Tabakoff, W.
Overview
Works:  88 works in 109 publications in 1 language and 257 library holdings 

Genres:  Conference papers and proceedings 
Roles:  Author 
Publication Timeline
.
Most widely held works by
W Tabakoff
Turbomachinery performance deterioration : presented at the AIAA/ASME 4th Joint Fluid Mechanics, Plasma Dynamics, and Lasers
Conference, Atlanta, Georgia, May 1214, 1986 by Plasma Dynamics, and Lasers Conference AIAA/ASME Joint Fluid Mechanics(
Book
)
4 editions published in 1986 in English and Undetermined and held by 76 WorldCat member libraries worldwide
4 editions published in 1986 in English and Undetermined and held by 76 WorldCat member libraries worldwide
Particulate laden flows in turbomachinery : presented at 1982 AIAA/ASME Joint Fluids, Plasma, Thermophysics, and Heat Transfer
Conference, St. Louis, Missouri, June 711, 1982 by
W Tabakoff(
Book
)
3 editions published in 1982 in English and held by 62 WorldCat member libraries worldwide
3 editions published in 1982 in English and held by 62 WorldCat member libraries worldwide
The initial development of the general nonisoenergetic compressible free shear layer by
P Carpenter(
Book
)
4 editions published in 1971 in English and held by 21 WorldCat member libraries worldwide
4 editions published in 1971 in English and held by 21 WorldCat member libraries worldwide
Pressure recovery measurements across a twodimensional hypersonic inlet with variable geometry by
W Tabakoff(
Book
)
2 editions published in 1965 in English and held by 3 WorldCat member libraries worldwide
The report describes the experimental measurement of pressure recovery across a simulated combustion chamber duct of a twodimensional hypersonic inlet with variable geometry. The model tested was a wedge type inlet which generated a single external shock wave. The program was conducted in the twentyinch hypersonic wind tunnel. Testing was at a nominal free stream Mach number of 14 and free stream Reynolds number of 721,000 per foot. (Author)
2 editions published in 1965 in English and held by 3 WorldCat member libraries worldwide
The report describes the experimental measurement of pressure recovery across a simulated combustion chamber duct of a twodimensional hypersonic inlet with variable geometry. The model tested was a wedge type inlet which generated a single external shock wave. The program was conducted in the twentyinch hypersonic wind tunnel. Testing was at a nominal free stream Mach number of 14 and free stream Reynolds number of 721,000 per foot. (Author)
A study of nonisoenergetic turbulent jet mixing between compressible subsonic streams in axisymmetric constant area duct by K. K Khanna(
Book
)
2 editions published in 1969 in English and held by 2 WorldCat member libraries worldwide
The problem of turbulent mixing between two compressible streams in a constant area duct is analyzed. The velocity and temperature profiles were worked in the main region of the mixing chamber for axisymmetric case. Turbulent free jet experimental data is used, to obtain expressions for velocity and temperature as a function of the distance from the inlet to the mixing chamber. It is found that energy diffuses more rapidly than momentum for ducted mixing. The results of the theoretical analysis indicate increasing tendency towards segregation of the streams for decreasing initial velocity difference between the mixing streams. On the basis of the mixing chamber length required to achieve adequate degree of mixing, it is concluded that a corrugated rim primary nozzle is needed to accelerate the mixing rate by increasing the contact surface between the streams. (Author)
2 editions published in 1969 in English and held by 2 WorldCat member libraries worldwide
The problem of turbulent mixing between two compressible streams in a constant area duct is analyzed. The velocity and temperature profiles were worked in the main region of the mixing chamber for axisymmetric case. Turbulent free jet experimental data is used, to obtain expressions for velocity and temperature as a function of the distance from the inlet to the mixing chamber. It is found that energy diffuses more rapidly than momentum for ducted mixing. The results of the theoretical analysis indicate increasing tendency towards segregation of the streams for decreasing initial velocity difference between the mixing streams. On the basis of the mixing chamber length required to achieve adequate degree of mixing, it is concluded that a corrugated rim primary nozzle is needed to accelerate the mixing rate by increasing the contact surface between the streams. (Author)
An analytical study of flow losses through a twodimensional turbine cascade with boundary layer injection [by] W. Tabakoff
and R. Earley by
W Tabakoff(
Book
)
2 editions published in 1972 in English and held by 2 WorldCat member libraries worldwide
A method for determining the performance of a twodimensional turbine cascade with boundary layer injection is developed using existing incompressible boundary layer approximate solutions with a new formulation for the injection. The overall cascade loss includes friction and wake mixing losses. The results of the analysis are compared with experimentally obtained data as a check of the validity of the new analytical method. (Author)
2 editions published in 1972 in English and held by 2 WorldCat member libraries worldwide
