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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: ºÚÁÏÍø, The Gateway, Leicester, LE1 9BH

T: +44 (0)116 250 61 56

E: mgoman@dmu.ac.uk

W:

 

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: Reducing flight upset risk and startle response: A study of the wake vortex alert with licensed commercial pilots dc.contributor.author: Borghini, Gianluca; Ronca, Vincenzo; Giorgi, Andrea; Aricò, Pietro; Di Flumeri, Gianluca; Capotorto, Rossella; Rooseleer, Frédéric; Kirwan, Barry; De Visscher, Ivan; Goman, M. (Mikhail G.); Pugh, Jonathan; Abramov, Nikolay; Granger, Géraud; Alarcon, Diana Paola Moreno; Humm, Elizabeth; Pozzi, Simone; Babiloni, Fabio dc.description.abstract: The study aimed at investigating the impact of an innovative Wake Vortex Alert (WVA) avionics on pilots' operation and mental states, intending to improve aviation safety by mitigating the risks associated with wake vortex encounters (WVEs). Wake vortices, generated by jet aircraft, pose a significant hazard to trailing or crossing aircrafts. Despite existing separation rules, incidents involving WVEs continue to occur, especially affecting smaller aircrafts like business jets, resulting in aircraft upsets and occasional cabin injuries. To address these challenges, the study focused on developing and validating an alert system that can be presented to air traffic controllers, enabling them to warn flight crews. This empowers the flight crews to either avoid the wake vortex or secure the cabin to prevent injuries. The research employed a multidimensional approach including an analysis of human performance and human factors (HF) issues to determine the potential impact of the alert on pilots' roles, tasks, and mental states. It also utilizes Human Assurance Levels (HALs) to evaluate the necessary human factors support based on the safety criticality of the new system. Realistic flight simulations were conducted to collect data of pilots' behavioural, subjective and neurophysiological responses during WVEs. The data allowed for an objective evaluation of the WVA impact on pilots' operation, behaviour and mental states (mental workload, stress levels and arousal). In particular, the results highlighted the effectiveness of the alert system in facilitating pilots' preparation, awareness and crew resource management (CRM). The results also highlighted the importance of avionics able to enhance aviation safety and reducing risks associated with wake vortex encounters. In particular, we demonstrated how providing timely information and improving situational awareness, the WVA will minimize the occurrence of WVEs and contribute to safer aviation operations. dc.description: open access article

  • 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=5.49×106 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 aerodynami