hayder kraidi - Academia.edu (original) (raw)

Papers by hayder kraidi

Industrial Engineering Letters, 2013

The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To contr... more The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To control the location of separation point, the turbulent flow was generated. To induce turbulent pattern, flow was disrupted by two adjacent circular cylinders in upstream of airfoil with 10 mm diameter for each cylinder. An experimental technique based on smoke wind tunnel with different air flow velocities (1.7 m/s and 2.5 m/s) was provided. The conjunction between the effect of the angles of attack and flow visualization around the airfoil NACA 2412 was verification. The angles of attack (0, 5 and 10) degree was used for each air flow velocity. ANSYS program software used to simulate and comparison all the experimental results. The experimental and numerical results showed, when the angle of attack increase, the location of the separation point was shifted toward the airfoil NACA 2412 leading edge. Also, effect of the wake of two cylinders on the location of the separation point was very clear. The vortex induced beyond the cylinders and upstream the airfoil help to prevent separation growth, thereby, the turbulent provided will accelerated the flow around the airfoil geometry and the adverse pressure in that location was decreased. So, the increases in airflow velocity will help the turbulent boundary layer to growth. The growth of turbulent flow boundary layer tends to avoid separation and the flow will reattached. Moreover, the accuracy of results were checked by validation the Kutta-condition experimentally and numerically. Keywords: Boundary layer control, airfoil NACA 2412, flow visualization, smoke wind tunnel Nomenclature Cp = pressure coefficient D=cylinder diameter 10mm p = pressure, N/m2 Re=Reynolds number u, v = velocity components in boundary layer in x and y direction respectively , m/s V= average velocity m/s x, y = cartesian coordinates Greek symbols α =angle of attack deg. ρ=air flow density kg/m 3 µ= viscosity N.m/s Subscript D=cylinder diameter c=airfoil chord

AIP Conference Proceedings

Journal of Babylon University, 2016

This paper estimates the sound and flow generated by a turbulent air flow in a duct from the know... more This paper estimates the sound and flow generated by a turbulent air flow in a duct from the knowledge of mean quantities (average velocity and sound pressure level).The sound excitation by fluid flow through duct can be used to predict fluid behavior. This behavior can be carried out by discovering the relation between sound excitation and fluid flow parameters like Reynolds number, Strouhal number and frequencies of turbulent fluid flow. However, the fluid flow container stability has to be taken in account simultaneously with fluid flow effect on sound generation and propagation. The experimental system used in this work is air flow through subsonic wind tunnel duct.The sound pressure levels of air flows through test section of subsonic wind tunnel (at three air flow velocities2.5, 7.3 and 12.5 m/s) respectively were carried out experimentally. The sound excitation or generation by air flow throughout the test section of subsonic wind tunnel without any obstruction can't be u...

Industrial Engineering Letters, 2019

The high speed cutting tools that made from ceramic materials, alumina based, it is very importan... more The high speed cutting tools that made from ceramic materials, alumina based, it is very important for the machining process. It has a hot hardness and abrasive resistance and chemical stability at the high temperature, but it has a brittleness and low fracture strength. In this study, synthesis samples from the α-alumina(Al2O3) doping with magnesia (MgO) with different percentage (0.35, 0.75, 1.1 % wt.) and compare with the pure alumina properties. It is using cold uniaxial pressing (200 MPa) and sintered at (1500ᵒC) remain three hours for this samples. The purpose was to study the effect of the doping on the mechanical and physical properties and the ability to enhancing it. Numerical simulation was worked for the contact and friction between the ceramic cutting tool and the workpiece material (AISI 1006 steel). This numerical methods dependent on ABAQUS Ver.6.14 program. The results show that ability of cutting and chip formation and successfully propagation through this type of cutting tools without failure it at high speed (150-250)m/min. Also, the stress and heat generated due to ceramic cutting tool was presented The result appeared increasing in the hardness and the density value by the doping with MgO. By increase the percentage of magnesia that given enhanced the properties. The MgO as a second phase reduce alumina grain size and increase the hardness and the wear resistance to cutting tools. Small amount of magnesia enhanced the densification rate grain growth and accelerate the sintering rate. The magnesia doping enable to sinter the mixture alumina-magnesia to near theoretical density. The best result was found with 0.75% MgO at 1500 o C (HV 19GPa).

