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Low-speed wind-tunnel experiments on a series of sharp-edged delta wings

P. B. Earnshaw; J. A. Lawford (1964)

A series of six delta wings of varying angles of sweepback has been tested. A three-component strain-gauge balance was used to investigate the forces and moments, and normal-force fluctuations for incidences between ± 60°. ...

Possio's subsonic derivative theory and its application to flexural-torsional wing flutter parts 1 and 2

R. A. Frazer; Sylvia W. Skan (1942)

Part I. Possio's Derivative Theory for an Infinite Aerofoil Moving at Subsonic Speeds. The derivative theory due to C. Possio for an infinite aerofoil moving at subsonic speeds is reviewed, and certain modifications are ...

Effects of longitudinal elastic camber on slender aircraft in steady symmetrical flight Parts I and II

A. S. Taylor; W. F. W. Urich (1964)

PART I Estimation of the Effect of Longitudinal Elastic Camber on Trim and Manoeuvrability of Slender Aircraft. An approximate method of estimating the effect of aeroelasticity on the longitudinal trim and quasi-steady ...

Flight measurements of the drag of a swept-wing aircraft (hunter Mk. 1) at mach numbers up to 1.2, together with some measurements of lift-curve slope

D. R. Andrews; J. E. Nethaway (1955)

Flight tests have been made to determine the drag of a Hawker Hunter F Mk. I aircraft. The results show that at low Mach number the drag coefficient at zero lift is 0.0125 and the effective induced-drag factor K is 1.09, ...

Measurements of the direct pitching-moment derivatives for three wing planforms at high subsonic speeds

J. B. Bratt; W. G. Raymer; J. E. G. Townsend (1953)

Measurements of the direct pitching damping and stiffness derivatives for a delta and two swept wing planforms made in the N.P.L. 9½ in. High Speed Tunnel are discussed, and results for the delta are compared with theory. ...

Boundary-layer separation in supersonic propelling nozzles

M. V. Herbert; R. J. Herd (1964)

A comparison has been made between the pressure rise at separation in convergent-divergent nozzles and that in other models with supersonic flow and a turbulent boundary layer. In the case of nozzles with uniform divergence, ...

Generalised aerodynamic forces on a T-tail oscillating harmonically in subsonic flow

D. E. Davies (1964)

The T-tail under investigation consists of a flat horizontal tailplane mounted on top of a flat vertical fin. The chords of the two surfaces at their junction are of the same length and are coincident. The T-tail is assumed ...

An investigation of the flow about circular cylinders placed normal to a low-density, supersonic stream

S. C. Metcalf; C. J. Berry; B. M. Davis (1964)

The pressure distribution around circular cylinders has been measured near M∞ = 2, for Reynolds numbers between 5 and 135. The induced pressure due to viscous effects has been estimated using a 'tangent-cylinder' method ...

The prevention of binary flutter by artificial damping

R. A. Frazer (1944)

Formulae are obtained which provide an estimate of the amount of artificial control needed to prevent binary flutter. Results are expressed in terms of a 'minimum damping multiplier' R, defined as the ratio of the least ...

A theoretical treatment of noise and non-linearities in a beam-riding system

E. G. C. Burt (1951)

The effectiveness of a beam-riding missile is greatly influenced by the mutual effect of noise and nonlinearities. The former is mostly due to radar jitter, while the principal non-linearity is that introduced by limiting ...

On the statistical optimisation of guided-weapon systems

E. G. C. Burt; R. W. Bain (1954)

The statistical nature of the input to a guided-weapon system (target information and noise) requires that the criterion of weapon performance be itself a statistical quantity. The criterion used in this paper is the mean ...

Oscillatory aerodynamic forces in linearised supersonic flow for arbitrary frequencies, planforms and mach numbers

D. J. Allen; D. S. Sadler (1963)

A method is described of performing a numerical integration to solve the integral equation connecting downwash an d velocity potential in linearised unsteady supersonic flow. Supersonic and subsonic leading edges and wakes ...

Transonic compressor noise the effect of inlet guide vane/rotor spacing

D. A. Kilpatrick; D. T. Reid (1964)

Comprehensive noise measurements were made in the inlet duct of a model of a typical two-stage transonic fan. The tests covered a range of variations in the inlet guide/rotor axial spacing from normal, in small increments, ...

Calculation of unsteady generalised airforces on a thin wing oscillating harmonically in subsonic flow

D. E. Davies (1963)

A method of obtaining numerical values of generalised airforces on a thin wing oscillating harmonically in subsonic flow is described. It is assumed that the linearised equations of potential flow are valid. The essence ...

Some exploratory measurements of leading-edge vortex positions on a delta wing oscillating in heave

R. L. Maltby; P. B. Engler; R. F. A. Keating (1963)

Some measurements of vortex-core height for a heaving delta wing at high incidence are presented. A method of flow visualization using smoke was specially developed for this investigation, and a simple theory for the ...

The supersonic flow past a circular cone at incidence

B. A. Woods (1963)

The problem of calculating the supersonic flow past a circular cone at small incidence α is treated by the method of inner and outer expansions, on the assumption that it can be expressed as a perturbation (in powers of ...

Lift due to interference between an aerofoil and an external non-lifting body

S. Neumark (1964)

This paper contains an attempt to explain the incremental negative or positive lift induced on an aerofoil by an external non-lifting body (such as an engine nacelle), as observed in some experiments. A two-dimensional ...

Forces on aerofoils with both incidence and forward speed varying

D. G. Randall (1964)

Determination of the inviscid, incompressible flow due to a thin, two-dimensional aerofoil moving with varying incidence and forward speed requires the solution of an integral equation. This report examines the case of ...

Structural damage caused by impulsive loads a theoretical analysis

E. H. Mansfield (1964)

A general theoretical technique is presented for the estimation of structural damage caused by impulsive loads. The technique, though approximate, takes account of differences that may exist between the elastic and plastic ...

Graphical treatment of binary mass-balancing problems

R. A. Frazer (1942)

A graphical method, based on 'classical' flutter theory, is described which provides a simple test of the effectiveness of mass-balancing in the prevention of flutter at various heights. Illustrative applications are made ...

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