Experiential Knowledge Without Experience: A response to Cray

This paper responds to Wesley Cray’s article “Omniscience and Worthiness of Worship.” According to Cray, “an omniscient being is one that instantiates all propositional and experiential knowledge,” and no person can have that entire body knowledge. Contrary to Cray, this paper indicates that God’s omniscience implies full propositional knowledge, but only experiential knowledge that is great-making and non-composite. The central argument this paper proposes is that experiential knowledge does not imply that one has had that experience; for God, experiential knowledge may come from a variety of avenues. This article concludes with alternative arguments against Cray’s formulation of God

The Failure of “She: An Evaluation of Solutions to Gendered Language

This thesis looks at the prevalence of gendered language in modern day English in North America. Drawing upon different analyses of masculine pronouns and slang, this paper argues that modern solutions to gendered language fail to come to terms with the contextual elements of language. While acknowledging that gendered language is a significant problem, the author argues that the solutions thus far presented, specifically replacing the generic pronoun “he” with “she,” cannot combat the way language reflects societal masculinization. Using Wittgenstein to criticize a Heidegger’s notion of language, this paper argues that societal change is a prerequisite to the success of linguistic substitutions for gendered language

Application of computational fluid dynamics and laminar flow technology for improved performance and sonic boom reduction

A discussion is given of the many factors that affect sonic booms with particular emphasis on the application and development of improved computational fluid dynamics (CFD) codes. The benefits that accrue from interference (induced) lift, distributing lift using canard configurations, the use of wings with dihedral or anhedral and hybrid laminar flow control for drag reduction are detailed. The application of the most advanced codes to a wider variety of configurations along with improved ray-tracing codes to arrive at more accurate and, hopefully, lower sonic booms is advocated. Finally, it is speculated that when all of the latest technology is applied to the design of a supersonic transport it will be found environmentally acceptable

Instrumentation advances for transonic testing

New and improved instrumentation, like new and improved wind tunnels, provide capabilities which stimulate innovative research and discovery. During the past few years there have been a number of instrumentation developments which have aided and abetted the acquisition of more accurate aerodynamic data and have led to new physical insights as well. Some of these advances are reviewed, particularly in the area of thin film gages, hot wire anemometry, and laser instrumentation. A description is given of the instruments and/or techniques and some sample results are shown

The pros and cons of code validation

Computational and wind tunnel error sources are examined and quantified using specific calculations of experimental data, and a substantial comparison of theoretical and experimental results, or a code validation, is discussed. Wind tunnel error sources considered include wall interference, sting effects, Reynolds number effects, flow quality and transition, and instrumentation such as strain gage balances, electronically scanned pressure systems, hot film gages, hot wire anemometers, and laser velocimeters. Computational error sources include math model equation sets, the solution algorithm, artificial viscosity/dissipation, boundary conditions, the uniqueness of solutions, grid resolution, turbulence modeling, and Reynolds number effects. It is concluded that, although improvements in theory are being made more quickly than in experiments, wind tunnel research has the advantage of the more realistic transition process of a right turbulence model in a free-transition test

Langley airfoil-research program

An overview of past, present, and future airfoil research activities at the Langley Research Center is given. The immediate past and future occupy most of the discussion; however, past accomplishments and milestones going back to the early NACA years are dealt with in a broad-brush way to give a better perspective of current developments and programs. In addition to the historical perspective, a short description of the facilities which are now being used in the airfoil program is given. This is followed by a discussion of airfoil developments, advances in airfoil design and analysis tools (mostly those that have taken place over the past 5 or 6 years), and tunnel-wall-interference predictive methods and measurements. Future research requirements are treated

Central Ohio Diabetes Association

IMPACT. 1: Diabetes is a disease that causes high blood glucose (sugar) levels. Diabetes occurs when the body doesn't make or properly use a hormone called insulin. When insulin doesn't do its job, blood sugar rises to toxic levels and damages vital organs. -- 2. Over 25% of people with diabetes are undiagnosed. Uncontrolled diabetes can cause blindness, stroke, heart disease, kidney failure, nerve, and blood vessel damage. -- 3. Fortunately education, proper medical treatment, regular exercise, weight control, and healthy eating can prevent or delay these serious health problems.PRIMARY CONTACT: Roy Bobbitt ([email protected])The Central Ohio Diabetes Association is an independent, local, non-profit, human service agency that "helps Central Ohioans living with diabetes detect their condition, prevent onset and complications, and learn to live well with the challenge of diabetes.

Theoretical and experimental pressure distributions for a 71.2 degree swept arrow-wing configuration at subsonic, transonic, and supersonic speeds

A wind-tunnel test of an arrow-wing body configuration consisting of flat and twisted wings, as well as a variety of leading- and trailing-edge control-surface deflections, was conducted at Mach numbers from 0.40 to 2.50 to provide an experimental data base for comparison with theoretical methods. Theory-to-experiment comparisons of detailed pressure distributions were made using current state-of-the-art and newly developed attached- and separated-flow methods. Conditions were delineated under which these theories provide accurate basic and incremental aeroelastic loads predictions. Current state-of-the-art linear and nonlinear attached-flow methods were adequate only at small-angle-of-attack cruise conditions. Of the several separated-vortex methods evaluated, only the one utilizing a combination of linear source and quadratically varying doublet panels showed promise of yielding accurate loads distributions at moderate to large angles of attack

The Plan of Measuring Educational Efficiency in Bay City

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Semiempirical method for predicting vortex-induced rolling moments

A method is described for the prediction of rolling moments on a wing penetrating a vortex velocity field generated by a large aircraft. Rolling moments are determined from lifting pressure coefficients computed with an inviscid-flow linear panel method. Two empirical corrections are included to account for the lifting efficiency of an airfoil section and the local stall on the wing. Predicted rolling moments are compared with those from two windtunnel experiments. Results indicate that experimental rolling moments, for which the Reynolds number of the following wing is low, should be interpreted with caution