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Professor Mikhail Goman

Job: Professor of Dynamics

Faculty: Computing, Engineering and Media

School/department: School of Engineering and Sustainable Development

Research group(s): Centre for Engineering Science and Advance Systems (CESAS), Nonlinear Flight Dynamics Research Group (NFD)

Address: ذكذكتسئµ, The Gateway, Leicester, LE1 9BH

T: +44 (0)116 250 61 56

E: mgoman@dmu.ac.uk

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Personal profile

Mikhail Goman joined De Montofrt University in 1997 being invited and funded by the Defence Evaluation and Research Agency (known as DERA), UK and QinetiQ, Ltd. He is Professor of Dynamics since 2000 at the Faculty of Technology. His research and scientific career started in 1972 at the Central Aerohydrodynamic Institute (TsAGI, ), named after Prof N.E.Zhukovsky, in Russia. He had an extensive experience in aerodynamic modelling and nonlinear flight dynamics with special focus on critical flight regimes in extended flight envelope. For this cycle of works and practical applications he was awarded in 1992 the Zhukovsky Gold medal, the highest aeronautical accolade in Russia, for the best work in Theory of Aviation.

Mikhail Goman is a Co-Director of the newly established Centre for Engineering Science and Advanced Systems (CESAS) at the Faculty of Technology and Head of Nonlinear Flight Dynamics Research Group, which is involved in research collaboration with a number of world famous research Institutions such as TsAGI, Russia and the National Aerospace Laboratories (CSIR-NAL), India. Recently, he was leading the development of the aerodynamic model of a generic airliner in extended flight envelope as a part of the European Union 7th Framework Programme research project SUPRA (2009-2012), Simulation of UPset Recovery in Aviation (). This project was aimed at creating new simulation technologies (aerodynamic modelling, motion cueing and simulator driving algorithms) in support of pilot training on available flight simulators in extended flight envelope, where stalled flight conditions may lead to the Loss-of-Control in Flight (LOC-I), the major cause of flight catastrophes in modern transport aviation. The developed SUPRA extended aerodynamic model was highly ranked by the invited technical experts from the NASA Langley Research Centre and the Boeing Company. 

Research group affiliations

Centre for Engineering Science and Advance Systems (CESAS)

Nonlinear Flight Dynamics Research Group (NFD)

Publications and outputs


  • dc.title: Prediction of aerodynamic characteristics of high-lift Common Research Model in ground effect dc.contributor.author: Sereez, Mohamed; Abramov, Nikolay; Goman, M. (Mikhail G.) dc.description.abstract: Reynolds Averaged Navier-Stokes (RANS) simulations are performed to investigate the aerodynamic characteristics of the NASA Common Research Model (CRM) in its high-lift (HL) configuration in close proximity to the ground. The RANS simulations are conducted at a moderate Reynolds number of Re=5.49أ—106 and M=0.2 with the use of the Spalart-Allmaras (SA) turbulence model. out of ground effect (OGE) simulation results are validated against available wind tunnel data before proceeding to in ground effect (IGE) simulations. The obtained computational results in the immediate vicinity of the ground with asymmetric aircraft attitudes demonstrate significant changes in the longitudinal and lateral-directional aerodynamic characteristics, which should be taken into account in flight dynamics analysis of aircraft during take-off and landing in crosswind conditions. dc.description: open access article

  • dc.title: Wing Rock Prediction in Free-to-Roll Motion Using CFD Simulations dc.contributor.author: Sereez, Mohamed; Lambert, Caroline; Abramov, Nikolay; Goman, M. (Mikhail G.) dc.description.abstract: The free-to-roll wing rock CFD simulation of a slender 80-degree delta wing is performed using the Dynamic Fluid-Body Interaction (DFBI) framework and the overlap/chimera mesh method. The purpose of the simulations carried out was to test the capabilities of the current CFD methods for predicting wing rock motion over a wide range of angles of attack, including strong conical vortex interactions and vortex breakdown phenomenon. The predictions of steady aerodynamic dependencies and the aerodynamic stability derivatives based on forced oscillation tests along with the time histories of the wing rock motion of an 80-degree delta wing are in good qualitative and quantitative agreement with the available wind tunnel experimental data demonstrating onset of the wing rock motion. At higher angles of attack with vortex breakdown CFD simulations demonstrated an excitation of the large amplitude regular oscillations or the low amplitude chaotic oscillations depending on the applied initial conditions.

