://resolver.caltech.edu/CaltechETD:etd-09122002-094628