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

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- by
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- Engineering, Fluid Mechanics, Particle Image Velocimetry, Flow Control

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

Performance and efficiency of a Vertical Axis Wind Turbine improved by using a modified turbine blade, derived from biological features, by harness more wind energy. The detailed simulations were carried in Q-blade's X-foil, Java foil and Sim Scale software at low wind speed with bio-mimicable cambered foil add-ons to different biostructure blades such as Maple seed leaf, Eagle wing. Among these simulations, the Corrugated Dragonfly vein FX 63-137 foil shows improved performance over cambered foils and FX 63-37 itself. The Maple-Wing combined blade structure showed an improved lift-drag ratio with a high coefficient of power.

- by Zeal Press
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- Vorticity, Vertical Axis Wind Turbine (VAWT), Lift Coefficient, Drag Coefficient

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.

- by JASH MATHEW
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- Lift Coefficient, Structured Grids, High Lift Devices

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.

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

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 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 IJRAME Journal and +1
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- Flat plate, Lift Coefficient, Drag Coefficient, Square Cylinder
- by saide saidi
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- Engineering, Finite Volume Methods, Fluids, Turbulent Flow
- by Mirza Haseeb Khalid
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- Computational Fluid Dynamics, Airfoil, Lift Coefficient, Drag Coefficient

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 Mayuri Gore
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- Aerospace Engineering, Aerodynamics, Drag, Vortex

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

The hysteresis effect on the vortex induced vibration (VIV) on a circular cylinder is investigated by the numerical solution of the two-dimensional Reynolds averaged Navier-Stokes equations. An upwind and total variation diminishing (TVD) conservative scheme is used to solve the governing equations written in curvilinear coordinates and the k-ɛ turbulence model is used to simulate the turbulent flow in the wake of the body. The cylinder is supported by a spring and a damper and free to vibrate in the transverse direction. In previous work, numerical results for the amplitude of oscillation and vortex shedding frequency were compared to experimental data obtained from the literature to validate the code for VIV simulations. In the present work, results of practical interest are presented for the power absorbed by the system, phase angle, amplitude, frequency, and lift coefficient. The numerical results indicate that the hysteresis effect is observed only when the frequency of vortex ...

- by Carlos Levi
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- Mechanical Engineering, Civil Engineering, Mathematics, Turbulence
- by Dominique Legendre
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- Engineering, Fluid Mechanics, Interaction, Dynamics
- by Leon Glicksman
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- Engineering, Computational Fluid Dynamics, Fluidization, Heat and Mass Transfer
- by fabian moraga
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- Engineering, Data Analysis, Multiphase Flow, Two Phase Flow
- by Federico Toschi
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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 sachin paramane
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- Mechanical Engineering, Applied Mathematics, Modeling, Heat Transfer
- by Sakir Amiroudine
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- Mechanical Engineering, Aerospace Engineering, Applied Mathematics, Geology
- by Alberto Savino
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- Aerospace Engineering, Aerodynamics, Trailing edge noise, Morphing

1. A Harris' hawk with a mass of 0.702 kg and a maximum wing span of 1.02 m glided freely in a wind tunnel at air speeds between 6.1 and 16.2ms−1. The glide angle varied from 8.5% at the slowest speed to a minimum of 5% at speeds between 8.0 and 14.7 ms−1. The maximum ratio of lift to drag was 10.9 and the minimum sinking speed was 0.81ms−1 2. Wing span decreased when either air speed or glide angle increased. Wing area was a parabolic function of wing span 3. Lift and profile drag coefficients of the wings fell in a polar area similar to that for a laggar falcon (Falco jugger) and a black vulture (Coragyps atratus). A single polar curve relating lift coefficients to minimum profile drag coefficients can predict the maximum gliding performance of all three birds when used with a mathematical model for gliding flight 4. The parasite drag values that have been used with the model are probably too high. Thus, the profile drag coefficients determined from the polar curve mentioned a...

- by Carlton Heine
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- Performance, Aerodynamics, Biological Sciences, Raptor
- by ali bousri
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- Engineering, Applied Mathematics, Geology, Geophysics
- by Dr. Hazim Moria
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- Aerodynamics, Multidisciplinary, Wind Tunnel, Flow visualisation
- by Oronzio Manca
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- Mechanical Engineering, Aerospace Engineering, Applied Mathematics, Geology

In the work of Fischer et al. (2002, “Forces on Particles in an Oscillatory Boundary Layer,” J. Fluid Mech., 468, pp. 327–347, 2005; “Influence of Wall Proximity on the Lift and Drag of a Particle in an Oscillatory Flow,” ASME J. Fluids Eng., 127, pp. 583–594) we computed the lift and drag forces on a sphere, subjected to a wall-bounded oscillatory flow. The forces were found as a function of the Reynolds number, the forcing frequency, and the gap between the particle and the ideally smooth rigid bounding wall. Here we investigate how the forces change as a function of the above parameters and its moment of inertia if the particle is allowed to freely rotate. Allowing the particle to rotate does not change appreciably the drag force, as compared to the drag experienced by the particle when it is held fixed. Lift differences between the rotating and nonrotating cases are shown to be primarily dominated in the mean by the pressure component. The lift of the rotating particle varies si...

- by Juan M. Restrepo
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- Engineering, Physics, Two Phase Flow, Oscillations

Mean drag and lift coefficients were studied for groups of two, three, and four circular cylinders arranged in-line, in both smooth and turbulent flow conditions. Effects of varying surface roughness and cylinder size were also investigated. Reynolds numbers for the tests ranged from 2.7×104 to 8.6×104. The majority of the tests were conducted with cylinder arrays sequentially arranged, with their

The paper presents the ground effects on the flow over five NACA symmetrical airfoils by analyzing the coefficients of lift. The unbounded flow over a selected airfoil was first simulated, and the results were validated against the established data in order to validate the method used in obtaining the lift coef icients. In the presence of ground, we kept the angle of attack to be constantly zero throughout the computations. Ground clearances were set based on those for aircrafts whose wing cross sections are the airfoils of interest. ANSYS was used for such numerical computations. We illustrate percentage increment of lift that isinversely proportional to the ground clearance. This work sheds insight on the important parameters that need to be taken into account in the operational of an aircraft.

- by IAEME Publication
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- Aerodynamics, Lift Coefficient, Ground Clearance, Iaeme Ijmet
- by Sergio Nardini
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- Mechanical Engineering, Aerospace Engineering, Applied Mathematics, Geology
- by Daniele Pucci
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- Atmospheric Modeling, Vehicle Dynamics, Aerodynamics, Trajectory
- by Detlef Lohse
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- Engineering, Fluid Mechanics, Numerical Simulation, Mathematical Sciences
- by Sakir Amiroudine
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- Mechanical Engineering, Aerospace Engineering, Applied Mathematics, Geology

The Karman Vortex Street generated by a circular cylinder is investigated by the numerical solution of the compressible Navier–Stokes equations in the incompressible Mach number range (Mach&lt;0.3) using the Beam and Warming implicit scheme. The agreement with the fully incompressible projection method (Chorin, 1968) is fairly good while convergence time is very much better. The investigation suggests that the compressible

- by Juan Wanderley
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- Civil Engineering, Ocean Engineering, Computational Fluid Dynamics, Hydraulics