A method for determining the performance of a twodimensional turbine cascade with boundary layer injection is developed using existing incompressible boundary layer approximate solutions with a new formulation for the injection. The overall cascade loss includes friction and wake mixing losses. The results of the analysis are compared with experimentally obtained data as a check of the validity of the new analytical method. (Author)
Measurement of the heat transfer to a twodimensional hypersonic inlet with variable geometry by
W Tabakoff(
Book
)
2 editions published in 1965 in English and held by 2 WorldCat member libraries worldwide
The report describes the experimental measurement of aerodynamic heat transfer to a twodimensional variable geometry hypersonic inlet model. The program was conducted in a twentyinch hypersonic tunnel. Testing was at a nominal free stream Mach number of 14 and free stream Reynolds numbers of 721,000 and 631,000 per foot. The experimental results are compared to an approximate theoretical solution for laminar boundary layer flow over a flat plate. (Author)
2 editions published in 1965 in English and held by 2 WorldCat member libraries worldwide
The report describes the experimental measurement of aerodynamic heat transfer to a twodimensional variable geometry hypersonic inlet model. The program was conducted in a twentyinch hypersonic tunnel. Testing was at a nominal free stream Mach number of 14 and free stream Reynolds numbers of 721,000 and 631,000 per foot. The experimental results are compared to an approximate theoretical solution for laminar boundary layer flow over a flat plate. (Author)
An Analytical Solution of Wall Temperature Distribution for Transpiration and Local Mass Injection Over a Flat Plate by
Roointon E Pavri(
Book
)
2 editions published in 1972 in English and held by 2 WorldCat member libraries worldwide
An analytical solution is given of the nonsimilar laminar boundary layer with continuous or local injection and variable wall temperature. The solution is for a flat plate with zero pressure gradient, but it can be modified for variable pressure. The method consists of transforming the partial differential equations for momentum and enthalpy and then solving the transformed equations by assuming polynomial velocity and temperature profiles. The first part presents the solution for continuous injection (transpiration cooling), and the second part involves discontinuous boundary conditions due to local injection. (Author)
2 editions published in 1972 in English and held by 2 WorldCat member libraries worldwide
An analytical solution is given of the nonsimilar laminar boundary layer with continuous or local injection and variable wall temperature. The solution is for a flat plate with zero pressure gradient, but it can be modified for variable pressure. The method consists of transforming the partial differential equations for momentum and enthalpy and then solving the transformed equations by assuming polynomial velocity and temperature profiles. The first part presents the solution for continuous injection (transpiration cooling), and the second part involves discontinuous boundary conditions due to local injection. (Author)
A study of compressor erosion in helicopter engine with inlet separator by
W Tabakoff(
Book
)
2 editions published in 1986 in English and held by 2 WorldCat member libraries worldwide
Performance of aircraft engines, operating in areas where the atmosphere is polluted by small solid particles, can suffer due to blade surface erosion. Erosion damage can lead to significant reduction in engine efficiency as well as performance, due to the change in blade surfaces, tip leakages and blade pressure distribution. This report presents the results of an investigation of the solid particle dynamics and the resulting blade erosion through a helicopter engine with inlet particle separator. Particle trajectories are computed in the inlet separator which is characterized by considerable hub and tip contouring and radial variation in the swirling vane shape. The nonseparated particle trajectories are determined through the deswirling vanes and the five stage axial and one stage radial compressors. Impact data for a very large number of ingested particles is used to calculate the resulting blade surface erosion. The erosion pattern indicates the location of maximum blade erosion. In addition, the distribution of particle impact data (which is pertinent to erosion such as the impact velocities, impact angles and in particular, the frequency of particle impacts) is presented to suggest possible procedure to reduce the erosion in the critically affected blade areas. Keywords: Compressor aerodynamics, Compressor blades, Ingestion(Engines), and Particulate flow trajectory calculations
2 editions published in 1986 in English and held by 2 WorldCat member libraries worldwide
Performance of aircraft engines, operating in areas where the atmosphere is polluted by small solid particles, can suffer due to blade surface erosion. Erosion damage can lead to significant reduction in engine efficiency as well as performance, due to the change in blade surfaces, tip leakages and blade pressure distribution. This report presents the results of an investigation of the solid particle dynamics and the resulting blade erosion through a helicopter engine with inlet particle separator. Particle trajectories are computed in the inlet separator which is characterized by considerable hub and tip contouring and radial variation in the swirling vane shape. The nonseparated particle trajectories are determined through the deswirling vanes and the five stage axial and one stage radial compressors. Impact data for a very large number of ingested particles is used to calculate the resulting blade surface erosion. The erosion pattern indicates the location of maximum blade erosion. In addition, the distribution of particle impact data (which is pertinent to erosion such as the impact velocities, impact angles and in particular, the frequency of particle impacts) is presented to suggest possible procedure to reduce the erosion in the critically affected blade areas. Keywords: Compressor aerodynamics, Compressor blades, Ingestion(Engines), and Particulate flow trajectory calculations
