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The icing of compressor blades and their protection by surface heating

G. L. Shires; G. E. Munns (1955)

This paper describes an investigation into the feasibility of protecting compressor blades against ice accretion by the method of surface heating. Experiments with surface-heated inlet guide vanes and stator blades were ...

The Ideal Drag Due to a Shock Wave. Parts I and II

C. N. H. Lock (1945)

Part 1. The subject of the present note is the increase of the drag of an aerofoil which arises from the presence of limited shock waves when the forward speed lies between the so-called shock stalling speed and the velocity ...

Identification of the flutter mechanism from a large-order flutter calculation

J. C. A. Baldock (1978)

The phase differences between degrees-of-freedom in a flutter calculation are discussed. From the study of phase variations with airspeed in binary systems, a technique is evolved for identifying the essential degrees-of-freedom ...

Ignoration of distortional co-ordinates in the theory of stability and control

Duncan, W. J. (College of Aeronautics, )

Ill-conditioned flutter equations and their improvement for simulator use

E.G. Broadbent (1956)

Impact measurements on a large model of a representative landplane fuselage on water

J.E.Allen (1956)

Impedance measurements on a spinning model helicopter rotor

R. Cansdale; D. R. Gaukroger (1978)

The imperial college graphite heated hypersonic windtunnel

J. K. Harvey; R. W. Jeffery; D. C. Uppington (1971)

This report describes the design and development of a graphite-heated, continuous running, Mach 20 windtunnel which operates with Reynolds numbers between 6 x 10power4 and 5 x 10power6 per metre. Preliminary calibrations ...

Improper integrals in theoretical aerodynamics

K.W. Mangler (1952)

Improved entrainment method for calculating turbulent boundary layer development

M. R. Head; V. C. Patel (1968)

Summary. A simple integral method is presented for the calculation of two-dimensional incompressible turbulent boundary layers. Use is made of established relationships to determine values of the entrainment coefficient ...

An improved method for calculating generalised airforces on oscillating wings in subsonic flow

G. Long (1969)

A lifting-surface theory of Multhopp-type has been revised to include an improved method of spanwise integration and programmed in Fortran IV. Generalised airforces have been calculated for three wings and the effects of ...

An improved strain-gauge type of load-cell thrust transducer

D. S. Dean (1958)

This paper describes the development of a novel-type of load cell which possesses certain advantages over the normal pillar type. Sensitivity is greater since the two concentrically nested tubular load-carrying members are ...

An improved technique of stability testing in free flight at transonic speeds, applied to a non-lifting slender wing

A. P. Waterfall (1971)

The improvement in pressure recovery in supersonic wind tunnels

H. Eggink (1949)

The inefficient pressure recovery of present day supersonic wind tunnels, which leads to high costs of plant installation and operation, is discussed and methods of improvement suggested. In particular, the diffuser system, ...

An improvement of the velocity distribution predicted by linear theory for wings with straight subsonic leading edges

D. G. Randall (1959)

Improvements in petrol engine performance with ultrasonic fuel atomisation

Norster, E. R. (College of Aeronautics, )

Improvements in the fatigue strength of joints by the use of interference fits

W. A. P. Fisher; W. J. Winkworth (1952)

A study is made of the effect of interference fit in loaded holes on the fatigue strength of the associated part. Fatigue-test results are given for aluminium alloy fiat bars with a single hole loaded by a pin in double ...

In-process measurement

Loxham, J. (College of Aeronautics, )

In-process stocks for automatic transfer lines

Roberts, A. C.; Kay, E. (College of Aeronautics, )

Incompressible flow about ellipsoids of revolution

Christopher, P. A. T. (Cranfield Institute of Technology; College of Aeronautics, )

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