Justification of possibility of application of an OpenFOAM package for obtaining aerodynamic characteristics of bluff bodies and studying of their dependence on geometrical parameters.

A mathematical model of the specific fuel consumption of the TV3-117 based thermogasdynamic calculation that takes account of the design of engine parts.

To evaluate the operational tolerance field hydraulic output parameters under various working conditions and the flight stages are mathematical relationships and the results obtained in the environment Mathcad in graphical form.

The linear vortical model ot the final scope of a wing is exsamined. It representis the flat rectangular spatial veil covered with continuously distributed vortical layer. Elements of digitization of a veil are the quadrangular panels laying on its surface. Method, algorithms and the program of calculation of three making vectors of inductive speed from any guided rectangular platform covered with a vortical layer are created. Its intensity linearly changes on the surface of a platform. The decision is received in elementary functions. The numerical way solves the task of a definition of the law of circulation of the attached whirlwinds in scope of a wing and calculation of its aerodynamic characteristics, being based on the accepted vortical model and a hypothesis of flat sections.

The numerical method of calculation of aerodynamic characteristics of a profile is stated on the basis of the experiment of aerodynamic characteristics of a rectangular wing of a final lengthening. The problem is solved by a method consecutive approximation with the use of a matrix of private derivative factors of elevating force and aerodynamic resistance of a wing under the appropriate characteristics of a profile.

In this paper numerical investigation of airodynamic characteristics (Суа, Сха, mz, K) of non-modified (without partitions) and modified (with partitions) profiled plate with flap are presented. Different pitch angles of flap were considered. Comparison of results showed increase of pitching moment and lift coefficient for modified plate.

The results of numerical research of a soft type airship aerodynamic characteristics in subsonic flow of viscous gas are received for the airship locating near to a screen and having the working propellers. The influence of propeller rotation and relative distance of the airship to the screen on values of its aerodynamic normal and longitudinal forces, and also pitching moment is shown at various airship angles of attack.

This article is concentrated on modeling and researching of aerodynamic characteristics of main and tail rotors’ combination of a single-rotor helicopter scheme. Non-linear free wake vortical model with diffusion of free wake is used. The model is constructed on the base of Helicopter Design Faculty, MAI. There was analyzed a number of special flight regimes of a helicopter. There were counted aerodynamic characteristics of rotors.

On the basis of methods of computing aerodynamics (CFD) research by definition of aerodynamic effects from the strake on a tail boom of cylindrical section is conducted and the estimation of the constants and variable forces operational depending on the strake angular rule.

The present publication describes the results of the first stage of the flying laboratory (Mi-171 helicopter) flight tests performed at Mil Moscow Helicopter Plant, JSC facilities. Main rotor components with blades made of polymer composite materials and X-type tail rotor were tested on the Mi-171 № 14987, flying laboratory, under Mi-171A Helicopter Retrofit Program.

The calculation of turbulent flow using LES model and prediction of sound generated by a rod-airfoil configuration was done using OpenFoam code and library libAcoustics. Good results are obtained for frequency and drag coefficients compared with results from experiment. The additional investigation need to be performed for improvement of SPL results.

The results of acoustic characteristics of the main rotor, in particular the thickness noise are presented. The influences of geometric and kinematic parameters on the thickness noise are investigated.

Presented methodology to the design and check calculations of an isolated propeller for mini-UAV based on the vortex theory of Zhukovsky. Results of the calculation of propeller mini-UAVs and their comparison with results matching propeller on a normal chart. Shows the effect of Re, as well as the degree of reduction in the aerodynamic and geometric characteristics of the propeller.

– an angle of attack of the main rotor). The vortex ring state has been considered also.

The calculation and experimental investigations of an external fuel tank influence on longitudinal and lateral aerodynamic characteristics of the light transport cryoplan model has been executed. Tank influence on drag coefficient and lift-drag ratio of the model is presented. It's revealed the essential decreasing the model directional stability due to tank installation. Technical solutions intended for increasing cryoplan's directional stability are developed and preliminarily investigated.

The paper considers methodological issues related to determining of hydrometeorological conditions, which are maximum permissible for operation of see-based aircrafts. Flight-test methods are proposed to obtain the corresponding restrictions on the aircraft performance.

Velocity vector indication at HUD is effective technique for fulfilling carrier landing and landing on short runway. The command glide slope value and carrier velocity are added to traditional algorithm of the velocity vector indication. This make a possibility of carrier landing without using optical landing system (OLS), at heavy deck motion and significant side wind.

In-flight simulation method of the aircraft carrier landing was developed for the purpose of terms reduction and increase of flight training safety. The image of the simulated carrier and optical landing system are reproduced at the HUD. Flight training is conducted at some safety height. This training technique can be fulfilled without real carrier and its landing equipment. During the flight a pilot can fulfill simulation of the carrier landing unlimited times. Simulation of the carrier landing is continued up to moment when virtual hook touch the virtual deck.

The results of the analysis of the applicability of known application software systems for automated synthesis of fuzzy control traffic light UAV during its flight in adverse weather conditions. The solution is based on a previously formulated and put into consideration the principle of permissible limited a priori estimation of the uncertainty of aerodynamic characteristics of UAVs.

The Couette-Taylor flow of compressible gas at high Reynolds numbers is studied. Problem statement is formulated on the basis of the differential equation system (the Navier-Stockes equations) for compressible gas in cylindrical coordinates. On the basis of physical model built in CFD, the numerical results for various temperatures of the cylinder’s surfaces and rotational speed are obtained. The relation between vortice dimensions and surface temperatures and rotational speed is established.

Introduction to the results of a numerical study buffeting on Onera M6 wing. The determination of condition to appear buffeting of the modes of oscillation of a shock when interacting with in the boundary layer at Mach numbers and angles of attack.

There is the statement of a problem of visualization of instructions of topside controller to sea-based air crew while training on pilot-in-the-loop simulator.