International Conference on Computer and Electrical Engineering 4th (ICCEE 2011), 2011

Introduction The study of composite materials, i.e., mixtures consisting of at least two phases o... more Introduction The study of composite materials, i.e., mixtures consisting of at least two phases of different chemical compositions, has been of great interest fro m both fundamental and practical standpoints. The macroscopic physical p roperties of such materials can be co mbined so as to produce materials with a desired average response. [1]. The properties of poly me r-mineral reinforced composites are determined by the co mponent properties (particle shape, surface area, surface chemistry, poly mer microstructure) and by the preparation method and processing conditions as well. A mong of preparation methods, injection mo lding has strong influence on the internal microstructure of polymers and in a consequence on mechanical response of the material [2]. Doping of poly mers attracted the scientific and technological researchers , because of their wide applications. The dopants in polymer can change the molecular structure and hence the microstructure as well as the macroscopic properties of the polymer [3]. Po lyvinyl alcohol (PVA), which is essentially made fro m polyvinyl acetate through hydrolysis, is easily degradable by bio logical organis ms and in water is a solubilized crystalline structure polymer [4]. PVA is formed by the polymerizat ion of vinyl acetate, which is then hydrolyzed into PVA. Fig. 1 shows the chemical structure of PVA. The excellent chemical resistance and physical p roperties of PVA resins have led to broad industrial use [5]. PVA is a low cost hydrophilic poly mer and therefore swells in the presence of water or bio logical flu ids to form hydrogels. This property is particularly useful because it can allow for the release of drugs incorporated into these hydrogels. Since PVA has a high selectivity of water to alcohols, it exhibits low methanol permeab ility and has been used in some alkaline fuel cell [6-7]. PVA is an artificial polymer that has been used during the first half of the century worldwide. It has been applied in the industrial, co mmercial, med ical, and food sectors and has been used to produce many end products, such as lacquers, resins, surgical threads, and food packaging materials that are often in contact with food [8]

Industrial Engineering Letters, 2013

The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To contr... more The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To control the location of separation point, the turbulent flow was generated. To induce turbulent pattern, flow was disrupted by two adjacent circular cylinders in upstream of airfoil with 10 mm diameter for each cylinder. An experimental technique based on smoke wind tunnel with different air flow velocities (1.7 m/s and 2.5 m/s) was provided. The conjunction between the effect of the angles of attack and flow visualization around the airfoil NACA 2412 was verification. The angles of attack (0, 5 and 10) degree was used for each air flow velocity. ANSYS program software used to simulate and comparison all the experimental results. The experimental and numerical results showed, when the angle of attack increase, the location of the separation point was shifted toward the airfoil NACA 2412 leading edge. Also, effect of the wake of two cylinders on the location of the separation point was very c...

Many researchers have been tried to discuss the parameters that used to enhance the heat transfer... more Many researchers have been tried to discuss the parameters that used to enhance the heat transfer rate within different shapes of enclosure that exerted by an external magnetic field with a lid driven. So, in this research, combined effect of non-Newtonian fluid that contains Nanoparticles Al2O3 within new square enclosure heat geometry shapes (four cases that will be elaborated in this research: case I :small wavy notched shape, case II: small semicircle notched, case III: bigger semicircle notched and the last one case IV has a large wavy notched) have been solved numerically by finite element method that base on the Galerkin weighted residual formulation where used in COMSOL Multiphasic under a relevant dimensionless parameters: 0.001  Ri  1, 0  Ha  60, solid volume fraction 0    0.1, power law index 0.2  n  1.4, Grashof

Industrial Engineering Letters, 2013

The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To contr... more The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To control the location of separation point, the turbulent flow was generated. To induce turbulent pattern, flow was disrupted by two adjacent circular cylinders in upstream of airfoil with 10 mm diameter for each cylinder. An experimental technique based on smoke wind tunnel with different air flow velocities (1.7 m/s and 2.5 m/s) was provided. The conjunction between the effect of the angles of attack and flow visualization around the airfoil NACA 2412 was verification. The angles of attack (0, 5 and 10) degree was used for each air flow velocity. ANSYS program software used to simulate and comparison all the experimental results. The experimental and numerical results showed, when the angle of attack increase, the location of the separation point was shifted toward the airfoil NACA 2412 leading edge. Also, effect of the wake of two cylinders on the location of the separation point was very clear. The vortex induced beyond the cylinders and upstream the airfoil help to prevent separation growth, thereby, the turbulent provided will accelerated the flow around the airfoil geometry and the adverse pressure in that location was decreased. So, the increases in airflow velocity will help the turbulent boundary layer to growth. The growth of turbulent flow boundary layer tends to avoid separation and the flow will reattached. Moreover, the accuracy of results were checked by validation the Kutta-condition experimentally and numerically. Keywords: Boundary layer control, airfoil NACA 2412, flow visualization, smoke wind tunnel Nomenclature Cp = pressure coefficient D=cylinder diameter 10mm p = pressure, N/m2 Re=Reynolds number u, v = velocity components in boundary layer in x and y direction respectively , m/s V= average velocity m/s x, y = cartesian coordinates Greek symbols α =angle of attack deg. ρ=air flow density kg/m 3 µ= viscosity N.m/s Subscript D=cylinder diameter c=airfoil chord

