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Papers by Anton Gorbushin

Research paper thumbnail of Investigation of a strain-gauge dynamometer for measuring boundary layer friction force on the wind tunnel wall

Izmeritelʹnaâ tehnika, Aug 31, 2023

Research paper thumbnail of Strain gauge dynamometer for measuring the boundary layer friction force on the walls of wind tunnels

Measurement Techniques, Dec 6, 2023

Research paper thumbnail of Novel method for measuring non-stationary pitch and roll angles with a pendulous accelerometer in the presence of vibrations

Measurement, Nov 30, 2023

Research paper thumbnail of Non-stationary load measurement using six-component strain-gauge balances

Measurement, Dec 31, 2023

Research paper thumbnail of Studying Dependence of “Rigid” Aerodynamic Models Elastic Deformations on Their Geometric and Design Parameters

Vestnik Moskovskogo aviatsionnogo instituta

Research paper thumbnail of The Earliest Russian Wind Tunnels

53rd AIAA Aerospace Sciences Meeting, 2015

The paper describes the origin of the first Russian wind tunnels developed by V.A. Pashkevich in ... more The paper describes the origin of the first Russian wind tunnels developed by V.A. Pashkevich in 1871, K.E. Tsiolkovsky in 1897, prof. N.E. Zhukovsky in 1902, 1909 and 1910 and D.P. Ryabushinsky under the guidance of prof. N.E. Zhukovsky in Kuchino aerodynamic institute in 1904. These wind tunnels are shown diagrammatically and as photographs also presented in the paper are descriptions and sketches of Pashkevich threecomponent mechanical aerodynamic balance, Tsiolkovsky single-component balance as well as balances used by Zhukovsky in his aerodynamic experiments. Description of experimental investigations and some test results are also provided. The paper is written based on materials published by the wind tunnel designers at the boundary of the 19th and the 20th centuries.

Research paper thumbnail of Experience in the application of numerical methods to TsAGI's wind-tunnel testing techniques

This paper briefly presents the history of numerical methods' implementation into TsAGI's... more This paper briefly presents the history of numerical methods' implementation into TsAGI's experimental technologies since the launch of the Buran-Energiya space system program in the 1980s. New features of the method developed at TsAGI within the framework of Electronic Wind Tunnel software package for numerically solving the Navier-Stokes equations are described. Application examples of the programs for solving problems associated with the test methodology adapted for the TsAGI T-128 and T-104 wind tunnels are provided.

Research paper thumbnail of Static component of the temperature error of the strain-gauge balance: determination of the temperature sensitivity coefficient

Izmeritel`naya Tekhnika, 2021

Research paper thumbnail of Self-Induced Suction of Fluid in a Turbulent Boundary Layer on a Permeable Surface

Computational Mathematics and Mathematical Physics, Oct 1, 2022

Research paper thumbnail of Verification of the method for assessing systematic errors of the balance calibration machine

Izmeritel`naya Tekhnika, 2022

Research paper thumbnail of Verification of the Method for Assessing Systematic Errors of the Bench for Calibrating Six-Component Strain-Gauge Balances

Research paper thumbnail of General Problems of Metrology and Measurement Technique Static Component of Temperature Error in the Strain-Gauge Balance: Determination of the Temperature Sensitivity Coefficient

Measurement Techniques, 2022

Research paper thumbnail of Specifics of application of videogrammetric system Vic-3D in aerodynamic experiment

Journal of Physics: Conference Series, 2021

The main objective of this work was testing a possibility of application of commercial videogramm... more The main objective of this work was testing a possibility of application of commercial videogrammetric system Vic-3D for measuring position and deformation of the aircraft model and its elements in an industrial the TsAGI transonic wind tunnel T-128. The object of research was a model of passenger aircraft with a wingspan of 2010 mm, fixed on the rear sting. The Vic-3D system used for measuring the position and deformation of the aircraft model was applied for the runs with and without flow at the pitch angles range from − 3 to +12 degrees. Model was tested in wind tunnel up to Mach number M = 0.853. An algorithm of working with the Vic-3D system was described in the article, some specifics of obtained results were underlined. An additional program to derive bend and twist deformations of a wing was developed. Results of an experiment were given, errors and inaccuracy were analyzed. Recommendations for using the system Vic-3D in an aerodynamic experiment were given.

Research paper thumbnail of Unsteady axial force measurement by the strain gauge balance

Measurement, 2020

Abstract A new method was developed to measure the unsteady force measurement by means of six-com... more Abstract A new method was developed to measure the unsteady force measurement by means of six-component strain gauge balance which finds use in technological processes, e.g. in wind tunnel experiments. A mathematical model in the form of damping spring was used as a core of the method. It was verified by results of experiments involving applying harmonic and step force. Applicability of the balance matrix defined in static conditions was validated by an experiment with harmonic steady-state oscillations of the balance. The developed methodology provides the measurement of arbitrary non-stationary load in inertial or non-inertial system using a strain gauge balance with relative deviation at the level of 0.3–3% in the whole balance’ operating frequency range, including the natural frequency. A dynamic calibration method was developed for the axial force of a six-component strain gauge balance by applying a harmonic force to the ground part of the balance.

