Browsing by Author "Marson, G. B."
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Item Open Access Aerodynamic characteristics of two low aspect ratio rectangular wings at Mach 2(College of Aeronautics, 1956-04) Marson, G. B.This note summarises the important results of a detailed experimental investigation into the flow and pressure distribution over two rectangular single wedge wings. The experiments were carried out .in the 9" x 9" supersonic tunnel at the College of Aeronautics, 6 at a Mach number of 2.0 and a Reynolds number of 2.5 x 10 per foot. Both wings had a chord of 3 inches and a total wedge angle of 6°. They had no real trailing edge, but were faired into a cylindrical support which could be rolled and pitched in the tunnel. Wing A was of 2 inch1span, giving an aspect ratio of 0.67. `Ting B was of 1 1/4 inch span, 0.42 aspect ratio. 132 pressure tappings 4 were spaced regularly over half of one surface of each wing, and up to 19 pressure readings could be taken simultaneously on vertical mercury manometers. models were pressure plotted at pitch angles of 0°, 2 1/2°, 5°, 7 1/2°, 10°, 15°, 20°, 25°, and 30°, and at all roll angles at intervals of 30°. Since each wing was symmetrical about the centreline, the complete pressure distribution over all surfaces at any roll angle Ø could he obtained from the readings taken on the one surface at Ø, 180°- Ø, 180° + Ø, and 360°- Ø. The pressure readings were then integrated to give the forces and moments on the complete wing… [cont.].Item Open Access The calculation of the wave drag of a family of low-drag axisymmetric nose shapes of fineness ratio 4.5 at zero incidence at supersonic speeds(College of Aeronautics, 1954-05) Marson, G. B.The pressure drag coefficients of a particular family of convex logarithmic projectile nose shapes in which the nose angle is an important parameter have been calculated over a range of supersonic Mach numbers using a rapid approximate method due to Zienkiewicz.5 The optimum nose angle for minimum wave drag of these profiles for each Mach number has been obtained. It is shown that above N = 1.5„ approximately, the optimum shape is similar to the hypersonic optimum profile and has the sane or- less wave drag than this profile. However for values of M/F, where P is the fineness ratio, below 0.5, both the hypersonic and the logarithmic optimum profiles have a higher drag than the so-called cubic profile (Ref, 9).Item Open Access The displacement effect of pitot tubes in narrow wakes at subsonic and supersonic speeds(College of Aeronautics, Cranfield, 1956-10) Marson, G. B.The apparent displacement of the effective centre of a circular pitot tube from it geometric centre when placed in narrow wakes has been measured at sub and super- sonic speeds. Similar effects were found at all speeds. Continues...Item Open 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.Item Open Access An experimental investigation of the pressure distributions on five bodies of revolution at Mach numbers of 2.45 and 3.19(College of Aeronautics, Cranfield, 1954-04) Marson, G. B.; Socha, W.; Keates, R. E.Measurements have been made in the College of Aeronautics 2½ x2½ intermittent high speed tunnel of the pressure distribution on five non lifting bodies of revolution of different nose angles at zero incidences. The tests were made at Mach numbers of 2.45 and 3.19. The results are compared with the pressure distributions given by two approximate theoretical methods, and good agreement is found at the Mach numbers used.