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The purpose of this paper is to focus on the variation of wake structures and aerodynamic forces with changes in the cylinder corner radius and orientation.

Numerical simulations were performed for flow past a square cylinder with different corner radii placed at an angle to the incoming flow. In the present study, the rounded corner ratio R/D=0 (square cylinder), 0.1, 0.2, 0.3, and 0.4 (where R is the corner radius and D is the characteristic dimension of the body) and the angle of incidence α in the range of 0°-45° were considered.

The numerical model was validated by comparing the present results with results in the available literature, and they were found to be in good agreement. The critical incidence angle for the rounded corner cylinder – corresponding to the minimum mean drag coefficient (C _D ), the minimum root mean square value of the lift coefficient C _L,RMS), and the maximum Strouhal number – shifted to a lower incidence angle compared with the sharp corner square cylinder. The minimum drag and lift coefficient at R/D=0 were observed for the critical incidence angle α_cri=12°, whereas for R/D=0.1-0.4, the minimum drag and lift coefficient were found to be within the range of 5°-10° for α.

The presented results shows the importance of the incidence angle and rounded corners of the square cylinder for reduction of aerodynamic forces. The two parameters support the shear layer flow reattachment on the lateral surface of the cylinder, have a strong correlation with the reduction of the wake width, and hence reduced the values of C _D and C _L .

THE complete study of the tail spin divides itself into four distinct parts: the entry into the spin, the steady spin maintained by the action of the controls, the uncontrolled spin, and the recovery from the spin. In this paper we will limit ourselves to the study of the uncontrolled tail spin, i.e., the spin which has reached the state of steady motion, and persists in it with controls neutralized, or even against controls. When we speak about steady motion, we imply that all forces and moments are in a state of complete equilibrium, and that there are no accelerations. The study of the uncontrolled spin is therefore the study of equilibrium in spin. If the proportions of an aeroplane are such as to make possible equilibrium in spin with controls set for recovery, there evidently will be no recovery, because recovery means lack of balance and resulting acceleration. In order to be safe the aeroplane must be proportioned so as to make equilibrium in tail spin impossible, unless the controls are set lor spinning.

This paper aims to study the energy ratios of plane waves on an interface of nonlocal thermoelastic halfspace (NTS) and nonlocal orthotropic piezothermoelastic half-space (NOPS).

The memory-dependent derivatives (MDDs) approach with a hyperbolic two-temperature (HTT), three-phase lag theory is used here to study how the energy ratios change at the interface with the angle of incidence.

Plane waves that travel through NTS and hit the interface as a longitudinal wave, a thermal wave, or a transversal wave send four waves into the NOPS medium and three waves back into the NTS medium. The amplitude ratios of the different waves that are reflected and transmitted are used to calculate the energy ratios of the waves. It is observed that these ratios are affected by the HTT, nonlocal and MDD parameters.

The energy ratios correspond to four distinct models; nonlocal HTT with memory, nonlocal HTT without memory, local HTT with memory and nonlocal classical-two-temperature with memory concerning the angle of incidence from 0 degree to 90 degree.

This model applies to several fields, including earthquake engineering, soil dynamics, high-energy particle physics, nuclear fusion, aeronautics and other fields where nonlocality, MDD and conductive temperature play an important role.

The authors produced the submitted document entirely on their initiative, with equal contributions from all of them.

THE development of modern aeroplanes designed for high speeds, with their thin, almost symmetrical wing sections, has led inevitably to high landing speeds and small gliding angles with the normal wing arrangement.

The purpose of this study is to investigate the reflection of plane waves in a double-porosity (DP) thermoelastic medium.

To derive the theoretical formulas for elastic wave propagation velocities through the potential decomposition of wave-governing equations. The boundary conditions have been designed to incorporate the unique characteristics of the surface pores, whether they are open or sealed. This approach provides a more accurate and realistic mathematical interpretation of the situation that would be encountered in the field. The reflection coefficients are obtained through a linear system of equations, which is solved using the Gauss elimination method.

The solutions obtained from the governing equations reveal the presence of five inhomogeneous plane waves, consisting of four coupled longitudinal waves and a single transverse wave. The energy ratios of reflected waves are determined for both open and sealed pores on the stress-free, the thermally insulated surface of DP thermoelastic medium. In addition, the energy ratios are compared for the cases of a DP medium and a DP thermoelastic medium.

A numerical example is considered to investigate the effect of fluid type in inclusions, temperature and inhomogeneity on phase velocities and attenuation coefficients as a function of frequency. Finally, a sensitivity analysis is performed graphically to observe the effect of the various parameters on propagation characteristics, such as propagation/attenuation directions, phase shifts and energy ratios as a function of incident direction in double-porosity thermoelasticity medium.

The purpose of this paper is to study the propagation of inhomogeneous waves in a partially saturated poro-thermoelastic media through the examples of the free surface of such media..

The mathematical model evolved by Zhou et al. (2019) is solved through the Helmholtz decomposition theorem. The propagation velocities of bulk waves in partially saturated poro-thermoelastic media are derived by using the potential functions. The phase velocities and attenuation coefficients are expressed in terms of inhomogeneity angle. Reflection characteristics (phase shift, loci of vertical slowness, amplitude, energy) of elastic waves are investigated at the stress-free thermally insulated boundary of a considered medium. The boundary can be permeable or impermeable. The incident wave is portrayed with both attenuation and propagation directions (i.e. inhomogeneous wave). Numerical computations are executed by using MATLAB.

