Pavel Vladimirovich Chuvakhov
Current Organizations / Institutes
The organizations/institutes from the scholar's latest article
Previous Organizations / Institutes
The organizations / institutes from the scholar's other articles in the past ten years
Pavel Vladimirovich Chuvakhov has a total of 20 co-authors. Here are the top co-authors by number of shared publications:
- Alexander Vitalyevich Fedorov
Moscow Institute of Physics and Technology
5 shared publications - I. O. Pogorelov
Central Aerohydrodynamic Institute (TsAGI), National Research Center “Zhukovsky Institute”, Zhukovskii, Russia
4 shared publications - Anton O. Obraz
Zhukovskii Central Aerohydrodynamic Institute, Zhukovskii, Russia
3 shared publications Herbert Olivier
RWTH Aachen University
3 shared publicationsI. V. Egorov
Moscow Institute of Physics and Technology
3 shared publications- I. V. Egorov
Moscow Institute of Physics and Technology, Zhukovskii, Russia
3 shared publications
Latest Publications
- 1 June 2026
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 64 (6) , 3613-3617
Analysis of the HIFiRE-1 Transition Experiment Using the Amplitude Method
- 1 June 2026
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 64 (6) , 3613-3617
Analysis of the HIFiRE-1 Transition Experiment Using the Amplitude Method
- 18 March 2025
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 1007, A27
Statistical model of laminar–turbulent transition onset caused by atmospheric particulates
Within the frameworks of the amplitude method and the linear stability theory, a statistical model of the initial stage of laminar–turbulent transition caused by atmospheric particulates (aerosols) penetrating into the boundary layer is developed. The model accounts for the process of boundary layer receptivity to particulates, asymptotic behaviour of unstable wave packets propagating downstream from particle–wall collisions and the amplitude criterion for the transition onset. The resulting analytical relationships can be used for quick predictions of the transition onset on bodies of relatively simple shape, where the undisturbed boundary layer is quasi-two-dimensional. The model allows us to explore the transition onset at realistic distributions of the particle concentration selected based on an analysis of known empirical data. As an example, a 14° half-angle sharp wedge flying in atmosphere at 20 km altitude and Mach number 4 is considered. It is shown that the transition onset corresponds to an N-factor of 15.3 for a flight under normal atmospheric conditions and 12.2 for a flight in a cloud after volcanic eruption. In accordance with physical restrictions, these values are below the upper limit $N\approx 16.8$ predicted for transition due to thermal fluctuations (perfectly ‘clean’ case). Nevertheless, they are significantly greater than $N=10$ which is commonly recommended for estimates of the transition onset in flight.- 18 March 2025
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 1007, A27
Statistical model of laminar–turbulent transition onset caused by atmospheric particulates
Within the frameworks of the amplitude method and the linear stability theory, a statistical model of the initial stage of laminar–turbulent transition caused by atmospheric particulates (aerosols) penetrating into the boundary layer is developed. The model accounts for the process of boundary layer receptivity to particulates, asymptotic behaviour of unstable wave packets propagating downstream from particle–wall collisions and the amplitude criterion for the transition onset. The resulting analytical relationships can be used for quick predictions of the transition onset on bodies of relatively simple shape, where the undisturbed boundary layer is quasi-two-dimensional. The model allows us to explore the transition onset at realistic distributions of the particle concentration selected based on an analysis of known empirical data. As an example, a 14° half-angle sharp wedge flying in atmosphere at 20 km altitude and Mach number 4 is considered. It is shown that the transition onset corresponds to an N-factor of 15.3 for a flight under normal atmospheric conditions and 12.2 for a flight in a cloud after volcanic eruption. In accordance with physical restrictions, these values are below the upper limit $N\approx 16.8$ predicted for transition due to thermal fluctuations (perfectly ‘clean’ case). Nevertheless, they are significantly greater than $N=10$ which is commonly recommended for estimates of the transition onset in flight.- 19 October 2024
- Published by The Russian Academy of Sciences in Izvestiâ Akademii nauk. Rossijskaâ akademiâ nauk. Mehanika židkosti i gaza
- No. 2,p. 113-125
Numerical simulation of the interaction between weak shock waves and supersonic boundary layer on a flat plate with the blunt leading edge
The interaction of weak shock waves in form of an N-wave with the supersonic laminar boundary layer on a flat plate with blunt leading edge at the free-stream Mach number M = 2.5 is numerically studied. The numerical results are compared with known experimental data. The combined influence of the N-wave and the leading edge bluntness on the laminar-turbulent transition process is discussed.
