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Dr Nikolay Abramov

Job: Senior Research Fellow

Faculty: Computing, Engineering and Media

School/department: School of Engineering and Sustainable Development

Research group(s): Centre for Engineering Science and Advanced Systems (CESAS)

Address: De Montfort University, The Gateway, Leicester, LE1 9BH

T: +44 (0)116 207 8694

E: nabramov@dmu.ac.uk

W: http://dmu.ac.uk

 

Research group affiliations

Centre for Engineering Science and Advanced Systems (CESAS)

Nonlinear Flight Dynamics Research Group (NFD)

Publications and outputs

  • Prediction Of Static Aerodynamic Hysteresis On A Thin Airfoil Using OpenFOAM
    Prediction Of Static Aerodynamic Hysteresis On A Thin Airfoil Using OpenFOAM Sereez, Mohamed; Abramov, Nikolay; Goman, Mikhail The paper presents computational prediction of aerodynamic hysteresis loops in static conditions for a two-dimensional aerofoil that was used as a cross-section profile for a rectangular wing with an aspect ratio of five, tested in the TsAGI T-106 wind tunnel at a Reynolds number of 𝑅𝑒=6×106 and a Mach number of 𝑀=0.15. Tests in the wind tunnel showed that minor changes in the curvature of the leading edge of the thin aerodynamic profile lead to a significant increase in the maximum lift coefficient when significant hysteresis loops appear in the aerodynamic characteristics of the wing. The computational predictions of stall aerodynamics presented in this paper are made for a two-dimensional profile using the OpenFOAM open-source code to simulate a flow based on the unsteady Reynolds-averaged Navier–Stokes equations using the Spalart–Allmaras turbulence model. The calculation results confirm the existence of loops of static aerodynamic hysteresis and bistable structures of the separated flow, and the results are qualitatively similar to the results observed experimentally on the wing with a finite aspect ratio. The file attached to this record is the author's final peer reviewed version. The Publisher's final version can be found by following the DOI link.
  • Aerodynamic Modeling for Post-Stall Flight Simulation of a Transport Airplane
    Aerodynamic Modeling for Post-Stall Flight Simulation of a Transport Airplane Abramov, Nikolay; Goman, M. (Mikhail G.); Khrabrov, A. N. (Alexander N.); Soemarwoto, B. The principles of aerodynamic modeling in the extended flight envelope, which is characterized by the development of separated flow, are outlined and illustrated for a generic transport airplane. The importance of different test techniques for generating wind tunnel data and the procedure for blending the obtained experimental data for aerodynamic modeling are discussed. Complementary use of computational fluid dynamics simulations reveals a substantial effect of the Reynolds number on the intensity of aerodynamic autorotation, which is later reflected in the aerodynamic model. Validation criteria for an extended envelope aerodynamic model are discussed, and the important role of professional test pilots with post-stall flying experience in tuning aerodynamic model parameters is emphasized. The paper presents an approach to aerodynamic modeling that was implemented in the project Simulation of Upset Recovery inAviation (2009–2012), funded by the EuropeanUnion under the seventh framework programme. The developed post-stall aerodynamic model of a generic airliner configuration for a wide range of angles of attack, sideslip, and angular rate was successfully validated by a number of professional test pilots on hexapod and centrifuge-based flight simulator platforms. The file attached to this record is the author's final peer reviewed version.; open access article
  • Impact of Ground Effect on Airplane Lateral Directional Stability during Take-Off and Landing
    Impact of Ground Effect on Airplane Lateral Directional Stability during Take-Off and Landing Sereez, M.; Abramov, Nikolay; Goman, M. (Mikhail G.) Computational simulations of aerodynamic characteristics of the Common Research Model (CRM), representing a typical transport airliner are conducted using CFD methods in close proximity to the ground. The obtained dependencies on bank angle for aerodynamic forces and moments are further used in stability and controllability analysis of the lateral-directional aircraft motion. Essential changes in the lateral-directional modes in close proximity to the ground have been identified. For example, with approach to the ground, the roll subsidence and spiral eigenvalues are merging creating the oscillatory Roll-Spiral mode with quite significant frequency. This transformation of the lateral-directional dynamics in piloted simulation may affect the aircraft responses to external crosswind, modify handling quality characteristics and improve realism of crosswind landing. The material of this paper was presented at the Seventh European Conference for Aeronautics and Space Sciences EUCASS-2017. Further work is carried out for evaluation of the ground effect aerodynamics for a high-lift configuration based on a hybrid geometry of DLR F11 and NASA GTM models with fully deployed flaps and slats. Some aspects of grid generation for a high lift configuration using structured blocking approach are discussed. Open Access journal
  • Computational Ground Effect Aerodynamics and Airplane Stability Analysis During Take-off and Landing
    Computational Ground Effect Aerodynamics and Airplane Stability Analysis During Take-off and Landing Sereez, M.; Abramov, Nikolay; Goman, M. (Mikhail G.) Computational simulations of aerodynamic characteristics of the Common Research Model (CRM), representing a typical transport airliner, are conducted using CFD methods in close proximity to the ground. The obtained dependencies on bank angle for aerodynamic forces and moments are further used in stability and controllability analysis of the lateral-directional aircraft motion. Essential changes in the lateral-directional modes in close proximity to the ground have been identified. For example, with approach to the ground, the roll subsidence and spiral eigenvalues are merging creating the oscillatory Roll-Spiral mode with quite significant frequency. This transformation of the lateral-directional dynamics in piloted simulation may affect the aircraft responses to external crosswind, modify handling quality characteristics and improve realism of crosswind landing.
