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Ultrasonic relaxation and attenuation in freons, in relation to their use in supersonic wind tunnels

Y. Miyahara; E. G. Richardson (1957)

An unconventional type of fatigue-testing machine

F. Aughtie; H. L. Cox (1953)

When any elastic system is subj ected to a range of load, the energy stored in the system fluctuates between two values corresponding to the maximum and minimum loads of the cycle. Since the driving unit usually supplies ...

A unified theory of friction, heat transfer and mass transfer in the turbulent boundary layer and wall jet

D. B. Spalding (1965)

Unsteady cavitating flow past curved obstacles

L. C. Woods (1954)

The Unsteady Forces on Finite Wings in Transient Motion. Part I. Initial Aerodynamic Forces Following a Sudden Change of Incidence. Part II. Transient Lift and Moment Functions for Rectangular and Delta Wings

B. D. Dore (1964)

Part I. The forces and moments on wings of finite aspect ratio undergoing a sudden change of incidence are considered at the start of the unsteady motion. Linearized theory is used and the flow is assumed to be incompressible. ...

Unsteady lift slope values obtained from flight measurements in gusts

D. M. Ridland (1963)

The unsteady motion of slender wings with leading-edge vortices

B. D. Dore (1965)

The unsteady response of an axial flow compressor with a distorted inlet flow

H. Mokelke (1972)

Upwash interference in a rectangular wind tunnel with closed side walls and porous slotted floor and roof

D. R. Holder (1962)

Solutions have been obtained for the upwash interference on two-dimensional aerofoils, and small-span wings, in a rectangular wind tunnel with viscous flow through the slotted floor and roof. A discussion is included on ...

Upwash interference on wings of finite span in a rectangular wind tunnel with closed side walls and porous-slotted floor and roof

D. R. Holder (1963)

An exact solution is obtained for the upwash interference on wings of finite span in a rectangular wind tunnel with dosed side walls and porous-slotted floor and roof. A resume of previous results concerning two-dimensional ...

Urea formaldehyde foamed plastic emergency arresters for civil aircraft

G. M. Gwynne (1975)

The use of a deep electrolytic tank as a lifting-surface calculator

H. S. Ward (1961)

An investigation of a deep electrolytic tank, applied as a lifting-surface calculator, has been made. The reasons for the initial choice of apparatus, and its subsequent behaviour are detailed. The calculator was developed ...

Use of a wind tunnel to determine the performance of slender wings suitable for a supersonic transport aircraft

J. Y. G. Evans (1964)

The use of air injection to prevent separation of the turbulent boundary layer in supersonic flow

D. J. Peake (1966)

The use of an araldite coated iron casting as a liner for a supersonic wind tunnel

C. S. Brown; K. G. Winter (1957)

A use of arbitrary modes in control-surface flutter investigations

T. Niblett (1967)

The use of calibrated strain gauges for flight load determination

P. B. Hovell; D. A. Webber; T. A. Roberts (1968)

An American statistical technique was evolved for the measurement of flight loads, but is of restricted use when applied to low aspect ratio multispar structures. This Report describes a modification in which a mixture of ...

Use of camber and twist to produce low-drag delta or swept-back wings, without leading-edge singularities, at supersonic speeds

G. M. Roper (1958)

Camber and twist is applied to the problem of producing low-drag wings with no leading-edge pressure singularities, at design lift. The suction peaks near the leading edges of the wing are removed and the associated adverse ...

The use of conical camber to produce flow attachment at the leading edge of a delta wing and to minimize lift-dependent drag at sonic and supersonic speeds

J. H. B. Smith; K. W. Mangler (1957)

In an attempt to avoid flow separation at the leading edge of a thin delta wing with subsonic leading edges, an attachment line is prescribed there. This is done by requiring the load, as predicted by attached-flow theory, ...

The use of cross-correlation and power spectral techniques for the identification of the hunter MK.12 dynamic response

D. E. Fry (1970)

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