Research paper thumbnail of Pioneering Russian wind tunnels and first experimental investigations, 1871–1915

Progress in Aerospace Sciences, 2017

A review of foreign and Russian sources is given mentioning the pioneering wind tunnels built in ... more A review of foreign and Russian sources is given mentioning the pioneering wind tunnels built in Russia at the turn of 19th and 20th centuries. The first wind tunnel in Russia was constructed by V.A. Pashkevich at the Mikhailovsky Artillery Academy in St. Petersburg in 1871. In total from 1871 through 1915, 18 wind tunnels were constructed in Russia: 11 in Moscow, 5 in St. Petersburg and 2 in Kaluga. An overview of the pioneering Russian wind tunnels built by V.A. Pashkevich, K.E. Tsiolkovsky, prof. N.E. Zhukovsky, D.P. Ryabushinsky and prof. K.P. Boklevsky is given. Schemes, photographs, formulas, description of the research and test results taken from the original papers published by the wind tunnel designers are given. Photographs from the N.E. Zhukovsky Scientific and Memorial Museum and the Archive of the Russian Academy of Sciences are used in the article. Methods of flow visualization and results of their application are presented. The Russian scientists and researchers' contribution to the development of techniques and methods of aerodynamic experiment is shown, including one of the most important aspects-the wall interference problem. World history adorns the world with great memories for the mind, and the Russian one decorates the homeland where we live and feel. N.M. Karamzin "History of the Russian State"

Research paper thumbnail of Investigation of the rear support interference on the aerodynamic characteristics of the RRJ-95 model in the T-128 transonic wind tunnel

ICIASF 2005 RecordInternational Congress onInstrumentation in AerospaceSimulation Facilities, 2005

ABSTRACT The interference of the rear sting and the crescent-shaped rigid strut on the aerodynami... more ABSTRACT The interference of the rear sting and the crescent-shaped rigid strut on the aerodynamic characteristics (drag, lift, pitching moment and base pressure coefficients) of the Russian regional jet model RRJ-95 is investigated in the TsAGI T-128 transonic wind tunnel at Mach numbers ranging from 0.7 to 0.88. The rear sting interference is studied experimentally. The weak interference (far field from the cone parts of the sting and the crescent-shaped strut) is evaluated within the framework of the small-disturbance theory with due regard for compressibility ac-cording to Prandtl-Glauert. The effect of the rear sting position variations relative to the model due to the sting deformation un-der the action of lift and pitching moment on the aerodynamic characteristics of the model is shown. The position of the point of applying the lift increment caused by the dummy rear sting inter-ference is determined depending on the Mach number, angle of attack, model configuration, mutual position of the dummy sting and the fuselage. For better understanding of the flow physics, the flow visualization is performed by the color oil method in the area of the fuselage afterbody- fin sting- dummy rear sting joint. The analysis reveals a rather complicated flow nature in the base re-gion. The presence of the wing changes the rear sting interference as compared with the fuselage alone.

Research paper thumbnail of Use of accelerometers for measurement of pitch and bank angles in an aerodynamic experiment

Measurement Techniques, 2012

ABSTRACT

Research paper thumbnail of The use of computational fluid dynamics in TsAGI experimental works

Mathematical Models and Computer Simulations, 2012

CONTENTS 1. Introduction 2. Mathematical WT Model and Its Constructive Features 3. Method of Nume... more CONTENTS 1. Introduction 2. Mathematical WT Model and Its Constructive Features 3. Method of Numerical Computation Based on the Explicit Scheme 4. Method of Numerical Computation Based on the Explicit Implicit Scheme 5. Boundary Conditions 6. Introduction of the WT Mathematical Model into the Technological Cycle of the Experiment 7. References

Research paper thumbnail of Recent experience in improving the accuracy of wall interference corrections in TsAGI T-128 wind tunnel

Progress in Aerospace Sciences, 2001

Typical sources of systematic errors in the wind tunnel tests are considered and analyzed with em... more Typical sources of systematic errors in the wind tunnel tests are considered and analyzed with emphasis on the prediction of wall interference problems. The review is made on the methods of wall interference corrections and boundary condition measurements in connection with the T-128 test technique development. The levels of interference corrections for transport aircraft tests are estimated using the computer

Research paper thumbnail of Measuring and computational system of TsAGI T-128 transonic wind tunnel

