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Effect of slipstream on longitudinal stability of multi-engined aircraft

Morris, D.E. (author), Morrall, J.C. (author)

Flight measurements of longitudinal stability power off and power on made on numerous aircraft have been analysed and a generalised curve for estimating the contribution of slipstream to longitudinal stability, applicable to both flaps up and flaps down cases, has been derived. Using this curve the change in stability due to slipstream at a...

report 1948

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Note on the Efficiency of Adiabatic Shock

Morley, A.W. (author)

This note records some calculations of the efficiency of adiabatic shock in air (Y = 1.40) ; where the efficiency is defined as the ratio of the work used to compress the air in the shock wave, from the inlet static to the outlet total head pressure, to the work required if the compression v/ere isentropic. This is the efficiency usually of...

report 1948

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The Efficiency of Adiabatic Expansion

Morley, A.W. (author)

The efficiency of a process of compression or expansion of a gas is commonly defined in terms of the change in energy which occurs as compared with the change required in isentropic flow. In another method the efficiency may be defined' in terms of the fraction of the mechanical work lost in friction and converted into heat. Alternatively, if...

report 1948

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Flutter of Systems with Many Freedoms

Duncan, W.J. (author)

Experience has shown that it is often necessary to retain many degrees of freedom in order to calculate critical flutter speeds reliably, but this entails much labour. Part I discusses the choice of a minimum set of freedoms and suggests that this should be based on the equation of energy and the use of the Lagrangian dynamical equation...

report 1948

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On the Integration of Hyperbolic Differential Equations

Robinson, A. (author)

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

report 1948

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Simple formulae for predicting the weights of wing, fuselage, and tail unit structures

Grinsted, F. (author)

The weights of wing, fuselage, and tail unit structures are expressed independently by simple formulae, by means of which predictions can be made quickly of the structure weights of project designs. The formulae are in terms of important dimensions and design features, and have been derived by analysis of the weights of current civil and...

report 1948

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The relative accuracy of quadrature formulae of the Cotes' closed type

Kirkby, S. (author)

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

report 1948

document

The relative accuracy of quadrature formulae of the Cote's closed type

Kirkby, S. (author)

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

report 1948

document

Prediction of wing structure weight

Grinsted, F. (author)

Expressions for wing structure weight are derived in terms of the important parameters in wing structural design. The main wing structure is treated by relating it to an ideal structure and a measure of structural efficiency is obtained. Though the expressions are derived froml past experience it is thought that they can be applied to new forms...

report 1948

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On a theory of sandwich construction

Hemp, W.S. (author)

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

report 1948

document

Assessment of errors in approximate solutions of differential equations

Duncan, W.J. (author)

The term assessment is applied to any process which enables us to set rigid bounds to the error or to estimate its value. It is shown that upper and lower bounds can be assigned whenever the Green' s function of the problem is one-signed; this is true in many important problems. Another method is applicable to step by step solutions of ordinary...

report 1947

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The aerodynamic derivatives with respect to sideslip for a delta wing with small dihedral at supersonic speeds Addendum

Robinson, A. (author), Hunter-Tod, J.H. (author)

Expressions are derived for the sideslip derivatives on the assumptions of the linearised theory of flow for a delta wing with small dihedral flying at supersonic speeds. A discussion is included in the appendix on the relation between two methods that have been evolved for the treatment of aerodynamic force problems of the delta wing lying...

report 1947

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Bound and trailing vortices in the linearised theory of supersonic flow, and the downwash in the wake of a delta wing

Robinson, A. (author), Hunter-Tod, J.H. (author)

The field of flow round a flat aerofoil at incidence can be regarded in linearised theory as the result of both bound and trailing vortices for supersonic as well as for low speed flight. This leads to a convenient method, given the lift distribution over an aerofoil, for calculating the flow round it at supersonic speeds. As an application of...

report 1947

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On source and vortex distributions in the linearised theory of steady supersonic

Robinson, A. (author)

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

report 1947

document

Application of the linear perturbation theory to compressible flow about bodies of revolution

Young, A.D. (author), Kirkby, S. (author)

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

report 1947

document

Note on the velocity and temperature distributions attained with suction on a flat plate of infinite extent in compressible flow

Young, A.D. (author)

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

report 1947

document

Wing body interference at supersonic speeds

Kirkby, S. (author), Robinson, A. (author)

The increment in lift due to wing-body interference at supersonic speeds is calculated approximately for an untapered wing, without sweepback. The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

report 1947

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The effect of the sweepback of Delta wings on the performance of an aircraft at supersonic speeds

Robinson, A. (author), Davies, F.T. (author)

The variation with sweepback of the total drag of an aircraft in level flight at supersonic speeds is calculated. It is shown that sweepback is not uniformly beneficial but that in general the optimum amount of sweepback depends on the design speed and altitude. The College of Aeronautics was founded in 1946 and was granted university status in...

report 1947

document

Note on the dynamics of a slightly deformable body

Hemp, W.S. (author)

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University

report 1947

document

Technique of the step-by-step integration ordinary differential equations

Duncan, W.J. (author)

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

report 1947