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The influence of flow parameters on minimum ignition energy and quenching distance
No full textExperiments have been carried out on the effects of pressure,
velocity, mixture strength, turbulence intensity and turbulence
scale on minimum ignition energy and quenching distance. Tests
were conducted at room temperature in a specially designed closedcircuit tunnel in which a fan was used to drive propane/air
mixtures at subatmospheric pressures through a 9 cm square working section at velocities up to 50 m/s. Perforated plates located at
the upstream end of the working section provided near-isotropic
turbulence in the ignition zone ranging from 1 to 22 percent in
intensity, with values of turbulence scale up to 0.8 cm.
Ignition was effected using capacitance sparks whose energy and
duration could be varied independently
Aeroplane design studies mach 2.2 and mach 3.0 supersonic airliners (academic years 1960 and 1962)
No full textThis report is divided into three parts. The first two of these describe the A-60,
Mach 2.2 airliner and the A-62, Mach 3.0 airliner design studies respectively. Apart
from the different cruise speeds these two aircraft were designed to meet the same
basic requirements and the third part of the report is a comparison of them.
The Mach 2.2 design was based upon the use of a slender, integrated, delta layout
with six turbojet engines buried in the rear fuselage. It was intended to carry up to 120
passengers over transatlantic ranges. Although the chosen engine installation enabled
a compact aircraft to be designed it did introduce severe structural and installation
difficulties.
A canard delta arrangement was proposed for the Mach 3.0 aircraft. Drooping
of the wing tips for supersonic flight was found to confer important stability advantages
without introducing an unacceptable weight penalty. The steel structure was designed
around the use of both corrugated reinforced and honeycomb sandwich skins, the former
being preferable. An interesting feature was the choice of a sealed, cryogenic, environmental
control system. This was found to be very attractive but as it proved to be
somewhat heavier than anticipated it is suggested that a good compromise could be
obtained by using a more conventional system for subsonic flight phases.
The major conclusion from the comparison between the two study aircraft was
that in many respects there is very little to choose between them. However the Mach
2.2 aircraft represents a more logical step from existing airliner designs and presents
fewer materials problems. As it is comparable economically it represents a better
choice for a first generation supersonic design
A note on some equipment used for boundary layer measurements in flight. Part 1, the design and construction of a large multitube manometer for use in flight. Part 2, two fixed head type combs for boundary layer investigations
No full textSome notes are presented relating to the design
and construction of a large multitube manometer and to two
'fixed head' type boundary layer combs to be used for the
measurement in flight of the boundary layer characteristics
of a swept back wing. Although the equipment described was
designed with a particular object in view, there is no
reason why the designs should not be modified as and where
necessary for the construction of similar equipment
Shock reflection and surface effects in the shock tube
No full textA 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
Drilling system design project 1967: final report of frame design committee
No full textThis report outlines the recommendations of the Frame
Design Committee for the final design of the machine, each
major part of the structure being considered individually
in the following sections :
1. Worktables
2. Guide and Slideways
3. Drill Head Support Structure
4. Swarf Disposal and Coolant Supply
5. General Constructio
A note on the decay of aircraft trailing vortices
No full textAn elementary theory of aircraft trailing vortex decay is presented
based on an assumed law for the variation of the mean eddy viscosity with
distance from the wing. This law is based on the experimental data of
Rose and Dee (1.963). The analysis gives results, as might be expected,
in agreement with their data. The justification for the analysis must
however be in doubt until more data are available covering a wide range of
variables such as aircraft size, distance, incidence, etc
Test report no. PLBO/9: comparison of PERPRO tools RD92 against Sanvik S1P under roughing conditions
No full textTools of grade RD92 and S1P were tested to 0.030 in. flank wear when machining EN9 at 300 fpm with 0.030 in/rev, feed and 0.10 in. depth of cut. The results showed that while there was no significant difference in tool life between the two grades, RD92 suffered greater
crater wear and nose deformation than did S1P
An investigation of the assembly of transistor cores: first year project 1964/65
No full text1. Introduction
This project was carried out for the Texas Instrument Company of
Bedford/ by members of the Ergonomics/ Operational Research and Management
sections at Cranfield. Texas Instruments wanted to increase production
of doUble alloy transistors by 25%. The increase could not be achieved
by hiring extra operators because the amount of floor space was limited.
The problem facing the group therefore was one of expanding output by
increasing the efficiency and productivity of the existing operators ... [cont.]