
Pavel MakeevMoscow Aviation Institute · Department of Aeronautical Engineering
Pavel Makeev
Ph.D of Engineering Sciences
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23
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Publications (23)
The original free vortex wake model was used for numerical investigation. Calculation of the aerodynamic characteristics in hover and vertical descent modes in the range of vertical descent speed of 0–30 m/s including the Vortex Ring State (VRS) area was performed. The calculations were carried out under the condition of variable blade pitch angle...
This paper considers the Mi-8 helicopter main rotor aerodynamics when flying near the infinite ground surface. The research is based on the free wake model developed by authors at Moscow Aviation Institute. The distance from the rotor's hub to the ground surface in the range of H = 6-16 m and the values of free stream (flight) velocity in the range...
Numerical studies of the aerodynamic characteristics of the coaxial main rotor of the Kamov Ka-32 helicopter in steep descent modes, including the area of the vortex ring state (VRS) modes, have been performed. Used in this paper is an original free vortex wake model of the rotor developed by the authors. The angles of attack of the rotor αR = 30 –...
This paper is dedicated to the numerical modeling of the aerodynamic characteristics of the full-scale coaxial main rotor. The modes of forward flight in the range of values V = 30−60 m∙s–1 (108−216 km∙h–1) have been under consideration. The simulation has been performed with the usage of two computational fluid dynamics (CFD) approaches: the free...
The vortex ring states are observed when the rotor is flowed at positive angles of attack. For the main rotor, these conditions are realized during a steep descent of the helicopter at low speeds. The rotor vortex ring states are affected by significant phenomena related to the behavior of its aerodynamics, including negative phenomena. The latter...
The presented work is dedicated to the development of the mathematical model of a closed-type wind tunnel (WT) in a two-dimensional (2D) formulation based on the computational fluid dynamics (CFD) Unsteady Reynolds Averaged Navier Strokes Equations (URANS) method. The influence of the WT walls perforation percentage on the aerodynamic characteristi...
A computational model of a wind tunnel (WT) with a special experimental rig has been developed directly for studying unsteady aerodynamic characteristics of a wing section with a helicopter blade profile. The model was constructed using CFD (Computational Fluid Dynamics) methods based on the URANS approach (Unsteady Reynolds Averaged Navier Strokes...
The research has been focused on aerodynamic characteristics of the Mi-8 helicopter main rotor in the hover and steep descent modes at rotor angles of attack αR = 90-30º, including vortex ring state area. The research is based on the original free wake model developed by the authors at Moscow Aviation Institute. Total and distributed aerodynamic ch...
The aerodynamic characteristics of three types of 6-bladed main rotors (MR) are calculated on the basis of the free vortex wake model. We focused on conventional, coaxial counter-rotating and coaxial co-rotating types of rotor. The vortex wake shapes and induced velocity fields in the rotors jet are analyzed. It is shown that rotational component o...
The article analyzes the problematic issues associated with the transition of universities to distance learning during a pandemic.
The paper is focused on numerical modeling of the aerodynamic characteristics of a full-scale coaxial main rotor in hover. The simulation was performed using two approaches of computational fluid dynamics (CFD): the original free wake model (FWM) developed by the authors and the unsteady Reynolds-averaged Navier–Stokes (URANS) equations method base...
The presented work is dedicated to the numerical study of the aerodynamic characteristics of the helicopter rotor. Two approaches to modeling of the rotor are applied: the free wake model developed by the Authors with using steady airfoil characteristics and the Unsteady RANS method based on the Ansys Fluent software. The modes of hovering and hori...
A method based on the complex application of the actuator disk and finite-blade vortex theories is presented for aerodynamic design of the pusher propeller of a promising rotorcraft for vertical takeoff and landing. The software package was created that allows us to select the propeller parameters, create its 3D model and calculate aerodynamic char...
The research has been conducted into aerodynamic performance of the MIL Mi-8 helicopter main rotor in the hover and steep descent modes at rotor angles of attack αR = 90…30º, including vortex ring state (VRS) area. Total and distributed aerodynamic performance, rotor wake shapes and airflow line pictures have been calculated. Based on the results a...
The main rotor operation is studied of the Mi-8 single-rotor helicopter in steep descent modes at the rotor angles of attack αR = 90−30 deg. The study resulted in total and distributed aerodynamic performance, rotor wake patterns and flow patterns. The vortex ring state area is designed based on the result analysis in terms of some features. The ca...
The efficiency of the helicopter main rotor in the hover mode is very important, because this mode essentially determines the performance characteristics of the helicopter. A feature of the helicopter rotor aerodynamics is a significant inductive blade influence that highly defines its aerodynamic characteristics. The problem of the influence of th...
The research is conducted of aerodynamic performance of the Mi-8 helicopter main rotor in the hover state and the vertical descent state, including vortex ring states (VRSs). Total and distributed aerodynamic performance, wake patterns, and main rotor flow patterns are calculated. The findings and results were compared with those provided by other...
The Mi-2 helicopter was taken as an example for modeling the main and tail rotors operation with account for the interference at low speed sliding flight. Aerodynamic characteristics were calculated. The form of nonlinear vortical wake was obtained.