Browsing by Author "Lilley, G. M."

An approximate solution of the turbulent boundary layer equations in incompressible and compressible flow

Lilley, G. M. (College of Aeronautics, 1960-07)

If over the ‘outer’ region/ of the boundary layer, where the mean velocity varies but little from its value outside the shear layer, a virtual eddy viscosity is defined, which is constant over the outer region but varies ...

Experimental investigation of the interference of a body on a low aspect ratio wing of rectangular planform at a Mach number of 2

Busing, J. R.; Marson, G. B.; Lilley, G. M. (College of Aeronautics, 1955-06)

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 ...

Experiments on an induction type high speed wind tunnel driven by low pressure steam

Lilley, G. M.; Holder, D. W. (College of Aeronautics, Cranfield, 1949-03)

The performance of an induction type high speed wind tunnel driven by low pressure steam (up to 120lb. per sq.in. absolute) has been investigated up to a Mach number of about 1.7. It was found that by suitable design a ...

Ground level disturbance from large aircraft flying at supersonic speeds

Lilley, G. M.; Spillman, J. J. (College of Aeronautics, 1960-05)

The Whitham-Walkden theory for the estimation of the strength of shock waves at ground level from aircraft flying at supersonic speeds is applied to the case of a typical projected supersonic civil transport aeroplane. If ...

An investigation of the flexure-torsion flutter characteristics of aerofoils in cascade.

Lilley, G. M. (College of Aeronautics, Cranfield, 1952-05)

Part 1 of this report describes the results obtained from a series of tests on the flexure-torsion flutter characteristics of cascades of similar aerofoils having symmetrical sections. Continues … Part 2 of this report ...

An investigation of the flow in an axial compressor inlet casing and its effect on the performance of the first stage of the axial compressor

Lilley, G. M. (College of Aeronautics, 19)

Summary The present report is a continuation of an interim report dated 8th August, 1951. The latter- report dealt with the flow in a model casing whereas the present reports deals with a similar investigation on the ...

An investigation of the noise field from a small jet and methods for its reduction.

Westley, R.; Lilley, G. M. (College of Aeronautics, Cranfield., 1952-01)

Sound measurements have been made on the noise from the jet of a one inch diameter convergent nozzle at atmospheric temperature and at speeds above and below choking. The noise level and spectrum have been investigated ...

A note on the decay of aircraft trailing vortices

Lilley, G. M. (College of Aeronautics, 1964-03)

An 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 ...

On some aspects of the noise propagation from supersonic aircraft

Lilley, G. M.; Westley, R.; Yates, A. H.; Busing, J. R. (College of Aeronautics, Cranfield, 1953-02)

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 ...

On surface pressure fluctuations in turbulent boundary layers

Lilley, G. M. (College of Aeronautics, 1960-04)

Existing work on the pressure fluctuations in turbulent shear flaws is briefly reviewed with special reference to the problem of wall turbulence. An approximate theory for the pressure fluctuations on the wall under both ...

A preliminary investigation of the flow over a particular wing body combination at Mach number 2

Busing, J. R.; Lilley, G. M. (College of Aeronautics, 1955-04)

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. ...

A preliminary report on the design and performance of ducted windmills

Lilley, G. M.; Rainbird, W. J. (College of Aeronautics, Cranfield, 1956-04)

A preliminary study is made of the theoretical gain in power output obtained with a fully ducted land-land type windmill is compared with the standard unshrouded type windmill. ...

Pressure fluctuations in an incompressible turbulent boundary layer

Lilley, G. M. (College of Aeronautics, 1960-06)

The response time of wind tunnel pressure measuring systems

Lilley, G. M.; Morton, D. (College of Aeronautics, 1960-11)

The time response of a wind tunnel pressure measuring system, comprising a pressure transducer of fixed volume and a length of capillary tubing, is analysed and the results compared with experiments. It is shown that ...

A review of pressure fluctuations in turbulent boundary layers at subsonic and supersonic speeds

Lilley, G. M. (College of Aeronautics, 1963)

The equation for the pressure fluctuations in a turbulent boundary layer are derived with special reference to their values at a rigid wall. It is shown that in incompressible flow the pressure field is defined completely ...

A simplified theory of skin friction and heat transfer for a compressible laminar boundary layer

Lilley, G. M. (College of Aeronautics, 1959-01)

The compressible laminar boundary layer equations for a perfect gas in steady flow at arbitrary external Mach number and wall temperature distribution are solved approximately by the combined use of the Stewartson- Illingworth ...

Some notes on the factors influencing the possible damage to buildings due to the passage of shock waves from aircraft flying at supersonic speeds

Lilley, G. M. (College of Aeronautics, 1952)

The purpose of this note is to discuss, from the limited information available, the order of magnitude of the strength and the configuration of the shock waves, close to ground level, generated from aircraft flying et ...

Some notes on the performance of small high speed wind tunnels

Lilley, G. M. (College of Aeronautics, Cranfield, 1948-12)

There is a need for high speed wind tunnels of modest dimensions and costs in establishments teaching the fundamentals of compressible flow. This paper discussed briefly the layouts and performances of various types of ...

The use of a potential flow tank for testing axi-symmetric contraction shapes suitable for wind tunnels

Babister, A. W.; Marshall, W. S. D.; Lilley, G. M.; Sills, E. C.; Deards, S. R. (College of Aeronautics, Cranfield., 1951-04)

The report gives details of tests in the potential flow tank on a series of axi-symmetric contraction shapes. The tests were in connection with the design of the 8ft x 6ft wind tunnel and a water tunnel. Continues...

Wall pressure fluctuations under turbulent boundary layers at subsonic and supersonic speeds

Lilley, G. M. (College of Aeronautics, 1963-03)

The problem of pressure fluctuations at a rigid wall under a turbulent boundary layer has attracted much attention in the past decade. At low Mach numbers the theory is well established from the work of Kraichnan and ...

Browsing by Author "Lilley, G. M."

Browsing by Author "Lilley, G. M."

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