Automation and Remote Control, 2011

ABSTRACT

Research paper thumbnail of Investigation of a strain-gauge dynamometer for measuring boundary layer friction force on the wind tunnel wall

Izmeritelʹnaâ tehnika, Aug 31, 2023

Research paper thumbnail of Strain gauge dynamometer for measuring the boundary layer friction force on the walls of wind tunnels

Measurement Techniques, Dec 6, 2023

Research paper thumbnail of Novel method for measuring non-stationary pitch and roll angles with a pendulous accelerometer in the presence of vibrations

Measurement, Nov 30, 2023

Research paper thumbnail of Non-stationary load measurement using six-component strain-gauge balances

Measurement, Dec 31, 2023

Research paper thumbnail of Studying Dependence of “Rigid” Aerodynamic Models Elastic Deformations on Their Geometric and Design Parameters

Vestnik Moskovskogo aviatsionnogo instituta

Research paper thumbnail of The Earliest Russian Wind Tunnels

53rd AIAA Aerospace Sciences Meeting, 2015

The paper describes the origin of the first Russian wind tunnels developed by V.A. Pashkevich in ... more The paper describes the origin of the first Russian wind tunnels developed by V.A. Pashkevich in 1871, K.E. Tsiolkovsky in 1897, prof. N.E. Zhukovsky in 1902, 1909 and 1910 and D.P. Ryabushinsky under the guidance of prof. N.E. Zhukovsky in Kuchino aerodynamic institute in 1904. These wind tunnels are shown diagrammatically and as photographs also presented in the paper are descriptions and sketches of Pashkevich threecomponent mechanical aerodynamic balance, Tsiolkovsky single-component balance as well as balances used by Zhukovsky in his aerodynamic experiments. Description of experimental investigations and some test results are also provided. The paper is written based on materials published by the wind tunnel designers at the boundary of the 19th and the 20th centuries.

Research paper thumbnail of Experience in the application of numerical methods to TsAGI's wind-tunnel testing techniques

This paper briefly presents the history of numerical methods' implementation into TsAGI's... more This paper briefly presents the history of numerical methods' implementation into TsAGI's experimental technologies since the launch of the Buran-Energiya space system program in the 1980s. New features of the method developed at TsAGI within the framework of Electronic Wind Tunnel software package for numerically solving the Navier-Stokes equations are described. Application examples of the programs for solving problems associated with the test methodology adapted for the TsAGI T-128 and T-104 wind tunnels are provided.

Research paper thumbnail of Static component of the temperature error of the strain-gauge balance: determination of the temperature sensitivity coefficient

Izmeritel`naya Tekhnika, 2021

Research paper thumbnail of Self-Induced Suction of Fluid in a Turbulent Boundary Layer on a Permeable Surface

Computational Mathematics and Mathematical Physics, Oct 1, 2022

Research paper thumbnail of Verification of the method for assessing systematic errors of the balance calibration machine

Izmeritel`naya Tekhnika, 2022

Research paper thumbnail of Verification of the Method for Assessing Systematic Errors of the Bench for Calibrating Six-Component Strain-Gauge Balances

Research paper thumbnail of General Problems of Metrology and Measurement Technique Static Component of Temperature Error in the Strain-Gauge Balance: Determination of the Temperature Sensitivity Coefficient

Measurement Techniques, 2022

Research paper thumbnail of Specifics of application of videogrammetric system Vic-3D in aerodynamic experiment

Journal of Physics: Conference Series, 2021

The main objective of this work was testing a possibility of application of commercial videogramm... more The main objective of this work was testing a possibility of application of commercial videogrammetric system Vic-3D for measuring position and deformation of the aircraft model and its elements in an industrial the TsAGI transonic wind tunnel T-128. The object of research was a model of passenger aircraft with a wingspan of 2010 mm, fixed on the rear sting. The Vic-3D system used for measuring the position and deformation of the aircraft model was applied for the runs with and without flow at the pitch angles range from − 3 to +12 degrees. Model was tested in wind tunnel up to Mach number M = 0.853. An algorithm of working with the Vic-3D system was described in the article, some specifics of obtained results were underlined. An additional program to derive bend and twist deformations of a wing was developed. Results of an experiment were given, errors and inaccuracy were analyzed. Recommendations for using the system Vic-3D in an aerodynamic experiment were given.

Research paper thumbnail of Unsteady axial force measurement by the strain gauge balance

Measurement, 2020

Abstract A new method was developed to measure the unsteady force measurement by means of six-com... more Abstract A new method was developed to measure the unsteady force measurement by means of six-component strain gauge balance which finds use in technological processes, e.g. in wind tunnel experiments. A mathematical model in the form of damping spring was used as a core of the method. It was verified by results of experiments involving applying harmonic and step force. Applicability of the balance matrix defined in static conditions was validated by an experiment with harmonic steady-state oscillations of the balance. The developed methodology provides the measurement of arbitrary non-stationary load in inertial or non-inertial system using a strain gauge balance with relative deviation at the level of 0.3–3% in the whole balance’ operating frequency range, including the natural frequency. A dynamic calibration method was developed for the axial force of a six-component strain gauge balance by applying a harmonic force to the ground part of the balance.