- 19 October 2024
- Published by The Russian Academy of Sciences in Izvestiâ Akademii nauk. Rossijskaâ akademiâ nauk. Mehanika židkosti i gaza
- No. 2,p. 113-125
Numerical simulation of the interaction between weak shock waves and supersonic boundary layer on a flat plate with the blunt leading edge
The interaction of weak shock waves in form of an N-wave with the supersonic laminar boundary layer on a flat plate with blunt leading edge at the free-stream Mach number M = 2.5 is numerically studied. The numerical results are compared with known experimental data. The combined influence of the N-wave and the leading edge bluntness on the laminar-turbulent transition process is discussed.
- Open Access
- 10 May 2024
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 986, E1
Numerical modelling of supersonic boundary-layer receptivity to solid particulates – CORRIGENDUM
- 10 May 2024
- Published by Cambridge University Press (CUP) in Journal of Fluid Mechanics
- Vol. 986, E1
Open AccessNumerical modelling of supersonic boundary-layer receptivity to solid particulates – CORRIGENDUM
- Open Access
- 1 April 2024
- Published by Pleiades Publishing Ltd in Fluid Dynamics
- Vol. 59 (2) , 279-290
Numerical Simulation of the Interaction between Weak Shock Waves and Supersonic Boundary Layer on a Flat Plate with the Blunt Leading Edge
The interaction of weak shock waves in form of an N -wave with the supersonic laminar boundary layer on a flat plate with blunt leading edge at the free-stream Mach number M = 2.5 is numerically studied. The numerical results are compared with known experimental data. The combined influence of the N -wave and the leading edge bluntness on the laminar-turbulent transition process is discussed.
- 1 April 2024
- Published by Pleiades Publishing Ltd in Fluid Dynamics
- Vol. 59 (2) , 279-290
Open AccessNumerical Simulation of the Interaction between Weak Shock Waves and Supersonic Boundary Layer on a Flat Plate with the Blunt Leading Edge
The interaction of weak shock waves in form of an N -wave with the supersonic laminar boundary layer on a flat plate with blunt leading edge at the free-stream Mach number M = 2.5 is numerically studied. The numerical results are compared with known experimental data. The combined influence of the N -wave and the leading edge bluntness on the laminar-turbulent transition process is discussed.
- 1 December 2023
- Published by Pleiades Publishing Ltd in Fluid Dynamics
- Vol. 58 (6) , 969-979
Interaction of Acoustic Disturbances with the Flat-Plate Supersonic Boundary Layer
Numerical simulation of the receptivity of a supersonic boundary layer on a flat pointed plate with respect to model acoustic disturbances that propagate in the free-stream flow (Mach number is equal to 5) and are characteristic of the background noise of shock wind tunnels is carried out within the framework of the full Navier–Stokes equations. Spectral analysis of the perturbations induced in the boundary layer is carried out. A method for restoring the amplitude of an acoustic disturbance in free-stream flow by measuring the pressure fluctuations on the plate surface is discussed.
- 1 December 2023
- Published by Pleiades Publishing Ltd in Fluid Dynamics
- Vol. 58 (6) , 969-979
Interaction of Acoustic Disturbances with the Flat-Plate Supersonic Boundary Layer
Numerical simulation of the receptivity of a supersonic boundary layer on a flat pointed plate with respect to model acoustic disturbances that propagate in the free-stream flow (Mach number is equal to 5) and are characteristic of the background noise of shock wind tunnels is carried out within the framework of the full Navier–Stokes equations. Spectral analysis of the perturbations induced in the boundary layer is carried out. A method for restoring the amplitude of an acoustic disturbance in free-stream flow by measuring the pressure fluctuations on the plate surface is discussed.
- 1 November 2023
- Published by The Russian Academy of Sciences in Izvestiâ Akademii nauk. Rossijskaâ akademiâ nauk. Mehanika židkosti i gaza
- No. 6,p. 3-13
ВЗАИМОДЕЙСТВИЕ АКУСТИЧЕСКИХ ВОЗМУЩЕНИЙ СО СВЕРХЗВУКОВЫМ ПОГРАНИЧНЫМ СЛОЕМ НА ПЛОСКОЙ ПЛАСТИНЕ
В рамках полных уравнений Навье–Стокса проведено численное моделирование восприимчивости сверхзвукового пограничного слоя на плоской заостренной пластине к модельным акустическим возмущениям, которые распространяются в набегающем потоке (число Маха 5) и характерны для фонового шума ударных аэродинамических труб. Проведен спектральный анализ возмущений, индуцированных в пограничном слое. Обсуждается способ восстановления амплитуды акустического возмущения в набегающем потоке с помощью измерения пульсаций давления на поверхности пластины.
