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Aeronautical Research Council Current Papers: Recent submissions
Now showing items 621-640 of 1393
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Review of general operating experience with a jet-lift VTOL research aircraft (short S.C.1)
D. Lean
;
H. W. Chinn
(
1965
)
A survey of aircraft handling criteria
C. Leyman
;
E. R. Nuttall
(
1966
)
Turbulent-boundary-layer behaviour and the auxiliary equation
John F. Nash
(
1966
)
A unified theory of friction, heat transfer and mass transfer in the turbulent boundary layer and wall jet
D. B. Spalding
(
1965
)
Slender-body theory calculations of the effect on lift and moment of mounting the wing off the fuselage centre-line
R. S. Bartlett
(
1965
)
Further tests with a variable ramp intake having a design mach number of 2.2
M. C. Neale
;
P. S. Lamb
(
1966
)
The time required for high speed airstreams to disintegrate water drops
D. C. Jenkins
;
J. D. Booker
(
1965
)
Measurements of vortex-breakdown position at low speed on a series of sharp-edged symmetrical models
P. B. Earnshaw
(
1965
)
Experimental investigation of the breakdown of a vortex in a tube
D. L. I. Kirkpatrick
(
1965
)
A digital recording system for structural research
D. Purslow
(
1965
)
The static pressure distribution around a circular jet exhausting normally from a plane wall into an airstream
L. J. S. Bradbury
;
M. N. Wood
(
1965
)
A parametric study of take-off and landing distances for high-lift aircraft
W. A. Mair
;
B. J. Edwards
(
1965
)
Methods and charts for estimating skin friction drag in wind tunnel tests with zero heat transfer
K. G. Smith
(
1965
)
Analysis of flight loads recorded on comet 4B aircraft by means of the fatigue load meter
R. Hain Taylor
(
1965
)
Measurements of dynamic stability from three simplified free-flight models of a supersonic research aircraft (Bristol T.188) over the mach number range 1.2 - 2.6
K. J. Turner
(
1965
)
Supersonic wind tunnel tests on a 1/12th scale model of the bristol type 188 research aircraft part 1 M = 1.4 to 2.0 part 2 M = 2.0 to 2.7
C. R. Taylor
;
T. A. Cook
(
1965
)
Alleviation of thermal stresses in aircraft structures
E. C. Capey
(
1965
)
Measurements of oscillatory derivatives at mach numbers up to 2.6 on a model of a supersonic transport design study (Bristol type 198)
J. S. Thompson
;
R. A. Fail
(
1965
)
Wind tunnel tests on a 1/12th scale model of the bristol type 188 research aircraft with rectangular, wedge intakes at mach numbers from 2.0 to 2.7
T. A. Cook
(
1965
)
Measurement of air temperature on an aircraft travelling at high subsonic and supersonic speeds
A. A. Woodfield
;
P. J. Haynes
(
1965
)
Now showing items 621-640 of 1393
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