Research paper thumbnail of Pioneering Russian wind tunnels and first experimental investigations, 1871–1915

Progress in Aerospace Sciences, 2017

A review of foreign and Russian sources is given mentioning the pioneering wind tunnels built in ... more A review of foreign and Russian sources is given mentioning the pioneering wind tunnels built in Russia at the turn of 19th and 20th centuries. The first wind tunnel in Russia was constructed by V.A. Pashkevich at the Mikhailovsky Artillery Academy in St. Petersburg in 1871. In total from 1871 through 1915, 18 wind tunnels were constructed in Russia: 11 in Moscow, 5 in St. Petersburg and 2 in Kaluga. An overview of the pioneering Russian wind tunnels built by V.A. Pashkevich, K.E. Tsiolkovsky, prof. N.E. Zhukovsky, D.P. Ryabushinsky and prof. K.P. Boklevsky is given. Schemes, photographs, formulas, description of the research and test results taken from the original papers published by the wind tunnel designers are given. Photographs from the N.E. Zhukovsky Scientific and Memorial Museum and the Archive of the Russian Academy of Sciences are used in the article. Methods of flow visualization and results of their application are presented. The Russian scientists and researchers' contribution to the development of techniques and methods of aerodynamic experiment is shown, including one of the most important aspects-the wall interference problem. World history adorns the world with great memories for the mind, and the Russian one decorates the homeland where we live and feel. N.M. Karamzin "History of the Russian State"

Research paper thumbnail of Investigation of the rear support interference on the aerodynamic characteristics of the RRJ-95 model in the T-128 transonic wind tunnel

ICIASF 2005 RecordInternational Congress onInstrumentation in AerospaceSimulation Facilities, 2005

ABSTRACT The interference of the rear sting and the crescent-shaped rigid strut on the aerodynami... more ABSTRACT The interference of the rear sting and the crescent-shaped rigid strut on the aerodynamic characteristics (drag, lift, pitching moment and base pressure coefficients) of the Russian regional jet model RRJ-95 is investigated in the TsAGI T-128 transonic wind tunnel at Mach numbers ranging from 0.7 to 0.88. The rear sting interference is studied experimentally. The weak interference (far field from the cone parts of the sting and the crescent-shaped strut) is evaluated within the framework of the small-disturbance theory with due regard for compressibility ac-cording to Prandtl-Glauert. The effect of the rear sting position variations relative to the model due to the sting deformation un-der the action of lift and pitching moment on the aerodynamic characteristics of the model is shown. The position of the point of applying the lift increment caused by the dummy rear sting inter-ference is determined depending on the Mach number, angle of attack, model configuration, mutual position of the dummy sting and the fuselage. For better understanding of the flow physics, the flow visualization is performed by the color oil method in the area of the fuselage afterbody- fin sting- dummy rear sting joint. The analysis reveals a rather complicated flow nature in the base re-gion. The presence of the wing changes the rear sting interference as compared with the fuselage alone.

Research paper thumbnail of Use of accelerometers for measurement of pitch and bank angles in an aerodynamic experiment

Measurement Techniques, 2012

ABSTRACT

Research paper thumbnail of The use of computational fluid dynamics in TsAGI experimental works

Mathematical Models and Computer Simulations, 2012

CONTENTS 1. Introduction 2. Mathematical WT Model and Its Constructive Features 3. Method of Nume... more CONTENTS 1. Introduction 2. Mathematical WT Model and Its Constructive Features 3. Method of Numerical Computation Based on the Explicit Scheme 4. Method of Numerical Computation Based on the Explicit Implicit Scheme 5. Boundary Conditions 6. Introduction of the WT Mathematical Model into the Technological Cycle of the Experiment 7. References

Research paper thumbnail of Recent experience in improving the accuracy of wall interference corrections in TsAGI T-128 wind tunnel

Progress in Aerospace Sciences, 2001

Typical sources of systematic errors in the wind tunnel tests are considered and analyzed with em... more Typical sources of systematic errors in the wind tunnel tests are considered and analyzed with emphasis on the prediction of wall interference problems. The review is made on the methods of wall interference corrections and boundary condition measurements in connection with the T-128 test technique development. The levels of interference corrections for transport aircraft tests are estimated using the computer

Research paper thumbnail of Measuring and computational system of TsAGI T-128 transonic wind tunnel

Automation and Remote Control, 2011

ABSTRACT