CoA. Notes (1952-1969)

Permanent URI for this collection

https://dspace.lib.cranfield.ac.uk/handle/1826/9626

Browse

Browsing CoA. Notes (1952-1969) by Author "Busing, J. R."

Now showing 1 - 3 of 3
  • Thumbnail Image
    ItemOpen Access
    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.
  • Thumbnail Image
    ItemOpen Access
    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.
  • Thumbnail Image
    ItemOpen Access
    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.