- 1 November 2023
- Published by The Russian Academy of Sciences in Izvestiâ Akademii nauk. Rossijskaâ akademiâ nauk. Mehanika židkosti i gaza
- No. 6,p. 3-13
ВЗАИМОДЕЙСТВИЕ АКУСТИЧЕСКИХ ВОЗМУЩЕНИЙ СО СВЕРХЗВУКОВЫМ ПОГРАНИЧНЫМ СЛОЕМ НА ПЛОСКОЙ ПЛАСТИНЕ
В рамках полных уравнений Навье–Стокса проведено численное моделирование восприимчивости сверхзвукового пограничного слоя на плоской заостренной пластине к модельным акустическим возмущениям, которые распространяются в набегающем потоке (число Маха 5) и характерны для фонового шума ударных аэродинамических труб. Проведен спектральный анализ возмущений, индуцированных в пограничном слое. Обсуждается способ восстановления амплитуды акустического возмущения в набегающем потоке с помощью измерения пульсаций давления на поверхности пластины.
- 1 September 2023
- Published by The Russian Academy of Sciences in Žurnal vyčislitelʹnoj matematiki i matematičeskoj fiziki
- Vol. 63 (9) , 1554-1563
Universal Approach to Analysis of Dissipation Properties of a Numerical Method for Solving Gas Dynamic Equations
A universal approach to the verification of a numerical method for solving the Navier–Stokes equations is proposed, through which the dissipation properties of the method can be reliably assessed. The approach is based on viscous damping of weak elementary perturbations propagating in uniform flow. The corresponding theoretical solution allows one to determine the order of convergence of the numerical method.
- 1 September 2023
- Published by The Russian Academy of Sciences in Žurnal vyčislitelʹnoj matematiki i matematičeskoj fiziki
- Vol. 63 (9) , 1554-1563
Universal Approach to Analysis of Dissipation Properties of a Numerical Method for Solving Gas Dynamic Equations
A universal approach to the verification of a numerical method for solving the Navier–Stokes equations is proposed, through which the dissipation properties of the method can be reliably assessed. The approach is based on viscous damping of weak elementary perturbations propagating in uniform flow. The corresponding theoretical solution allows one to determine the order of convergence of the numerical method.
- 1 September 2023
- Published by Pleiades Publishing Ltd in Computational Mathematics and Mathematical Physics
- Vol. 63 (9) , 1708-1716
Universal Approach to Analysis of Dissipation Properties of a Numerical Method for Solving Gas Dynamic Equations
A universal approach to the verification of a numerical method for solving the Navier–Stokes equations is proposed, through which the dissipation properties of the method can be reliably assessed. The approach is based on viscous damping of weak elementary perturbations propagating in uniform flow. The corresponding theoretical solution allows one to determine the order of convergence of the numerical method.
- 1 September 2023
- Published by Pleiades Publishing Ltd in Computational Mathematics and Mathematical Physics
- Vol. 63 (9) , 1708-1716
Universal Approach to Analysis of Dissipation Properties of a Numerical Method for Solving Gas Dynamic Equations
A universal approach to the verification of a numerical method for solving the Navier–Stokes equations is proposed, through which the dissipation properties of the method can be reliably assessed. The approach is based on viscous damping of weak elementary perturbations propagating in uniform flow. The corresponding theoretical solution allows one to determine the order of convergence of the numerical method.
- 11 April 2023
- Published by Pleiades Publishing Ltd in Mathematical Models and Computer Simulations
- Vol. 15 (2) , 177-188
Sources of Turbulence on an Unswept Wing of a Supersonic Passenger Airplane
The two most likely sources of disturbances capable of triggering boundary layer turbulization over a smooth unswept wing of a supersonic airplane are considered in terms of the full Navier–Stokes equations: atmospheric turbulence and acoustic noise radiated by the turbulent boundary layer over the fuselage. The frequency wave characteristics of boundary layer disturbances over the wing are analyzed and the dominant mechanism of transition is revealed. The numerical results are compared with those of linear stability theory.
- 11 April 2023
- Published by Pleiades Publishing Ltd in Mathematical Models and Computer Simulations
- Vol. 15 (2) , 177-188
Sources of Turbulence on an Unswept Wing of a Supersonic Passenger Airplane
The two most likely sources of disturbances capable of triggering boundary layer turbulization over a smooth unswept wing of a supersonic airplane are considered in terms of the full Navier–Stokes equations: atmospheric turbulence and acoustic noise radiated by the turbulent boundary layer over the fuselage. The frequency wave characteristics of boundary layer disturbances over the wing are analyzed and the dominant mechanism of transition is revealed. The numerical results are compared with those of linear stability theory.