For a century, researchers have used the standard lift coefficient C(L) to evaluate the lift, L, generated by fixed wings over an area S against dynamic pressure, ½ρv(2), where v is the effective velocity of the wing. Because the lift coefficient was developed initially for fixed wings in steady flow, its application to other lifting systems requires either simplifying assumptions or complex ad...

determining characteristics and behavior of fluid flow and obtaining the aerodynamic coefficients are important and considerable tasks in investigation of flow over the bodies. in this research, leading edge radius effects on the flow behavior over a delta wing with a sweep angle of 50 degree at different reynolds numbers between 0.5×106 and 2.5×106 are investigated numerically. three different...

the steger and warming flux vector splitting implicit scheme is used to numerically solve two dimensional reynolds averaged navier–stokes (rans) equations governing the vortex induced vibration of a flexible riser laterally supported by a spring and a damper. the k–ε model is used as turbulence model to simulate the turbulent flow in the wake of the riser. to update the new position of the rise...

We study here the motion of a spherical gas bubble in a solid body rotating flow of clean silicon oil, to avoid contamination of interface. From the measurement of its equilibrium position, lift and drag forces are determined. Five different silicon oils have been used, providing five different viscosities and Morton numbers. For spherical bubbles the drag coefficient is at first order the same...

Numerical investigation of flow around a square cylinder are presented using the multi-relaxation-time lattice Boltzmann methods at different Reynolds numbers. A detail analysis are given in terms of time-trace analysis of drag and lift coefficients, power spectra analysis of lift coefficient, vorticity contours visualizations, streamlines and phase diagrams. A number of physical quantities mea...

Due to the interference effects, the intrinsic aerodynamic parameters obtained from the individual component testing are always fundamentally different than those obtained for complete model testing. Consideration and limitation for such testing need to be taken into account in any design work related to the component buildup method. In this paper, the scaled model of a straight rectangular can...

An innovative step change is required to improve or replace the current mechanically deployed leading edge high lift systems for civil transport aircraft. This paper provides a review of existing leading edge device technologies for high lift and possible future technologies based on flow control. There is an emphasis on those flow control technologies that will be sufficiently mature enough fo...

The capability of flapping wings to generate lift is currently evaluated by using the lift coefficient CL, a dimensionless number that is derived from the basal equation that calculates the steady-state lift coefficient CL for fixed wings. In contrast to its simple and direct application to fixed wings, the equation for CL requires prior knowledge of the flow field along the wing span, which re...

Submit Manuscript | http://medcraveonline.com Abbreviations: c: chord; u∞ : Free Stream Velocity; ν: Kinematic Viscosity; Re: Chord Reynolds number, ( ) / u c n ∞ = ; OGE: Out of the Ground Effect; GE: Ground Effect; Cd: Sectional Drag Coefficient; Cdp: Sectional Pressure Drag Coefficient; Cl: Sectional Lift Coefficient; Cl,max: Maximum Cl; l C α :Lift-Curve Slope; Cm: Sectional Pitching Moment...