  • dc.title: A modified dual time integration technique for aerodynamic quasi-static and dynamic stall hysteresis dc.contributor.author: Sereez, Mohamed; Abramov, Nikolay; Goman, M. (Mikhail G.) dc.description.abstract: Simulation of the aerodynamic stall phenomenon in both quasi-static and dynamic conditions requires expensive computational resources. The computations become even more costly for static stall hysteresis using an unsteady solver with very slow variation of angle of attack at low reduced frequencies. In an explicit time-marching solver that satisfies the low Courant number condition, that is, CFL<1, the computational cost for such simulations becomes prohibitive, especially at higher Reynolds numbers due to the presence of thin-stretched cells with large aspect ratio in the boundary layer. In this paper, a segregated solver method such as the Semi-Implicit Method for Pressure-Linked Equations (SIMPLE) is modified as a dual pseudo-time marching method so that the unsteady problem at each time step is reformulated as a steady state problem. The resulting system of equations in the discretized finite volume formulation is then reduced to zero or near-zero residuals using available convergence acceleration methods such as local time stepping, multi-grid acceleration and residual smoothing. The performance and accuracy of the implemented algorithm was tested for three different airfoils at low to moderate Reynolds numbers in both incompressible and compressible flow conditions covering both attached and separated flow regimes. The results obtained are in close agreement with the published experimental and computational results for both quasi-static and dynamic stall and have demonstrated significant savings in computational time. dc.description: open access article

  • dc.title: Investigation of Aerodynamic Characteristics of a Generic Transport Aircraft in Ground Effect Using URANS Simulations dc.contributor.author: Sereez, Mohamed; Abramov, Nikolay; Goman, M. (Mikhail G.) dc.description.abstract: This paper focuses on computational prediction of aerodynamic and the flow field characteristics for NASA Common Research Model (CRM) in it’s High-Lift (HL) configuration in close proximity to the ground. The URANS simulation with the Spalart-Allmaras (SA) turbulence model is checked for the quality of the generated mesh and compared with the available wind tunnel data. The obtained simulation results in the immediate vicinity of the ground demonstrate significant changes in the longitudinal and lateral-directional aerodynamic characteristics in aircraft banked positions, which is important for a better understanding of aircraft landing in crosswind conditions. dc.description: This papers contributes to the methodology of the Impact Case Study submitted by ذكذكتسئµ to the REF2021 "Enhancing Pilot Training and Flight Safety Through Improved Aerodynamic Modelling and Prediction of Nonlinear Flight Dynamics" (rated 3*).

  • dc.title: Evaluation of Aerodynamic Characteristics in Oscillatory Coning Using CFD Methods dc.contributor.author: Sereez, Mohamed; Goman, M. (Mikhail G.) dc.description.abstract: The wind tunnel rotary-balance testing is widely used in aircraft dynamics to characterise aerodynamics at moderate and high angles of attack during stall and spin regimes. In such experiments an aircraft test model is rotated along the wind-tunnel free-stream velocity vector allowing the measurement of aerodynamic characteristics in steady rotational flow conditions with constant angle of attack and sideslip. In modified tests named as oscillatory coning, the rotation vector is tilted from the free-stream velocity vector making flow conditions with periodic variations in angle of attack and sideslip. This allows evaluation of unsteady aerodynamic responses superimposed on steady conical rotation. The use of CFD methods for prediction of aerodynamic characteristics in rotary-balance and oscillatory coning conditions may significantly complement experimental data via extrapolation of data for higher Reynolds numbers, elimination of interference effects from supporting system, extraction of unsteady aerodynamic derivatives affecting aircraft dynamic stability. This paper presents CFD simulation results obtained in rotary-balance and oscillatory coning motions for the NASA Common Research Model (CRM) in its wing-body configuration at moderate ً‌‘…ً‌‘’ = 1 أ— 10^6 , low Mach number ً‌‘€=0.2 and the use of the obtained unsteady responses in aerodynamic modelling. dc.description: This paper contributes to the methodology of the REF2021 Impact Case Study "Enhancing Pilot Training and Flight Safety Through Improved Aerodynamic Modelling and Prediction of Nonlinear Flight Dynamics" submitted by ذكذكتسئµ (rated 3*).

