Browsing by Author "Busing, J. R."

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    Experimental investigation of the interference of a body on a low aspect ratio wing of rectangular planform at a Mach number of 2
    (College of Aeronautics, 1955-06) Busing, J. R.; Marson, G. B.; Lilley, G. M.
    Results are given of pressure measurements on awing of gross aspect ratio approximately 2/3 mounted on a cylindrical body with an ogival nose, made at a Mach number of 2.00 in the 9in, x 9in, supersonic -wind tunnel at the College of Aeronautics. The wing section was a single wedge having a 6° total nose angle. The ranges of body incidence and roll in these tests were from 0° to 30°, and 0°, 30°, 600 and 90° respectively. The normal force, lift, drag and side force coefficients, and rolling and pitching moments were obtained from the pressure measurements.
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    On some aspects of the noise propagation from supersonic aircraft
    (College of Aeronautics, Cranfield, 1953-02) Lilley, G. M.; Westley, R.; Yates, A. H.; Busing, J. R.
    The noise problem associated with an aircraft flying at supersonic speeds is shown to depend primarily on the shock wave pattern formed by the aircraft. The noise intensity received by a ground observer from a supersonic aircraft flying at high as well as low altitudes, is shown to be high although it is of a transient nature. Continues…
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    A preliminary experimental investigation of the effect of surface catalytic efficiency on stagnation point heat transfer
    (College of Aeronautics, 1962-01) Busing, J. R.
    Results of an experimental investigation to measure the difference between the heat transfer rate to a catalytic wall and to a non-catalytic wall are presented. Using thin film thermometer techniques, associated with an electrical analogue, direct measurement was made of the heat transfer rate to a chemically deposited platinum film and a vacuum evaporated silicon monoxide film. These films were formed near the stagnation point of a pyrex glass sphere and the experiments were done in the College of Aeronautics shock tube. The models were designed so that the heat transfer rates were measured under identical flow conditions. The results obtained indicate that the heat transfer rate to the platinum film is significantly higher than the heat transfer rate to the silicon monoxide film.
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    A preliminary investigation of the flow over a particular wing body combination at Mach number 2
    (College of Aeronautics, 1955-04) Busing, J. R.; Lilley, G. M.
    Results are presented of visual tests, by surface flow and Schlieren techniques, of the flaw over a particular wing body combination at M = 2.0, made in the 9in x 9in supersonic wind tunnel at the College of Aeronautics. It should be noted that the photographs in this report represent only a small part of all the data collected. The effects of providing roughened bands and air jets for transition fixation on the body are discussed. It is shown that although such methods may be satisfactory at zero or low angles of incidence they do not fix transition uniformly over the complete body circumference at higher incidences. For this reason the main part of the tests have been performed with free transition. The formation of vortex sheets on both wings and body is discussed for a range of incidence and roll angles and some conclusions are drawn as to the shape of the vortex pattern and its induced flow effects.
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    Shock reflection and surface effects in the shock tube
    (College of Aeronautics, 1966) Busing, J. R.; Clarke, John F.
    A thin-film resistance thermometer, mounted on the end-wall of a shock tube, is used to record surface temperatures and heat transfer rates following reflection of the primary shock wave. This information is combined with the results of theoretical investigations to produce simultaneous information about surface accommodation effects and gas thermal conductivities at high pressures and moderate temperatures.
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    Weak compression waves in relaxing gases
    (Cranfield University, 1972) Scott, E. M.; Clarke, J. F.; Busing, J. R.
    Studies have been made of the structure of weak compression (shock) waves in relaxing gases. These studies have been primarily concerned with the development of separate theoretical and experimental techniques. These techniques are not inter-related in general except in the overall context of Vibrational relaxation. The theoretical studies have been concerned with the influence on the structure of weak normal shock waves of translational non-equilibrium. bimodal relaxation and second order unimodal relaxation. The affect of translational nonequilibrium on the relaxation process has been studied by forming an asymptotic expansion in the ratio of the viscous length to the relaxation length. The perturbation scheme was singular and required the application at the method of matched asymptotic expansions. Bimodal relaxation has been studied by forming an asymptotic expansion in the ratio of the energy of the secondary vibrational mode to the total Vibrational energy. The addition of a second order term to the rate equation describing the behaviour of a single vibrational mode has also been studied by forming an asymptotic expansion. In this case. the perturbation parameter was the ratio of the two relaxation times concerned. The experimental studies have been concerned with the production and study or weak normal shock waves in the Cranfield Institute or Technology 2" shock tube. A time resolved quantitative schlieren system has been used for the study of the weak normal shock waves. This particular system had been developed previously for this purpose. and further developments and refinements have been made to it. Experimental studies have been made with the schlieren system of the structure or strong incident shock waves in carbon dioxide. The vibrational relaxation time of carbon dioxide determined in this way for translational temperatures from 300 o K to 1200 o K has been found to be in reasonable agreement with measurements made elsewhere. A technique has been developed for the production of weak incident shock waves in t.i.1e shock tube, which involved the positioning of a perforated plate in the channel of the shock tube. The vibrational relaxation time of carbon dioxide determined in this way for translational o temperatures of approximately 300 K has been found to be in good agreement with measurements made elsewhere. Good agreement has also been obtained between the experimentally measured density gradient profiles and theoretical profiles. The curvature of the shock waves obscured the transition from a fully dispersed to a partly dispersed shook wave. Further improvements and refinements have been made to a technique which had been developed previously for the propagation of weak normal shock waves through the reflected shock region of the shock tube flow. This technique was used to study the behaviour of fully dispersed shock waves at high temperatures. The relaxation time of carbon dioxide determined in this way for temperatures from 300 o K to 600o K has been found to be in good agreement with measurements made elsewhere.