A technique of calculation of aircraft condensation trails (contrails) and wake vortices interaction is described. The technique is based on a suitable for real-time applications mathematical model of far wake utilizes the method of discrete vortices. The technique is supplemented by account of the influence of axial velocities in the vortex nucleus on contrail and wake vortex location. Results of calculations of contrails and wake vortices interaction for Il-76 and B-747 aircraft are presented.

Calculation results of influence of functional systems refusals on takeoff and landing of plane Il-96T using mathematical modeling.

Research paper is devoted to the description of a new modification of the algorithm for calculating the vortex filaments motion. The results of methodological studies showing that this algorithm can correctly simulate the elongation, shortening, bending and reconnection of vortex filaments, as well as known qualitative phenomena arising from the vortex rings interaction are given. Particular attention is paid to the repetition of the calculation recently investigated experimentally the evolution of bound vortices. It is shown that with the developed algorithm can be steadily modeled complex vortex loops evolution. The main advantage of the new algorithm is stability and high-speed computing.

The paper shows possibility of implementing the open source CFD software package OpenFOAM for calculation of unsteady vortex flows in researching of flow past cylinder with plate. Flow structure and aerodynamic characteristics have been obtained, and evaluation of the perturbations caused by the vortex shedding from the surface of cylinder has been conducted. Method of flow control in the region of the near wake has been proposed.

In this paper, the preliminary results of computational modeling of an aircraft with the airbrake deployed are presented. The calculations were performed with OpenFOAM software package. The results outlined are a part of a research project to optimise aircraft performance using a perforated airbrake. Within this stage of the project OpenFOAM software package with hybrid RANS-LES approach was tested in respect to a given configuration of the aircraft, airbrake and then has been compared with the test data. For the worst case the amplitude of the peak force acting on the tail fin can be up to 6 times higher than the average value without airbrake deployed. To reduce unsteady loads acting on the tailfin, perforation of the airbrake was proposed.

Influence of various design data of jet controls (amount of jets, a direction of injection, geometrical characteristics of nozzles, their mutual position, etc.) on flow structure and flying vehicles aerodynamic characteristics is defined and recommendations on optimum use of jet injection as a way of control of flow near flying vehicles are developed.

The problem of noise generation of rotor due to the thickness of blades - displacement noise is considered. The method of calculating the displacement noise, which is based on linear acoustic theory for the changes in the effective thickness of the blade over time due to the compressibility of the flow are described.

Calculations of the perturbed velocity field and induced turbulence due to the motion of the ship in the atmospheric surface layer based on gradient wind are presented in this paper.

The article deals with the task of determination of wing shape for sub-sonic commercial aircraft by photogrammetric method. It provides the procedure for measurements taken on ground and in flight. It also provides the outcome of wing twist for commercial aircraft at cruise.

The article considers the task of competitiveness prolongation for the aircraft put into operation. It describes the means to increase aerodynamic efficiency of commercial aircraft and provides the outcome of regional aircraft modification.

The article conducted research, using the simulation PFD stand to determine dangerous combination "height - flight speed" for gyroplane and developed preliminary recommendations on the actions of the pilot in the event of failure of the gyroplane power plant.

The present publication describes the calculation of helicopter fuselage aerodynamic characteristics and its separate elements, by computing experiment. On the basis of program commercial package CFX ANSYS the technique has been mastered and longitudinal and lateral characteristics of the helicopter fuselage on the various flight modes are calculated.

The article is devoted to an assessment of danger degree of a flight situation with the engine failure on the ascending maneuvers using natural- model approach and expert evaluation in the absence of the possibility of using a pilotage stand.

The analysis of the impact of limited size areas on the aerodynamic characteristics of the rotor obtained using previous studies and some of the results of modern experimental research are given.

The article shows the peculiarities and disadvantages of the classical single-fuselage configuration aircraft for local lines. It also provides an overview of the twin-fuselage configuration aircraft. A version of the twin-fuselage passenger aircraft is offered and the ground of its advantages is given.

One of the main stages of the creation of seaplanes and amphibious aircraft are flight certification tests, including tests to determine their landing and sailing characteristics on the water. In accordance with aviation regulations (part 21) certification work is carried out according to the methods of determination of compliance (MOC), which are the main organizational and methodological document for testing. The paper discusses the main provisions of the standard methods for the determination of the runway and sea keeping characteristics of seaplanes and amphibians on water areas with full-scale tests.

This article describes validation procedure of the birds throw into gas-turbine engine (GTE) simulation model and the preceding verification of its main components. The provided data are including predictive and experimental data, as an additional documentary proof of the simulation model fidelity, repeatability and sensitivity.

For the evaluation of the tolerance of output parameters of the controls functional subsystem the hydraulic system under different operating conditions and phases of flight are given mathematical relationships and the results obtained in Mathcad are given in graphical form.

Experimental and theoretical methods of studying life characteristics of metal-composite high-pressure cylinders are considered. It is shown that the stiffness of a load-bearing composite shell has a considerable effect on service life of the cylinders. Experimental results and their comparison with data of theoretical calculations are presented.