In this medium, the permanence of five inhomogeneous waves is found. Incidence of the inhomogeneous wave at the thermally insulated stress-free surface results in five reflected inhomogeneous waves in a partially saturated poro-thermoelastic media. The reflection coefficients and splitting of incident energy are obtained as a function of propagation direction, inhomogeneity angle, wave frequency and numerous thermophysical features of the partially saturated poro-thermoelastic media. The energy of distinct waves (incident wave, reflected waves) accompanying interference energies between distinct pairs of waves have been exhibited in the form of an energy matrix.

The sensitivity of propagation characteristics (velocity, attenuation, phase shift, loci of vertical slowness, energy) to numerous aspects of the physical model is analyzed graphically through a particular numerical example. The balance of energy is substantiated by virtue of the interaction energies at the thermally insulated stress-free surface (opened/sealed pores) of unsaturated poro-thermoelastic media through the bulk waves energy shares and interaction energy.

The purpose of this paper is to investigate the influence of a propeller slipstream on the aerodynamic characteristics of a fixed-wing micro air vehicle (MAV) by simplifying a propeller to an actuator disk and an actuator volume.

A computational fluid dynamic (CFD) approach.

The simulation flows are found and show that the propeller slipstream changes the flow field around the wing, which improves the aerodynamic performance of the wing. The aerodynamic performance is improved first, when the separation of the boundary flow at the upper surface wing is delayed. Second, the flow region of the boundary layer is boosted close to the wing surface again at a high incidence angle. And finally, the velocity inlet of the wing is increased by the propeller-induced flow.

The incidence angle is in the range of 0-80°with an increment of 20°. The free stream velocity and RPM used are 6 m/s and 5,000 rpm, respectively.

A propeller is simplified to an actuator disk and an actuator volume.

In this paper a comprehensive survey of spinning phenomena is attempted. The presentation is elementary in character, starting with the simple geometry of the spin, then dealing with autorotation, including wing‐dropping tendencies, passing on then to a consideration of aerodynamic pitching and yawing moments, and finally some attention is given in turn to the incipient spin, the steady spin and recovery. The arguments are in the main qualitative so that a student of the subject may first familiarise himself with the fundamental principles. A bibliography is given which includes all the important papers published on the subject within the last few years, together with a few which are now more of historical interest. Most of these reports emanate from the A.R.C. and N.A.C.A. and due acknowledgment is made of the source of some of the experiments which have been taken in illustration of the points made. Although not the urgent problem that it once was, the subject of the spinning of aeroplanes continues to occupy a prominent place in the programmes of various research establishments, both here and abroad. Because both of the complexity of the phenomena involved and of the great importance that an ultimate solution should be found it has continued to be since the war one of the most difficult and protracted problems in aeronautics. Owing to the body of experimental data which has been gradually built up, model and full scale, designers now know what peculiar properties in an aeroplane are liable to prove dangerous as far as recovery is concerned. There is unfortunately no mathematical precision about this process and the fact that machines can still be built which, unless they are tested in the spinning tunnel and the necessary modifications made, might become uncontrollable in a spin should be sufficient to indicate that a final solution is far front having been achieved. It seems exceedingly unlikely that there will ever be sufficient experimental evidence to enable a designer to predict confidently that his machine, if it be perfectly orthodox, will not have some vicious spinning tendency. On the other hand, any designer could build a perfectly safe aeroplane from the point of view of spinning if due regard had not to be paid to other items of performance and safety. The necessity for compromise in design becomes a major problem when spinning is one of the factors that have to be taken into account. There is ample evidence that this problem is being resolutely tackled by designers. All the same, the present position cannot be regarded as satisfactory and, unless some new device is produced which will remove autorotation from the possible regimes of an aeroplane, we must continue to progress along already well‐tried lines.

This paper aims to study the impact of pyro-electricity, moisture and temperature diffusivity on the energy distribution of plane waves at the free surface of an orthotropic piezo-hygro-thermo-elastic medium.

This study presents the novel creation of governing equations for an anisotropic piezothermoelastic medium with moisture impact, which is a significant contribution of this paper.

In addition to providing numerical data for the amplitude ratios and energy ratios of reflected waves, this study identifies five different kinds of coupled reflected plane waves, namely, quasi-longitudinal P wave, quasi-thermal wave, quasi-transverse wave, quasi-moisture wave and electric potential wave.

The graphical analysis examines the impact of various factors, such as the angle of incidence, moisture and temperature diffusivity, pyro-electricity and frequency, on energy distribution.

This paper's results significantly impact the development of more efficient piezoelectric materials and their applications in geophysics.

The authors of the submitted document initiated and produced it collectively, with equal contributions from all members.

A helicopter tail rotor is required to provide yaw control and essentially that alone. However, it is expected to achieve that role when placed in an aerodynamically difficult location on the aircraft and to operate in a severe aerodynamic environment. This paper describes the pedal travel behaviour caused by aerodynamic interaction between the main rotor wake, the sideways velocity and subsequent forces generated by the tail boom noticed in Sea King helicopters, operating in extreme conditions during the Falklands war. Using earlier research which showed the effectiveness of a modification – a strake – to interrupt the air flow over the tail boom, conducts tests to examine the flow, the effects of the modification, and the side suction force. It also finds that the strake provides a simple and cost‐effective solution to the problem.