Industrial Engineering Letters, 2013

The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To contr... more The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To control the location of separation point, the turbulent flow was generated. To induce turbulent pattern, flow was disrupted by two adjacent circular cylinders in upstream of airfoil with 10 mm diameter for each cylinder. An experimental technique based on smoke wind tunnel with different air flow velocities (1.7 m/s and 2.5 m/s) was provided. The conjunction between the effect of the angles of attack and flow visualization around the airfoil NACA 2412 was verification. The angles of attack (0, 5 and 10) degree was used for each air flow velocity. ANSYS program software used to simulate and comparison all the experimental results. The experimental and numerical results showed, when the angle of attack increase, the location of the separation point was shifted toward the airfoil NACA 2412 leading edge. Also, effect of the wake of two cylinders on the location of the separation point was very clear. The vortex induced beyond the cylinders and upstream the airfoil help to prevent separation growth, thereby, the turbulent provided will accelerated the flow around the airfoil geometry and the adverse pressure in that location was decreased. So, the increases in airflow velocity will help the turbulent boundary layer to growth. The growth of turbulent flow boundary layer tends to avoid separation and the flow will reattached. Moreover, the accuracy of results were checked by validation the Kutta-condition experimentally and numerically. Keywords: Boundary layer control, airfoil NACA 2412, flow visualization, smoke wind tunnel Nomenclature Cp = pressure coefficient D=cylinder diameter 10mm p = pressure, N/m2 Re=Reynolds number u, v = velocity components in boundary layer in x and y direction respectively , m/s V= average velocity m/s x, y = cartesian coordinates Greek symbols α =angle of attack deg. ρ=air flow density kg/m 3 µ= viscosity N.m/s Subscript D=cylinder diameter c=airfoil chord

Industrial Engineering Letters, 2013

The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To contr... more The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To control the location of separation point, the turbulent flow was generated. To induce turbulent pattern, flow was disrupted by two adjacent circular cylinders in upstream of airfoil with 10 mm diameter for each cylinder. An experimental technique based on smoke wind tunnel with different air flow velocities (1.7 m/s and 2.5 m/s) was provided. The conjunction between the effect of the angles of attack and flow visualization around the airfoil NACA 2412 was verification. The angles of attack (0, 5 and 10) degree was used for each air flow velocity. ANSYS program software used to simulate and comparison all the experimental results. The experimental and numerical results showed, when the angle of attack increase, the location of the separation point was shifted toward the airfoil NACA 2412 leading edge. Also, effect of the wake of two cylinders on the location of the separation point was very clear. The vortex induced beyond the cylinders and upstream the airfoil help to prevent separation growth, thereby, the turbulent provided will accelerated the flow around the airfoil geometry and the adverse pressure in that location was decreased. So, the increases in airflow velocity will help the turbulent boundary layer to growth. The growth of turbulent flow boundary layer tends to avoid separation and the flow will reattached. Moreover, the accuracy of results were checked by validation the Kutta-condition experimentally and numerically. Keywords: Boundary layer control, airfoil NACA 2412, flow visualization, smoke wind tunnel Nomenclature Cp = pressure coefficient D=cylinder diameter 10mm p = pressure, N/m2 Re=Reynolds number u, v = velocity components in boundary layer in x and y direction respectively , m/s V= average velocity m/s x, y = cartesian coordinates Greek symbols α =angle of attack deg. ρ=air flow density kg/m 3 µ= viscosity N.m/s Subscript D=cylinder diameter c=airfoil chord

AIP Conference Proceedings

Journal of Babylon University, 2016

This paper estimates the sound and flow generated by a turbulent air flow in a duct from the know... more This paper estimates the sound and flow generated by a turbulent air flow in a duct from the knowledge of mean quantities (average velocity and sound pressure level).The sound excitation by fluid flow through duct can be used to predict fluid behavior. This behavior can be carried out by discovering the relation between sound excitation and fluid flow parameters like Reynolds number, Strouhal number and frequencies of turbulent fluid flow. However, the fluid flow container stability has to be taken in account simultaneously with fluid flow effect on sound generation and propagation. The experimental system used in this work is air flow through subsonic wind tunnel duct.The sound pressure levels of air flows through test section of subsonic wind tunnel (at three air flow velocities2.5, 7.3 and 12.5 m/s) respectively were carried out experimentally. The sound excitation or generation by air flow throughout the test section of subsonic wind tunnel without any obstruction can't be u...

