|Statement||by A. S. Taylor and W. F. W. Urich.|
|Series||Aeronautical Research Council (Great Britain) Reports and memoranda,, no. 3426, Reports and memoranda (Aeronautical Research Council (Great Britain)) ;, no. 3426.|
|Contributions||Urich, W. F. W., joint author.|
|LC Classifications||TL526.G7 A4 no. 3426|
|The Physical Object|
|Number of Pages||95|
|LC Control Number||67071453|
The responses of a slender supersonic transport aircraft flying through random turbulence have been evaluated for the cruise condition. The problem was simplified by assuming that the aircraft responds only in heave, pitch and longitudinal bending as defined by the fundamental normal mode and by using piston theory : E. Huntley. () Effect of elastic deformation on flight dynamics of projectiles with large slenderness ratio. Aerospace Science and Technol Online publication date: 1-DecCited by: Effect of elastic deformation on flight dynamics of projectiles with large slenderness ratio Aerospace Science and Technology, Vol. 71 Aeroservoelastic modelling and control of a slender anti-air missile for active damping of longitudinal bending vibrationsCited by: Fig. 6 shows the comparison of the predicted aerodynamic forces in three directions with the data extracted from x direction aerodynamic force agrees well with the reference data when x 30 m, the amplitude and the period gradually decline and the calculated value is a little smaller than the reference aerodynamic forces in the y and z directions both fit.
with the slender planform the slender-wing aircraft was always thought to pose considerable lateral control problems especially in the landing approach in the presence of side-gusts and/or steady cross-wind. However, flight experience on the two slender-wing research aircraft operating in this country. The Handley Page , research aircraft was designed to study the aerodynamic and handling qualities of slender wing aircraft at low speed flight conditions. This airplane experience a wing rock motion when the angle of attack exceeded approximately 20°, as shown in Fig. 2. The effects of camber and twist are felt as changes in the angle of attack for zero lift, and in the aerodynamic center pitching moment as a result of the basic lift distribution. The normal force, or lift, acting on slender, axially symmetric bodies at an angle of attack are, according to the so-called slender-body theory, distributed along the body in accordance. In designing an airplane a great deal of effort is spent in developing the desired degree of stability around all three axes. But longitudinal stability about the lateral axis is considered to be the most affected by certain variables in various flight conditions. As we learned earlier, longitudinal stability is the quality which makes an airplane stable about its lateral axis.
This paper reviews an extensive programme of experimental work which was aimed at the production of integrated slender wings which had volume distribu. Wing Body type of aircraft symmetrical sections with a This work was conducted in order to document the X longitudinal and lateral- directional linear aero model at numerous trim flight. The actuated abdomens of insects such as dragonflies have long been suggested to play a role in optimisation and control of flight. We have examined the effect of this type of actuation in the simplified case of a small fixed wing aircraft to determine whether energetic advantages exist in normal flight when compared to the cost of actuation using aerodynamic control surfaces. We explore the. F.G. IRVING , D.I.C., S., in An Introduction to the Longitudinal Static Stability of Low-Speed Aircraft, All-moving Tails. High-speed aeroplanes frequently use all-moving tails, where the angle η T is directly controlled by the movements of the pilot's control column. If the tailplane is moved via an irreversible power-control system, stick-free stability is no longer of.