2,789 research outputs found
The Phil Rogers Russell, D.O. Collection
No full textFinding aid for The Phil Rogers Russell, D.O. CollectionPhil Rogers Russell, D.O., practiced osteopathic medicine in the state of Texas from his 1917 graduation from the American School of Osteopathy, Kirksville, Missouri, until his death at the age of 80 in 1975. He was a strong supporter of the profession and was instrumental in the establishment and growth of the Fort Worth Osteopathic Hospital and the Texas College of Osteopathic Medicine. He won numerous awards and honors from the American Osteopathic Association, the Texas Osteopathic Association, other osteopathic institutions and associations, and civil awards. He was the author of "Quack Doctor", a memoir of his years as an osteopathic physician.The Phil R. Russell, D.O. Collection consists of speeches, articles, book manuscripts, books, memorabilia, photographs, certificates and awards that Dr. Russell authored or was presented during his lifetime
The Life and Legacy of Dr. Russell Moore
No full textAlumni Memorial Chapel, October 13, 2011Dr. R. Albert Mohler Jr. celebrates the 40th birthday of Dr. Russell Moore (Oct. 9) by sharing his favorite photos with the SBTS chapel audience
Combustion enhancement in a scramjet engine using oxygen enrichment and porous fuel injection
No full textThis paper reports on the experimental testing of oxygen-enriched porous fuel injection in a scramjet engine. Fuel was injected via inlet mounted, oxide-based ceramic matrix composite (CMC) injectors on both flow path surfaces that covered a total of 9.2% of the intake surface area. All experiments were performed at an enthalpy of 3.93–4.25 MJ/kg, flight Mach number 9.2–9.6 and an equivalence ratio of 0.493. At this condition, the engine was shown to be on the verge of achieving appreciable combustion. Oxygen was then added to the fuel prior to injection such that two distinct enrichment levels were achieved. Combustion was found to increase, by as much as 40% in terms of combustion-induced pressure rise, over the fuel-only case with increasing oxygen enrichment. Further, the onset of combustion was found to move upstream with increasing levels of oxygen enrichment. Thrust, both uninstalled and specific, and specific impulse were found to be improved with oxygen enrichment. Enhanced fuel–air mixing due to the pre-mixing of oxygen with the fuel together with the porous fuel injection are believed to be the main contributors to the observed enhanced performance of the tested engine
Numerical investigation of transverse jets through multiport injector arrays in supersonic crossflow
No full textA three-dimensional numerical study has been performed of the effects of sonic gaseous hydrogen injection through multiple transverse injectors subjected to a supersonic crossflow. Solutions were obtained for a series of injection configurations in a Mach 4.0 crossflow, with a global equivalence ratio of ø = 0:5. Results indicate a different flow structure than for a typical single jet, with the development of two clearly defined wake vortices, including a stagnation point and reversed flow region immediately behind each downstream jet. While the overall penetration was reduced under the investigated conditions, significant improvements were observed when nondimensionalizing against the equivalent jet diameter for each modeled injector row. This was found to be the result of increased jet-to-freestream momentum ratio due to the subsonic flow regions between each injector. Further enhancements were also observed in terms of mixing performance for the multijet cases. Improvements of up to 5% in the overall mixing efficiency were experienced by using multiple jets due to increased mixant interface area and intermediate stirring through wake vortices between each injector. No improvement in far-field mixing was observed. Overall, it has been demonstrated that there are benefits to be gained through the injection of gaseous hydrogen from many small injectors rather than fewer large injectors. Copyright © 2010 by A. S. Pudsey and R. R. Boyce. Published by the American Institute of Aeronautics and Astronautics, Inc
Justification of Induction: Russell and Jin Yuelin. A Comparative Study
No full textJin Yuelin (1895-1984), a Chinese logician and philosopher, is greatly influenced by Hume's and Russell's philosophies. How should we respond to Hume's problem of induction? This is an important clue to understand Jin's whole philosophical career. The first section of this paper gives a brief historical review of Russell and Jin. The second section outlines Hume's skeptical arguments against causality and induction. The third section expounds Russell's justification of induction by discussing his views on Hume's skepticism, causality, principle of induction, and empirical postulates. The fourth section clarifies Jin's justification of induction by discussing his critique of Hume's epistemology and his arguments for the reliability of causality and the eternal truth and apriority of the principle of induction. The final section compares Jin's justification of induction with Russell's and concludes that there are similarities and differences between their projects and that both their attempts fail. This paper takes the similar responses to the problem of induction by Jin and Russell to demonstrate the communication that there has been between Chinese philosophers and the Western ones.http://gateway.webofknowledge.com/gateway/Gateway.cgi?GWVersion=2&SrcApp=PARTNER_APP&SrcAuth=LinksAMR&KeyUT=WOS:000310146900004&DestLinkType=FullRecord&DestApp=ALL_WOS&UsrCustomerID=8e1609b174ce4e31116a60747a720701EthicsHistory & Philosophy Of ScienceLogicPhilosophyA&HCISCI(E)0ARTICLE4353-3783
Aerothermal-structural analysis of a rocket-launched Mach 8 scramjet experiment: ascent
No full textThis paper reports on the methodology and results of a weak-coupled aerothermal–structural analysis on the ascent phase of the SCRAMSPACE Mach 8 scramjet flight experiment. This vehicle was essentially unshrouded during the flight trajectory, relying on the thin, 5 mm thick aluminum external shell of the payload to maintain structural integrity and protect the flight experiment. As such, understanding the thermal–structural response of the vehicle was imperative to mission success. Using two- and three-dimensional models, an iterative procedure was employed to compute the flowfield, convective heating, wall temperatures and structural coupling at flight times covering both peak heating and peak surface temperature. Accounting for such coupling resulted in a 150 K reduction in wall temperature compared to the more conservative cold wall assumption. Despite this, peak temperatures remained of the order of 550 K. Further, thermally induced stresses within these regions were in excess of four times the material failure limits. Irreversible material failure during ascent was therefore concluded likely to occur on the external shell. Two alternate materials, steel 1006 and copper, were therefore assessed with the results indicating that steel sections on the external shell resulted in the best thermal–structural response of the payload
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