  • Computational Simulation of Airfoils Stall Aerodynamics at Low Reynolds Numbers
    Computational Simulation of Airfoils Stall Aerodynamics at Low Reynolds Numbers Sereez, M.; Abramov, Nikolay; Goman, M. (Mikhail G.) Experimental results for aerodynamic static hysteresis at stall conditions obtained in the TsAGI's T-124 low-turbulence wind tunnel for NACA0018 are presented and analysed. Computational predictions of aerodynamic static hysteresis are made using the OpenFOAM simulations considering di erent grids, turbulence models and solvers. Comparisons of compu- tational simulation results with experimental wind tunnel data are made for 2D NACA0018 and NACA0012 airfoils at low Reynolds numbers Re = (0.3-1.0) millions. The properties of the proposed phenomenological bifurca- tion model for simulation of aerodynamic loads at the existence of static hysteresis are discussed.
  • Flight Envelope Expansion via Active Control Solutions for a Generic Tailless Aircraft
    Flight Envelope Expansion via Active Control Solutions for a Generic Tailless Aircraft Abramov, Nikolay; Bommanahal, Mallesh; Chetty, S.; Goman, M. (Mikhail G.); Kolesnikov, E. N.; Murthy, P V Satyanarayana Aircraft dynamics at high angles of attack due to loss of stability and control essentially limits its manoeuvrability. Modern control systems implement flight envelope protection at the cost of maneuverability to improve safety in these conditions. Flight envelope boundaries, which are set taking into account deterioration of stability and controllability due to separated flow, can be expanded by appropriate design of control laws. However, such a design requires extensive analysis of the maneuver envelope of the airframe and its utilization by the flight envelope protection laws. The reliability of this analysis depends on the adequate aerodynamic modeling which captures nonlinear unsteady variation of aerodynamic loads in these flight regimes. Two novel models for unsteady aerodynamics at low and high subsonic Mach numbers are described. These models and prototyping control laws are used for closed loop computational analysis. The computational methodology of clearing flight control laws for flight envelope expansion of a Generic Tailless Aircraft (GTA) is addressed
  • Synthetic Aerodynamics Modeling for Pilot Training in the Extended Flight Envelope
    Synthetic Aerodynamics Modeling for Pilot Training in the Extended Flight Envelope Murthy, P V Satyanarayana; Abramov, Nikolay; Goman, M. (Mikhail G.) Flight at high angles of attack is associated with a variety of types of aircraft departure and post stall behaviour. Every aircraft will exhibit specific set of flight characteristics in extended flight envelope. This work was motivated by the need for using flight simulator in training pilots in those high angles of attack conditions to give pilots awareness about nonlinear aircraft behaviours and peculiarities of flight at stall and above stall. Flight simulators, equipped with representative aerodynamic models covering normal and extended flight envelope can be utilised for this purpose. A special approach of building a synthetic aerodynamic model over an available high angle of attack aerodynamic model is discussed in this paper. The Synthetic modelling presented in this paper assumes complementary transformation of a number of key aerodynamic characteristics of the original aerodynamic model with an objective to diversify post stall dynamics.
  • Aerodynamic model of transport airplane in extended envelope for simulation of upset recovery
    Aerodynamic model of transport airplane in extended envelope for simulation of upset recovery Abramov, Nikolay; Goman, M. (Mikhail G.); Khrabrov, A. N. (Alexander N.); Kolesnikov, E. N.; Sidoryuk, M. E. (Maria E.); Soemarwoto, B.; Smaili, H. The paper presents the aerodynamic model in extended flight envelope for a generic airliner with under wing engines and conventional tail developed within the EU Framework Programme (FP7) research project Simulation of Upset Recovery in Aviation (SUPRA) (www.supra.aero). The SUPRA aerodynamic model is covering angles of attack beyond stall and speeds from take-off to cruise flight. The aerodynamic model in extended flight envelope developed for piloted simulation of upset prevention and recovery has been successfully validated by a number of expert pilots.
  • Final results of the supra project: Improved Simulation of Upset Recovery
    Final results of the supra project: Improved Simulation of Upset Recovery Fucke, Lars; Groen, E.; Goman, M. (Mikhail G.); Abramov, Nikolay; Wentink, M.; Nooij, Suzanne; Zaichik, L.
  • Pushing Ahead - SUPRA Airplane Model for Upset Recovery
    Pushing Ahead - SUPRA Airplane Model for Upset Recovery Abramov, Nikolay; Goman, M. (Mikhail G.); Khrabrov, A. N. (Alexander N.); Kolesnikov, E. N.; Fucke, Lars; Soemarwoto, B.; Smaili, H. One of the primary objectives of the European Union 7th Framework Program research project SUPRA – “Simulation of Upset Recovery in Aviation” – is the development and validation of the aerodynamic model of a generic large transport airplane aimed for piloted simulation in the post-stall region and upset recovery training. Modeling methods for prediction of post-stall flight dynamics, use of the wind tunnel data from different experimental facilities complemented by CFD analysis, validation criteria, nonlinear dynamics investigation and piloted simulation results are presented in this paper. The aerodynamic model was successfully validated by a number of expert pilots and found acceptable for upset recovery training.