High Temperature Erosion Study of INCO 600 Metal(
Book
)
2 editions published in 1983 in English and held by 2 WorldCat member libraries worldwide
2 editions published in 1983 in English and held by 2 WorldCat member libraries worldwide
Particulate laden Flows in turbomachinery : Presented at a Conference(
Book
)
1 edition published in 1982 in English and held by 2 WorldCat member libraries worldwide
1 edition published in 1982 in English and held by 2 WorldCat member libraries worldwide
The solution of the equations of motion for unsteady viscous particualate flows by
A Hamed(
Book
)
2 editions published in 1974 in English and held by 2 WorldCat member libraries worldwide
A numerical method is developed to solve the equations that govern the motion of the two dimensional flow of a suspension consisting of incompressible visious gas and suspended solid particles. The numerical method is implicit, second order and iterative. The frozen and equilibrium wall friction coefficient are compared with the corresponding analytically determined values for a simple example, and are found to be in agreement. It is concluded that the present numerical method for investigating the nonequilibrium flow regime, gives accurate results not only for nonequilibrium flow conditions, but also predicts frozen and equilibrium flow conditions very accurately. (Author)
2 editions published in 1974 in English and held by 2 WorldCat member libraries worldwide
A numerical method is developed to solve the equations that govern the motion of the two dimensional flow of a suspension consisting of incompressible visious gas and suspended solid particles. The numerical method is implicit, second order and iterative. The frozen and equilibrium wall friction coefficient are compared with the corresponding analytically determined values for a simple example, and are found to be in agreement. It is concluded that the present numerical method for investigating the nonequilibrium flow regime, gives accurate results not only for nonequilibrium flow conditions, but also predicts frozen and equilibrium flow conditions very accurately. (Author)
An experimental investigation of the erosive characteristics of 2024 aluminum alloy by
G Grant(
Book
)
2 editions published in 1973 in English and held by 2 WorldCat member libraries worldwide
The erosive characteristics of 2024 aluminum alloy have been experimentally examined. The parameters investigated included the particle approach angle, particle velocity, particle size, specimen length, particle material, particle concentration, and quantity of abrasive impacting the specimen. From this data an analytical model has been developed which will predict the erosion of this material
2 editions published in 1973 in English and held by 2 WorldCat member libraries worldwide
The erosive characteristics of 2024 aluminum alloy have been experimentally examined. The parameters investigated included the particle approach angle, particle velocity, particle size, specimen length, particle material, particle concentration, and quantity of abrasive impacting the specimen. From this data an analytical model has been developed which will predict the erosion of this material
An analytical solution of the compressible laminar momentum and thermal boundary layers with pressure gradient and continuous
mass injection by
Roointon E Pavri(
Book
)
2 editions published in 1972 in English and held by 2 WorldCat member libraries worldwide
The study describes an analytical solution of the nonsimilar laminar boundary layer with pressure gradient, variable wall temperature and continuous injection. The method consists of transforming the partial differential equations for momentum and enthalpy and then solving the transformed equations by assuming polynomial stream function and enthalpy profiles. Solutions obtained show very good agreement with exact numerical results. The solutions are obtained for flows over wedges as well as at the twodimensional stagnation point and over curved surfaces of a twodimensional body in crossflow. The results of the study show that the boundary layer is very strongly effected by the injection mass flow rate
2 editions published in 1972 in English and held by 2 WorldCat member libraries worldwide
The study describes an analytical solution of the nonsimilar laminar boundary layer with pressure gradient, variable wall temperature and continuous injection. The method consists of transforming the partial differential equations for momentum and enthalpy and then solving the transformed equations by assuming polynomial stream function and enthalpy profiles. Solutions obtained show very good agreement with exact numerical results. The solutions are obtained for flows over wedges as well as at the twodimensional stagnation point and over curved surfaces of a twodimensional body in crossflow. The results of the study show that the boundary layer is very strongly effected by the injection mass flow rate
A quasianalytical method for the calculation of particle trajectories by
G. K Grant(
Book
)
