Lift Coefficient Research Papers - Academia.edu (original) (raw)

The flow over multi-element airfoils has been numerically investigated in ansys fluent and has been compare the aerodynamic parameters with the standard NACA airfoils 4412 and 0012. The 2D viscous, transient, pressure model equations together with the k-ω turbulence model were applied to this numerical simulation utilizing the multi-block unstructured grids of sphere of influence type. Numerical results showed that the aerodynamic parameters of multi element airfoils with tail effect is much optimum than the standard naca airfoils. Also the analysis is made on different flap and slat angles of different conditions and the optimization of multi element airfoils has been performed.

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- Lift Coefficient, Structured Grids, High Lift Devices

The aim of this paper is to investigate the vortex structures as well as lift and drag coefficients in flows around a square cylinder in compare with circular cylinder using the commercial Fluent software. Furthermore, the effect of the Reynolds number on the formation of the vortex structures as well as velocity field is investigated and compared for both circular and square cylinder at different times. The results show the good agreements of the drag coefficient, lift coefficient and the Strouhal number with the previous studies. Moreover, the results show that the lift coefficient is increased strongly when the Reynolds number increases; however, the drag coefficient and the Strohoul number do not change noticeably. Furthermore, increasing the Reynolds number causes that the fluctuations in lift and drag coefficients start at an earlier time.

- by Taha Khademinejad and +1
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- Computational Fluid Dynamics, Lift Coefficient, Drag Coefficient, Square Cylinder

The wing of aircraft is designed according to the mission or operational purposes. In the design, maintenance and operations of training aircrafts, cost, reliability and safety are some of the most important parameters to consider. Wing performances are not just determined by their aerodynamic characteristics but also their structural characteristics which is the ability to sustain both internal and external loads. In addition to the internal weights of the spars, ribs, stringers, landing gear and tanks, the fuel load and aerodynamic loads are external forces that act on the structure and exert pressure on it. This paper will concentrate on the structural design of the wing of a two-seater trainer aircraft. The report addresses both modeling and simulation in order to evaluate the wing structural performances. The modeling is performed using SolidWorks and the simulation using ANSYS. Also, a MATLAB m-file coding is used to generate the wing external dimensions. The result of the simulation is then analyzed and interpreted. At the end, a construction of V-n diagram for the designed wing is achieved.

Flow past a square cylinder with and without corner modifications is carried out numerically by using CFD
fluent. The wake is generated by a uniform flow of Reynolds number (Re) 150 based on the characteristic length
of the cylinder, D. 2D unsteady numerical simulation is done using FVM employing pressure based solver and
PISO scheme. A computational grid independence study has been done to obtain a grid resolution which predicts
the results without any discrepancies. The flow separation point for the square cylinder with and without corner
modifications is obtained. The pressure distribution in the near wake region and around the square cylinder
surface is also investigated for different corner geometries. The results are presented in the form of coefficient of
pressure Vs Domain length/D, Coefficient of pressure along the cylinder wall and wall shear stress along the
cylinder wall. The results indicate that the flow separation in case of square cylinder without sharp corners is
delayed. The adverse pressure gradient along the surface of the cylinder and in the near wake region is smaller
for round corners. The tangential velocity of square cylinder with sharp corners is large when compared with
modified corners.
Keywords: Square Cylinder, Corner modifications, Reynolds number, wake, grid independence, flow separation
point, Pressure distribution, Lift coefficient, Drag coefficient.