  • dc.title: Prediction Of Static Aerodynamic Hysteresis On A Thin Airfoil Using OpenFOAM dc.contributor.author: Sereez, Mohamed; Abramov, Nikolay; Goman, M. (Mikhail G.) dc.description.abstract: 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 ً‌‘…ً‌‘’=6أ—106 and a Mach number of ً‌‘€=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. dc.description: 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.

  • dc.title: Aerodynamic Modeling for Post-Stall Flight Simulation of a Transport Airplane dc.contributor.author: Abramov, Nikolay; Goman, M. (Mikhail G.); Khrabrov, A. N. (Alexander N.); Soemarwoto, B. dc.description.abstract: 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 modelling that was implemented in the project Simulation of Upset Recovery in Aviation (2009–2012), funded by the European Union 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. dc.description: The file attached to this record is the author's final peer reviewed version.; open access article

  • dc.title: Experimental investigation of aerodynamic hysteresis using a 5-DoF wind tunnel manoeuvre rig dc.contributor.author: Gong, Z.; Araujo-Estrada, Sergio A.; Lowenberg, M. H.; Neild, Simon; Goman, M. (Mikhail G.) dc.description.abstract: The high-incidence aerodynamics of a lightweight jet trainer aircraft model has been investigated using a novel five-degree-of-freedom (DOF) dynamic maneuver rig, recently updated with improved actuation and data acquisition systems, in the 7 أ— 5 ft closed-section low-speed wind tunnel at the University of Bristol. The major focus was to identify the nonlinear and unsteady aerodynamic characteristics specific to the stall region and which affect free-to-move aircraft-model behavior. First, the unstable equilibrium states in the limit-cycle regions were stabilized, and so observed, over a wide range of angles of attack using a simple elevator feedback control lawbased on pitch angle and pitch-rate sensor measurements. Tests with two DOF, namely, the aircraft model and rig-arm pitch angles, revealed the existence of static hysteresis in the normal force acting on the aircraft model in the stall region. Unlocking the aircraft model in roll and yaw accompanied by feedback stabilization of the lateral–directional modes of motion demonstrated the onset of asymmetric aerodynamic rolling and yawing moments in this four-DOF configuration. This observation implicitly indicates a link between the static hystereses in the normal aerodynamic force with an onset of aerodynamic asymmetry. The experimental results show the efficiency of the updated multi-DOF actively controlled maneuver rig in providing insight into complicated aerodynamic effects within the stall region. dc.description: Open Access article

  • dc.title: Impact of Ground Effect on Airplane Lateral Directional Stability during Take-Off and Landing dc.contributor.author: Sereez, Mohamed; Abramov, Nikolay; Goman, M. (Mikhail G.) dc.description.abstract: 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. dc.description: Open Access journal

  • dc.title: Synthetic Turbulence Modeling for Evaluation of Ultrasonic Cross-Correlation Flow Measurement dc.contributor.author: Gurevich, A.; Goman, M. (Mikhail G.); Gurevich, Y.G.; Lopez, A.M. dc.description.abstract: Performance of an ultrasonic cross-correlation flow measurement instrument may be significantly affected by turbulence at the location of the ultrasonic sensors. In this paper, a new method of generating Synthetic Turbulence is presented, to provide an effective tool for creating a variety of turbulent fields, which can be used to model and analyze instrument performance under different flow conditions. In the proposed method, a turbulent field is presented as a Fourier time-series in each point in space. Turbulence structures are defined by a spatial distribution of phase functions for each harmonic. Principles of designing a phase function to achieve the desirable distribution of turbulence scales, and two-point correlations, are outlined by considering the example of Uniform Isotropic Turbulence. One application of this method, presented in this work, is the mathematical modeling of ultrasonic cross-correlation flow measurement. Results predicted by the proposed mathematical model show good agreement with experimental data. dc.description: 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

Key research outputs

1) J. Pattinson, M. H. Lowenberg, and M. G. Goman. Investigation of poststall Oscillations of an Aircraft Wind-Tunnel Model, Journal of Aircraft (accepted for publication).