2 editions published in 1973 in English and held by 2 WorldCat member libraries worldwide
The equation of motion of a sand particle under the influence of aerodynamic drag has been developed in the inertial coordinate system. The method of solution presented is very easy to use in that only one first order differential equation has to be solved. The equation of motion has been integrated and solved for the special cases of onedimensional steady flow and onedimensional accelerating flow as well as the general case of two or threedimensional accelerating flow. The computerized models of these three problems are presented along with solutions of example problems. High speed movies were taken of sand particles which had been accelerated in a specially designed tunnel. These results demonstrated the extreme accuracy of this method of solution. (Author)
2 editions published in 1973 in English and held by 2 WorldCat member libraries worldwide
The equation of motion of a sand particle under the influence of aerodynamic drag has been developed in the inertial coordinate system. The method of solution presented is very easy to use in that only one first order differential equation has to be solved. The equation of motion has been integrated and solved for the special cases of onedimensional steady flow and onedimensional accelerating flow as well as the general case of two or threedimensional accelerating flow. The computerized models of these three problems are presented along with solutions of example problems. High speed movies were taken of sand particles which had been accelerated in a specially designed tunnel. These results demonstrated the extreme accuracy of this method of solution. (Author)
Erosion prediction in turbomachinery resulting from environmental solid particles by
G Grant(
Book
)
1 edition published in 1975 in English and held by 1 WorldCat member library worldwide
1 edition published in 1975 in English and held by 1 WorldCat member library worldwide
A numerical study of the temperature field in a cooled radial turbine rotor by
A Hamed(
Book
)
1 edition published in 1977 in English and held by 1 WorldCat member library worldwide
1 edition published in 1977 in English and held by 1 WorldCat member library worldwide
Review  Turbomachinery Performance Deterioration Exposed to Solid Particulates Environment(
Book
)
1 edition published in 1984 in English and held by 1 WorldCat member library worldwide
1 edition published in 1984 in English and held by 1 WorldCat member library worldwide
Calculation of the Three Dimensional Particle Trajectories in a Turbine Stage(
)
1 edition published in 1972 in English and held by 1 WorldCat member library worldwide
The equations of motion, in three dimensions, of solid particles entrained by a gas flow through the stationary and rotating cascades of a turbine are derived. The gas velocity components and density at all the mesh points of a square grid constructed in the flow channels are computed assuming a compressible flow. Formulas to determine the proper drag on the particles for a wide range of Reynolds numbers are given. A gas particle flow tunnel is used to investigate experimentally the phenomenon of particle impact with the turbine blades or casing and their rebound from these walls. Formulas for the restitution ratio due to collision and the rebound to incidence angle ratio are derived. This information is used in the equations of motion of the solid particles
1 edition published in 1972 in English and held by 1 WorldCat member library worldwide
The equations of motion, in three dimensions, of solid particles entrained by a gas flow through the stationary and rotating cascades of a turbine are derived. The gas velocity components and density at all the mesh points of a square grid constructed in the flow channels are computed assuming a compressible flow. Formulas to determine the proper drag on the particles for a wide range of Reynolds numbers are given. A gas particle flow tunnel is used to investigate experimentally the phenomenon of particle impact with the turbine blades or casing and their rebound from these walls. Formulas for the restitution ratio due to collision and the rebound to incidence angle ratio are derived. This information is used in the equations of motion of the solid particles
Twodimensional flow losses of a turbine cascade with boundary layer injection by
W Tabakoff(
Book
)
1 edition published in 1972 in English and held by 1 WorldCat member library worldwide
1 edition published in 1972 in English and held by 1 WorldCat member library worldwide
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Related Identities
 American Society of Mechanical Engineers Fluids Engineering Division
 American Society of Mechanical Engineers
 American Institute of Aeronautics and Astronautics Propulsion Committee
 American Society of Mechanical Engineers Gas Turbine Division
 Crowe, C. T. (Clayton T.)
 Cale, D. B.
 American Society of Mechanical Engineers Gas Turbine Power Division
 CINCINNATI UNIV OHIO Dept. of AEROSPACE ENGINEERING
 Hamed, A. Author
 Carpenter, P. Author
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Associated Subjects
Aerodynamic heating Aerodynamics Aerodynamics, Hypersonic AirplanesMotors AirplanesRamjet enginesAir intakes Axial flow Boundary layer Cascades (Fluid dynamics) CompressorsBlades Differential equations Drag (Aerodynamics) Erosion Fluid dynamics Laminar boundary layer Laminar flow MaterialsErosion Numerical integration Shear flow Turbomachines TurbomachinesFluid dynamics TurbomachinesPerformance Turbulence Turbulent boundary layer Twophase flow