Industrial Engineering Letters, 2019

The high speed cutting tools that made from ceramic materials, alumina based, it is very importan... more The high speed cutting tools that made from ceramic materials, alumina based, it is very important for the machining process. It has a hot hardness and abrasive resistance and chemical stability at the high temperature, but it has a brittleness and low fracture strength. In this study, synthesis samples from the α-alumina(Al2O3) doping with magnesia (MgO) with different percentage (0.35, 0.75, 1.1 % wt.) and compare with the pure alumina properties. It is using cold uniaxial pressing (200 MPa) and sintered at (1500ᵒC) remain three hours for this samples. The purpose was to study the effect of the doping on the mechanical and physical properties and the ability to enhancing it. Numerical simulation was worked for the contact and friction between the ceramic cutting tool and the workpiece material (AISI 1006 steel). This numerical methods dependent on ABAQUS Ver.6.14 program. The results show that ability of cutting and chip formation and successfully propagation through this type of cutting tools without failure it at high speed (150-250)m/min. Also, the stress and heat generated due to ceramic cutting tool was presented The result appeared increasing in the hardness and the density value by the doping with MgO. By increase the percentage of magnesia that given enhanced the properties. The MgO as a second phase reduce alumina grain size and increase the hardness and the wear resistance to cutting tools. Small amount of magnesia enhanced the densification rate grain growth and accelerate the sintering rate. The magnesia doping enable to sinter the mixture alumina-magnesia to near theoretical density. The best result was found with 0.75% MgO at 1500 o C (HV 19GPa).

International Conference on Computer and Electrical Engineering 4th (ICCEE 2011), 2011

Introduction The study of composite materials, i.e., mixtures consisting of at least two phases o... more Introduction The study of composite materials, i.e., mixtures consisting of at least two phases of different chemical compositions, has been of great interest fro m both fundamental and practical standpoints. The macroscopic physical p roperties of such materials can be co mbined so as to produce materials with a desired average response. [1]. The properties of poly me r-mineral reinforced composites are determined by the co mponent properties (particle shape, surface area, surface chemistry, poly mer microstructure) and by the preparation method and processing conditions as well. A mong of preparation methods, injection mo lding has strong influence on the internal microstructure of polymers and in a consequence on mechanical response of the material [2]. Doping of poly mers attracted the scientific and technological researchers , because of their wide applications. The dopants in polymer can change the molecular structure and hence the microstructure as well as the macroscopic properties of the polymer [3]. Po lyvinyl alcohol (PVA), which is essentially made fro m polyvinyl acetate through hydrolysis, is easily degradable by bio logical organis ms and in water is a solubilized crystalline structure polymer [4]. PVA is formed by the polymerizat ion of vinyl acetate, which is then hydrolyzed into PVA. Fig. 1 shows the chemical structure of PVA. The excellent chemical resistance and physical p roperties of PVA resins have led to broad industrial use [5]. PVA is a low cost hydrophilic poly mer and therefore swells in the presence of water or bio logical flu ids to form hydrogels. This property is particularly useful because it can allow for the release of drugs incorporated into these hydrogels. Since PVA has a high selectivity of water to alcohols, it exhibits low methanol permeab ility and has been used in some alkaline fuel cell [6-7]. PVA is an artificial polymer that has been used during the first half of the century worldwide. It has been applied in the industrial, co mmercial, med ical, and food sectors and has been used to produce many end products, such as lacquers, resins, surgical threads, and food packaging materials that are often in contact with food [8]

Industrial Engineering Letters, 2013

The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To contr... more The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To control the location of separation point, the turbulent flow was generated. To induce turbulent pattern, flow was disrupted by two adjacent circular cylinders in upstream of airfoil with 10 mm diameter for each cylinder. An experimental technique based on smoke wind tunnel with different air flow velocities (1.7 m/s and 2.5 m/s) was provided. The conjunction between the effect of the angles of attack and flow visualization around the airfoil NACA 2412 was verification. The angles of attack (0, 5 and 10) degree was used for each air flow velocity. ANSYS program software used to simulate and comparison all the experimental results. The experimental and numerical results showed, when the angle of attack increase, the location of the separation point was shifted toward the airfoil NACA 2412 leading edge. Also, effect of the wake of two cylinders on the location of the separation point was very c...