2)  J. Pattinson, M. H. Lowenberg, and M. G. Goman. A Multi-Degree-of-Freedom Wind Tunnel Manoeuvre Rig for Dynamic Simulation and Aerodynamic Model Identification, Journal of Aircraft, Vol. 50, No. 2, March-April 2013.

3)  M. G. Goman, A. V. Khramtsovsky, and E. N. Kolesnikov.  Evaluation of Aircraft Performance and Maneuverability by Computation of Attainable Equilibrium Sets,Journal of Guidance, Control, and Dynamics, Vol. 31, No. 2, March–April 2008, pp. 329-339.

4)  M.G. Goman and A.V. Khramtsovsky. Computational framework for investigation of aircraft nonlinear dynamics,Advances in Engineering Software, Vol. 39, Issue 3, March 2008, pp.167-177, Elsevier Ltd.

5)  M. E. Sidoryuk, M. G. Goman, S. Kendrick, D. J. Walkerand P. Perfect.  An LPV Control Law Design and Evaluation for the ADMIRE Model, in the Book “Nonlinear Analysis and Synthesis Techniques for Aircraft Control”, Lecture Notes in Control and Information Sciences, Springer, 2008, ISSN 0170-8643, pp.197-229.

6)  M. G. Goman, A. V. Khramtsovsky and E. N. Kolesnikov Investigation of the ADMIRE Manoeuvring Capabilities Using Qualitative Methods, in the Book “Nonlinear Analysis and Synthesis Techniques for Aircraft Control”, Lecture Notes in Control and Information Sciences, Springer, 2008, ISSN 0170-8643, pp.301-324.

Research interests/expertise

Computational methods for investigation of critical flight regimes (high incidence departure, spin, inertia roll-coupling, flutter, etc.);

Modelling of unsteady aerodynamics at separated flow conditions (experimental and mathematical phenomenological methods);

Stabilisation of unstable systems under bounded control, control solutions for flight envelope protection, departure prevention, spin recovery, flutter suppression, etc.

Areas of teaching

Mechanical Principles, Dynamics & Control, Dynamics of Nonlinear Systems.

Qualifications

Mikhail Goman graduated from Moscow Institute of Physics and Technology, the Faculty of Aeromechanics and Flight Technology with MSc degrees in 1972 (). He then joined  the Central Aerohydrodynamic Institute (TsAGI), Russia (|), where he received PhD degree in 1978. 

Courses taught

Module leader for "Dynamics & Control"

Membership of external committees

RAeS International Committee in Aviation Training in Extended Envelope, ICATEE (2010-present)

NASA LaRC Loss-of-Control in Flight Research Working Group (2012-present)

Membership of professional associations and societies

Senior Member of the American Institute of Aeronautics and Astronautics (SMAIAA)

Conference attendance

1) N.Abramov, M.Goman, A.Khrabrov, E.Kolesnikov, B.Soemarwoto, L.Fucke, H.Smaili.  Aerodynamic Model of Transport Airplane in Extended Envelope for Simulation of Upset Recovery, ICAS 2012-3.1.2, 28th Congress of the International Council of the Aeronautical Sciences, 23-28 September 2012, Brisbane, Australia.

2) M.Bommanahal, M.Goman. Nonlinear Unsteady Aerodynamic Modeling by Volterra Variational Approach, AIAA 2012-4654, AIAA Atmospheric Flight Mechanics Conference, 13-16 August, Minneapolis, Minnesota.

3)  N.B.Abramov, M.G.Goman, A.N.Khrabrov, E.N.Kolesnikov, L.Fucke, B.Soemarwoto, H.Smaili. Pushing Ahead – SUPRA Airplane Model for Upset Recovery, AIAA 2012-4631, AIAA Modeling and Simulation Technoloies Conference, 13-16 August, Minneapolis, Minnesota.