- by IJRAME Journal and +1
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- Flat plate, Lift Coefficient, Drag Coefficient, Square Cylinder

In this work, Numerical study of Fluid Structure Interaction of uniform flow past a two dimensional pleated airfoil
is carried out. When the wing interact with the air, it is subjected to both aerodynamic forces acting on the surface
of the wing and the inertial force due to the acceleration of deceleration of the wing mass. The interaction between
these inertial and aerodynamic forces resulted in wing deformation. The dynamics of a pleated insect wing
subjected to aerodynamic loading is studied. The vortex induced vibration and forced vibration of a pleated flexible
insect wing subjected to aerodynamic load is studied by using ANSYS-14 multi physics solver. The insect wing is
of dragonfly wing cross section. In the first phase of the work, fluid flow simulation at Reynolds Number-100, 200,
500, and 1000 will be performed with angle of attack 00
to 150
. The result from the CFD solver will be fed in the
form of lift and drag forces are then fed into the ANSYS Workbench solver and one way Fluid Structure
Interaction analysis is performed.
Keyword: Lift Coefficient, Drag Coefficient, Angle of Attack, Reynolds No, Deflection

- by IJRAME Journal
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- Aerospace Engineering, Aeronautical Engineering, Airfoil, Lift Coefficient
- by shah man
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- Heat Transfer, Auv, Towing tank testing, Free Surface

Flow past a square cylinder with and without corner modifications is carried out numerically by using CFD
fluent. The wake is generated by a uniform flow of Reynolds number (Re) 150 based on the characteristic
length of the cylinder, D. 2D unsteady numerical simulation is done using FVM employing pressure based
solver and PISO scheme. A computational grid independence study has been done to obtain a grid resolution
which predicts the results without any discrepancies. The flow separation point for the square cylinder with and
without corner modifications is obtained. The pressure distribution in the near wake region and around the
square cylinder surface is also investigated for different corner geometries. The results are presented in the
form of coefficient of pressure Vs Domain length/D, Coefficient of pressure along the cylinder wall and wall
shear stress along the cylinder wall. The results indicate that the flow separation in case of square cylinder
without sharp corners is delayed. The adverse pressure gradient along the surface of the cylinder and in the
near wake region is smaller for round corners. The tangential velocity of square cylinder with sharp corners is
large when compared with modified corners.
Keywords: Square Cylinder, Corner modifications, Reynolds number, wake, grid independence, flow
separation point, Pressure distribution, Lift coefficient, Drag coefficient.

- by Daniele Pucci
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- Atmospheric Modeling, Vehicle Dynamics, Aerodynamics, Trajectory
- by saide saidi
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- Engineering, Finite Volume Methods, Fluids, Turbulent Flow

The dragonfly wings are highly corrugated, due to light in weight and good corrugation it increases the
aerodynamic performance and strength of the wing. When the wings interact with the air, it is subjected to
aerodynamic forces acting on the surface of the wing and the inertial force due to the acceleration or deceleration of
the wing mass. The interaction between these inertial and aerodynamic forces resulted in wing deformation. We are
interesting to calculate deformation and natural frequency of the dragon fly wing at different Reynolds number and
different angle of attack. A dragonfly insect has been chosen because MAVs (Micro air Vehicles) and Dragonfly
works almost same Reynolds Number i.e. Re- 102 to 104
. In this work, Numerical study of Vibration Analysis for a
Pleated Insect 2D Airfoil at Ultra Low Reynolds Numbers is carried out in gliding mode. The dynamics of a
pleated insect wing subjected to aerodynamic loading is studied for different Reynolds Number ranging from 100
to 1000 at different angle of attack ranging from 00 to 150
by using ANSYS-14 multi physics solver. The result
from the CFD solver will be fed in the form of lift and drag forces are then fed into the ANSYS Workbench solver
and vibration analysis is performed.
Keywords: Lift Coefficient, Drag Coefficient. Angle of Attack, Reynolds No, Deflection, Natural Frequency.