Many researchers have been tried to discuss the parameters that used to enhance the heat transfer... more Many researchers have been tried to discuss the parameters that used to enhance the heat transfer rate within different shapes of enclosure that exerted by an external magnetic field with a lid driven. So, in this research, combined effect of non-Newtonian fluid that contains Nanoparticles Al2O3 within new square enclosure heat geometry shapes (four cases that will be elaborated in this research: case I :small wavy notched shape, case II: small semicircle notched, case III: bigger semicircle notched and the last one case IV has a large wavy notched) have been solved numerically by finite element method that base on the Galerkin weighted residual formulation where used in COMSOL Multiphasic under a relevant dimensionless parameters: 0.001  Ri  1, 0  Ha  60, solid volume fraction 0    0.1, power law index 0.2  n  1.4, Grashof

Industrial Engineering Letters, 2013

The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To contr... more The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To control the location of separation point, the turbulent flow was generated. To induce turbulent pattern, flow was disrupted by two adjacent circular cylinders in upstream of airfoil with 10 mm diameter for each cylinder. An experimental technique based on smoke wind tunnel with different air flow velocities (1.7 m/s and 2.5 m/s) was provided. The conjunction between the effect of the angles of attack and flow visualization around the airfoil NACA 2412 was verification. The angles of attack (0, 5 and 10) degree was used for each air flow velocity. ANSYS program software used to simulate and comparison all the experimental results. The experimental and numerical results showed, when the angle of attack increase, the location of the separation point was shifted toward the airfoil NACA 2412 leading edge. Also, effect of the wake of two cylinders on the location of the separation point was very clear. The vortex induced beyond the cylinders and upstream the airfoil help to prevent separation growth, thereby, the turbulent provided will accelerated the flow around the airfoil geometry and the adverse pressure in that location was decreased. So, the increases in airflow velocity will help the turbulent boundary layer to growth. The growth of turbulent flow boundary layer tends to avoid separation and the flow will reattached. Moreover, the accuracy of results were checked by validation the Kutta-condition experimentally and numerically. Keywords: Boundary layer control, airfoil NACA 2412, flow visualization, smoke wind tunnel Nomenclature Cp = pressure coefficient D=cylinder diameter 10mm p = pressure, N/m2 Re=Reynolds number u, v = velocity components in boundary layer in x and y direction respectively , m/s V= average velocity m/s x, y = cartesian coordinates Greek symbols α =angle of attack deg. ρ=air flow density kg/m 3 µ= viscosity N.m/s Subscript D=cylinder diameter c=airfoil chord

Industrial Engineering Letters, 2013

The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To contr... more The vortex shedding effect on flow separation around airfoil NACA 2412 was investigated. To control the location of separation point, the turbulent flow was generated. To induce turbulent pattern, flow was disrupted by two adjacent circular cylinders in upstream of airfoil with 10 mm diameter for each cylinder. An experimental technique based on smoke wind tunnel with different air flow velocities (1.7 m/s and 2.5 m/s) was provided. The conjunction between the effect of the angles of attack and flow visualization around the airfoil NACA 2412 was verification. The angles of attack (0, 5 and 10) degree was used for each air flow velocity. ANSYS program software used to simulate and comparison all the experimental results. The experimental and numerical results showed, when the angle of attack increase, the location of the separation point was shifted toward the airfoil NACA 2412 leading edge. Also, effect of the wake of two cylinders on the location of the separation point was very clear. The vortex induced beyond the cylinders and upstream the airfoil help to prevent separation growth, thereby, the turbulent provided will accelerated the flow around the airfoil geometry and the adverse pressure in that location was decreased. So, the increases in airflow velocity will help the turbulent boundary layer to growth. The growth of turbulent flow boundary layer tends to avoid separation and the flow will reattached. Moreover, the accuracy of results were checked by validation the Kutta-condition experimentally and numerically. Keywords: Boundary layer control, airfoil NACA 2412, flow visualization, smoke wind tunnel Nomenclature Cp = pressure coefficient D=cylinder diameter 10mm p = pressure, N/m2 Re=Reynolds number u, v = velocity components in boundary layer in x and y direction respectively , m/s V= average velocity m/s x, y = cartesian coordinates Greek symbols α =angle of attack deg. ρ=air flow density kg/m 3 µ= viscosity N.m/s Subscript D=cylinder diameter c=airfoil chord