4) E.N.Kolesnikov and M.G. Goman. Analysis of Aircraft Nonlinear Dynamics Using Non-Gradient Based Numerical Methods and Attainable Equilibrium Sets, AIAA 2012-4406, AIAA Atmospheric Flight Mechanics Conference, 13-16 August 2012, Minneapolis, Minnesota.

5) N.B. Abramov, M.G.Goman, E.N.Kolesnikov, and M.E.Sidoryuk.  Investigation of Attainable Equilibrium Sets for Clearance of Flight Control Laws, AIAA 2010-491, 48th AIAA Aerospace Science Meeting, 4-7 January 2010, Orlando, Florida.

6) E.L.Groen, M. Wentink, M. Mayrhofer, H. Smaili, B.I.Soemarwoto, M.Goman, H.H.Bulthoff.  Outline of Research Project “SUPRA” on the Simulation of Upset Recovery,The Royal Aeronautical Society Spring 2009 Flight Simulation Conference Flight Simulation: Towards The Edge of the Envelope, 3-4 June 2009.

 7) M.N.Demenkov and M.G.Goman.  Bifurcation Control of Aeroelastic Limit Cycle Oscillations, Chaos 09Second IFAC meeting related to analysis and control of chaotic systems, London 22-24 June 2009.

8) M.G. Goman and M.N.Demenkov. Multiple Attractor Dynamics in Active Flutter Suppression Problem, Seventh International Conference on Mathematical problems in Engineering & Aerospace Sciences, ICNPAA 2008, Edited by Seenith Sivasundaram, Siena, June 2008, pp. 1042-1051. 

 9) K.Vikhorev, M.G. Goman and M.N.Demenkov, Effect of Control Constraints on Active Stabilization of Flutter Instability, Seventh International Conference on Mathematical problems in Engineering & Aerospace Sciences, ICNPAA 2008, Edited by Seenith Sivasundaram, Siena, June 2008, pp. 1042-1051.

10) J.Pattinson, M.H.Lowenberg, and M.G.Goman.  A Dynamic Rig for the Wind Tunnel Evaluation of Novel Flying Vehicles The Royal Aeronautical Society The Aerodynamic Conference The Aerodynamics of Novel Configurations Capabilities and Future Requirements 27th -29th October 2008.

11) M.N.Demenkov and M.G.Goman.  Suppressing Aeroelastic Vibrations via Stability Region Maximization and Numerical Continuation Technique, Proceedings of the International Conference on Control 2008 (UKACC), Manchester, UK, September 2-4, 2008.

Consultancy work

Consultancies in the form of short professional courses, software development, mathematical modelling for Mikoyan and Sukhoi Design Companies, Flight Research Institute, Russia, (1972--1992), ShenYang Aircraft Design and Research Institute, the P.R.China (1992--1993), Aeronautical Development Agency (ADA), India (1994--1996), Defence Evaluation Research Agency (DERA) UK, 1993-2001, QinetiQ Ltd (2002 -2004), National Aerospace Laboratories, CSIR-NAL, India (2010-2013).

Current research students

International PhD programme (part time):

Bommanahal, Mallesh Vithappa, NAL, India (1st supervisor)

Pudi, Venkata Satyanarayana Murthy, NAL, India (1st supervisor)

Gurevich, Alexander, AMAG Inc., Canada (1st supervisor)

Liu, Jianming, NUAA, Nanjing, China (1st supervisor)

Zheng, Gong, NUAA, Nanjing, China (1st supervisor)

Full time:

Bailey, Richard (2nd supervisor)

Externally funded research grants information

EU 7th Framework Programme research project SUPRA (2009-2012) ().

National Aerospace Laboratories CSIR-NAL, Bangalore, India (2010-2013, 2013-2014) ().

Russian Ministry of Higher Education and Science, International Grant (2012-2013) jointly with TsAGI ().

Professional esteem indicators

Member of Editorial body of Journal Nonlinear Studies ().

Reviewer for AIAA Journal of Aircraft, Journal Guidance, Control and Dynamics, the RAeS Aeronautical Journal, TsAGI’s Visualization of Mechanical Processes, Beggell House Inc, USA.

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