Showing papers by "Vaughn College of Aeronautics and Technology published in 1960"
TL;DR: In this article, the equations for planar two-dimensional steady flow of an ideal dissociating gas are linearized, assuming small disturbances to a free stream in chemical equilibrium.
Abstract: The equations for planar two-dimensional steady flow of an ideal dissociating gas are linearized, assuming small disturbances to a free stream in chemical equilibriumAs an example of their solution, the flow past a sharp corner in a supersonic stream is evaluated and the variations of flow properties in the relaxation zone are found Numerical illustrations are provided using an ‘oxygen-like’ ideal gas and comparisons made with a characteristics solution The flow past a sharp corner can be studied in a conventional shock tube and it may be possible to verify the present theory experimentally In particular it may prove feasible to use the results to obtain a measure of the reaction rates in the gas mixture
56 citations
01 Dec 1960
TL;DR: The Aslib Cranfield Project as discussed by the authors was the first attempt to make a complete test of various indexing systems, and was considered by many people in this country and the United States.
Abstract: The Aslib Cranfield Project had its beginning some years back, when several members of the Aslib Aeronautical Group took an active part in the development of a new form of index that had been proposed by the National Aeronautical Institute of Holland. Later we did some tests on the Uniterm system of co‐ordinate indexing and, following a joint conference with the Classification Research Group, the idea developed of making a complete test of various indexing systems. A draft programme was prepared and was considered by many people in this country and the United States. An application was made to the National Science Foundation for a grant to cover the first stage of the investigation, and in July 1957 the Foundation advised Aslib that the grant had been approved.
52 citations
TL;DR: In this article, the effect of structural damping on panel flutter has been investigated and it is concluded that there is an interdependence of structural and aerodynamic damping, which in the range of Mach numbers for which piston theory is valid, shows the destabilizing effect of the damping.
Abstract: The effect of structural damping on panel flutter has received little treatment in the literature but the available information suggests that such an effect may be destabilizing. By considering a two‐dimensional, simply‐supported panel and using linear piston theory for the aerodynamic forces an analysis is presented in which the effect of hysteretic structural damping is considered. The main emphasis is on flat unbuckled panels, although a brief investigation of buckled panels is also presented, and it is concluded that there is an interdependence of structural and aerodynamic damping, which in the range of Mach numbers for which piston theory is valid, shows the destabilizing effect of structural damping. This effect is apparently more pronounced at high altitudes. A comprehensive bibliography of panel flutter is also included.
34 citations
12 citations
TL;DR: In this article, a new method of speed control for sewing machines used in the shoe industry was studied in a series of experiments and the skill requirements of the task were examined and the new control was tested both in the laboratory and in the factory.
Abstract: A new method of speed control for sewing machines used in the shoe industry was studied in a series of experiments. The skill requirements of the task were examined and the new control was tested both in the laboratory and in the factory. The justification for this kind of investigation is discussed.
9 citations
3 citations
TL;DR: In this article, a relatively simple analysis in which only axi-symmetric deformations of the shell are considered is presented, where the shell is assumed to be unreinforced longitudinally.
Abstract: In ref. 1 an extensive review was made of the panel flutter problem and analyses dealing with flutter of cylindrical shells of finite length were discussed in considerable detail. It was stated that one of the central points of controversy is in the choice of the appropriately simplified governing equations for the thin–walled elastic shell. Related to this is the choice of flutter mode and the question as to how the critical flutter speed depends upon the number of circumferential and axial waves in that mode. Stepanov and Strack and Holt found that the critical Mach number decreases with increasing number of circumferential waves, and Fung has concluded that the axially symmetric mode is of the greatest interest. The purpose of this note is to present a relatively simple analysis in which only axi–symmetric deformations of the shell are considered. The shell is assumed to be unreinforced longitudinally.
2 citations
TL;DR: In this article, the authors describe the organization of a Laboratory Electronics Course in the Department of Aircraft Electrical Engineering at the College of Aeronautics, Cranfield, England, which caters to two standards of specialization and to students with a wide range of previous training.
Abstract: This paper describes the organization of a Laboratory Electronics Course in the Department of Aircraft Electrical Engineering at the College of Aeronautics, Cranfield, England. The course caters to two standards of specialization and to students with a wide range of previous training. The minor specialization course concentrates solely on fundamentals and the basic concepts, while the major course is carried to the threshold of design procedures. The contents of both courses are limited by the student's previous training and the time available for practical work. The over-all standard of the major course is that of the M.Sc. degree of a British University. Four different ways of construction and presentation of experiments are described and the limitations of each are discussed. Finally, the laboratory layout, equipment, and scheme of work for both courses is described.
1 citations
TL;DR: In this article, the displacement equations for a uniform cylinder of arbitrary cross-section subjected to a lateral pressure loading are presented, where the displacements are assumed to be small in comparison with the thickness of the shell.
Abstract: As far as is known, no explicit solution exists in the literature for the displacement equations in u, v and w , for a uniform cylinder of arbitrary cross section subjected to a lateral pressure loading. However, the advent of Ref. 1 now makes available an admirable treatise devoted entirely to the analysis of thin elastic shells. The equations developed in this reference apply only to linear problems, i.e. the displacements are assumed to be small in comparison with the thickness of the shell, but they are general enough to include all shells of arbitrary curvature. Unfortunately the generality of these equations inhibits their immediate use to cylindrical shell problems, and it is the purpose of this note to present the essential features of the theory for non-circular cylinders.
1 citations
TL;DR: Greenspon et al. as discussed by the authors presented an approximation to the plastic deformation of a Rectangular Plate under static load with design applications, I n t e r n a t i o n a l Shipbui ld ing Progress, Vol. 3, N o. 22, p p p. 329-340, J u n e, 1956.
Abstract: i T imoshenko , S., Theory of Plates and Shells, 1st Ed . , p . 304, M c G r a w Hil l Book Co. , Inc . , N e w York , 1940. 2 D a y , J . W., Hydrostatic Pressure Tests on Thin Rectangular Diaphragms 21 Inches by 13/i Inches, D a v i d T a y l o r Mode l Bas in R p t . 635, M a r c h , 1951. 3 D a y , J . W., Hydrostatic Pressure Tests on Thin Rectangular Diaphragms 84 Inches by 54 Inches, D a v i d T a y l o r M o d e l Basin R p t . 636, Apri l , 1951. 4 Greenspon , J . E. , An Approximation to the Plastic Deformation of a Rectangular Plate Under Static Load with Design Applications, I n t e r n a t i o n a l Shipbui ld ing Progress , Vol. 3, N o . 22, p p . 329-340 , J u n e , 1956. W+ve