Click here to view a full listing of Nikolay Abramov's publications and outputs.

Research interests/expertise

Flight dynamics, aerodynamic modelling, unsteady aerodynamics at separated flow conditions, identification, nonlinear dynamical systems, mathematical modelling.

Areas of teaching

  • ENGD2005 - Engineering Science 2
  • ENGD3038 – Dynamics and Control
  • ENGD1005 – Mechanical Principles

Qualifications

Nikolay Abramov graduated from Moscow Institute of Physics and Technology, the Faculty of Aeromechanics and Flight Technology with MSc degrees in 1998 (http://phystech.edu/|) and received PhD degree in Aeronautical Engineering at De Montfort University in 2005.) and received PhD degree in Aeronautical Engineering at De Montfort University in 2005.

Membership of professional associations and societies

Member of the American Institute of Aeronautics and Astronautics (AIAA), www.aiaa.org| since 2012.

Conference attendance

Pushing Ahead - SUPRA Airplane Model for Upset Recovery. N. Abramov, M. Goman, A. Khrabrov, E. Kolesnikov, L. Fucke, B. Soemarwoto, H. Smaili. AIAA Modeling and Simulation Technologies Conference, Minneapolis, Minnesota, USA, 13-16 August 2012.

Aerodynamic Model Development for Simulation of Upset Recovery of Transport Airplane.  N.Abramov, M.Goman, A.Khrabrov, B.Soemarwoto. RAeS Aerodynamics Conference - Applied Aerodynamics: Capabilities and Future Requirements. London, UK, 27 July 2010.

Externally funded research grants information

EU 7th Framework Programme research project SUPRA (2009-2012) www.supra.aero|, Researcher.

National Aerospace Laboratories CSIR-NAL, Bangalore, India (2010-2013) www.nal.res.in|, Researcher

NikolayAbramov