- by IJRAME Journal
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- Vibrations, VIBRATION ANALYSIS, Natural Frequency, Gliding
- by sachin paramane
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- Mechanical Engineering, Applied Mathematics, Modeling, Heat Transfer
- by Detlef Lohse
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- Engineering, Fluid Mechanics, Particle Image Velocimetry, Flow Control
- by fabian moraga
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- Engineering, Data Analysis, Multiphase Flow, Two Phase Flow
- by Detlef Lohse
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- Engineering, Fluid Mechanics, Two Phase Flow, Direct Numerical Simulation

Vortex shedding is one of the most interesting phenomenon in turbulent flow. This phenomenon was first studied by Strouhal. In this paper, the analysis of vortex shedding around a 2 dimensional circular cylinder with Reynolds No of 200, 500, and 1000 with different angle of attack 0 0 , 5 0 , and 10 0 has been studied. In this simulation an implicit pressure-based finite volume method and second order implicit scheme is used. Flow has been studied with the help of Navier-Stokes and continuity equations. The pressure, drag coefficients and vortex shedding for different Reynolds numbers and different angle of attack were computed and compared with other numerical result that show good agreement.

- by IJREI Journal
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- Lift Coefficient, Reynolds Number
- by Sakir Amiroudine
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- Mechanical Engineering, Aerospace Engineering, Applied Mathematics, Geology

Having access to high speed diving without the use of mechanical science and discovery centers have been considered. Production of simple, yet effective tool to reduce energy consumption and associated diver is very valuable. Assistant diver device that works with human muscle power, includes a pair of ballets. This system reduces the energy required to dive to less than half as the speed increases to 2 to 5 knot. Using numerical methods can answer a lot of questions and a simulation of the dynamic behavior of the device. In this article, modeling of fluid flow around the Diver helper of FLUENT software and using Dynamic Mesh have been done. Flow lines show an increase in the angle of the fins and causes development of vortices behind them. Pressure Cantor can also be used in the analysis of the fins. The drag coefficient ballet based on the device at various angles in a period is reported in charts.

The behavior of different add-on parts to a basic car model has been studied experimentally.Experiments were conducted with different add-on parts, like rear end spoiler & front end spoiler in order to find out how these add-on parts influence the drag and lift coefficients of a basic car model. The experiment was done in Jadavpur University low turbulence subsonic closed circuit wind tunnel at different Reynolds number.The results from the experiment indicated that the addition of different add-on parts like front end spoiler and rear end spoiler to a basic car model reduces the lift coefficient to a considerable amount while the drag coefficient is reduced by a small amount. It was concluded that the addition of these add-on parts like rear-end spoiler etc increases the aerodynamic stability of a basic car model and hence they can be used in real life which will be an added advantage.

- by Debojyoti Mitra
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- Lift Coefficient, Drag Coefficient
- by Sergio Nardini
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- Mechanical Engineering, Aerospace Engineering, Applied Mathematics, Geology

The behavior of different add-on parts to a basic car model has been studied experimentally .Experiments were conducted with different add-on parts, like rear end spoiler & front end spoiler in order to find out how these add-on parts influence the drag and lift coefficients of a basic car model. The experiment was done in Jadavpur University low turbulence subsonic closed circuit wind tunnel at different Reynolds number .The results from the experiment indicated that the addition of different add-on parts like front end spoiler and rear end spoiler to a basic car model reduces the lift coefficient to a considerable amount while the drag coefficient is reduced by a small amount. It was concluded that the addition of these add-on parts like rear-end spoiler etc increases the aerodynamic stability of a basic car model and hence they can be used in real life which will be an added advantage.

- by Debojyoti Mitra
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- Vehicle Aerodynamics, Engineering Science, Lift Coefficient, Drag Coefficient
- by Dominique Legendre
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- Engineering, Fluid Mechanics, Interaction, Dynamics
- by Oronzio Manca
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- Mechanical Engineering, Aerospace Engineering, Applied Mathematics, Geology
- by Jose E . Wesfreid
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- Mechanical Engineering, Fluid Mechanics, Vortex shedding, Drag Force
- by Sakir Amiroudine
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- Mechanical Engineering, Aerospace Engineering, Applied Mathematics, Geology
- by Federico Toschi
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- Engineering, Fluid Mechanics, Two Phase Flow, Direct Numerical Simulation
- by Dr. Hazim Moria
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- Aerodynamics, Multidisciplinary, Wind Tunnel, Flow visualisation