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AERADE: Recent submissions
Now showing items 2681-2700 of 3498
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On the interaction of the transmitted shock with the boundary layer in a shock tube using argon as test gas
L. Davies
;
K. Bridgman
(
1966
)
Comparison of helicopter and aeroplane vertical accelerations in turbulence
D. A. Webber
(
1966
)
The flapping behaviour of a helicopter rotor at high tip-speed ratios
E. Wilde
;
A. R. S. Bramwell
;
R. Summerscales
(
1966
)
A note on the turbulent uniform-property hydrodynamic boundary layer on a smooth impermeable wall comparisons of theory with experiment
M. P. Escudier
;
D. B. Spalding
(
1966
)
Characteristics of high-speed wind tunnels in the United Kingdom relevant to aeroelastic-model tests
C. A. K. Irwin
(
1967
)
Analysis of hinge moment data for rectangular and near rectangular trailing edge controls at supersonic and transonic speeds
D. Isaacs
(
1966
)
A review of information on the frequency of gusts at low altitude
N. I. Bullen
(
1966
)
Turbulent boundary layer theory and its application to blade profile design
D. J. L. Smith
(
1966
)
Viscosity effects on the two-dimensional flow in cascades
J. P. Gostelow
;
A. K. Lewkowicz
;
M. R. A. Shaalan
(
1967
)
Measurements of pressure distribution and shock-wave shape on power-law bodies at a mach number of 6.85
D.H. Peckham
(
1967
)
Low-speed wind-tunnel measurements of damping in yaw (n psi) on an aspect ratio 9 jet-flap complete model
A. P. Cox
;
S. F. J. Butler
(
1967
)
A procedure for the determination of cascade characteristics
J. A. P. Stoddart
;
D. Gardner
(
1966
)
A note on skin-friction laws for the incompressible turbulent boundary layer
J. F. Nash
(
1966
)
Approximate formulae for the lift and drag of wedge aerofoil sections at high supersonic speeds
L. C. Squire
(
1966
)
Two-dimensional normal fences on a flat plate
C. S. Barnes
(
1966
)
Normal accelerations measured in the cockpit and at the C.G. of a jet transport aeroplane during flight through rough air
J. Burnham
(
1966
)
A simple flexible supersonic wind tunnel nozzle for the rapid and accurate variation of flow mach number
D. Pierce
(
1967
)
Tests on an engine installation for a slender gothic wing at M = 1.82
R. T. Griffiths
(
1967
)
Further tests on a three-stage turbine of low reaction to examine the effects of reduced rotor pitch and improved sealing
I. H. Johnston
;
D. C. Dransfield
(
1966
)
Theoretical stability derivatives for a symmetrically tapered wing of aspect ratio 3 at supersonic speeds
Doris E. Lehrian
(
1966
)
Now showing items 2681-2700 of 3498
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