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About 10,000 papers for “Trailing edge”

Trailing-Edge Flow

Anatoly I. Ruban · Fluid Dynamics · 2017

Abstract Chapter 3 focuses on the high-Reynolds number flow of an incompressible fluid near the trailing edge of a flat plate. It begins with Goldstein’s (1930) solution for a viscous wake behind the plate, and shows that the displacement effect of the wake produces a singular pressure gradient near the trailing edge. It further shows that this singularity leads to a formation triple-deck viscous-inviscid interaction region that occupies a small vicinity of the trailing edge. A detailed analysis of the flow in each tier of the triple-deck structure is conducted based on the asymptotic analysis of the Navier–Stokes equations. As a result, the so-called ‘interaction problem’ is formulated. It concludes with the numerical solution of so-called ‘interaction problem’.

Cited by 0

Trailing Edge Noise . . .

J. Casper, F. Farassat · 2002

A new analytic result in acoustics called \\Formulation 1B," proposed by Farassat, is used to compute broadband trailing edge noise from an unsteady surface pressure distribution on a thin airfoil in the time domain. This formulation is a new solution of the Ffowcs Williams-Hawkings equation with the loading source term, and has been shown in previous research to provide time domain predictions of broadband noise that are in excellent agreement with experiment. Furthermore, this formulation lends itself readily to rotating reference frames and statistical analysis of broadband trailing edge noise. Formulation 1B is used to calculate the far eld noise radiated from the trailing edge of a NACA 0012 airfoil in low Mach number ows, using both analytical and experimental data on the airfoil surface. The results are compared to analytical results and experimental measurements that are available in the literature. Good agreement between predictions and measurements is obtained.

Cited by 0

Trailing edge noise

Ewert, Roland, Manoha, Eric · elib (German Aerospace Center) · 2007

- Introduction to trailing-edge noise simulation using LES
\n- Trailing-edge noise simulation using LES and APE
\n- Trailing-edge nosie simulation using LES, Euler equations and the Kirchhoff Integral
\n- Unsteady pressure-field analysis
\n-

Cited by 0

Trailing Edge Noise

American Institute of Aeronautics and Astronautics eBooks · 1976

- Introduction to trailing-edge noise simulation using LES - Trailing-edge noise simulation using LES and APE - Trailing-edge nosie simulation using LES, Euler equations and the Kirchhoff Integral - Unsteady pressure-field analysis -

Cited by 4

Trailing-Edge Flap Placement

Ranjan Ganguli, Dipali Thakkar, Sathyamangalam Ramanarayanan Viswamurthy · Advances in industrial control · 2015

Cited by 0

Trailing-Edge Flow by

Vagesh D. Narasimhamurthy, Vagesh D. Narasimhamurthy, Chalmers Tekniska Högskola et al. · 2015

Unsteady RANS (Reynolds Averaged Navier Stokes) computations of turbulent trailing-edge ow have been carried out at a Reynolds number of 1000 (based on the free-stream quantities and the trailing-edge thick-ness) using a 3D Finite Volume code, in which a Low Reynolds Number (LRN) model and model were implemented. The realizability constraints suggested by Durbin was also implemented in the models to study their effect on the unsteady vortex shedding. Central differenc-ing scheme was used for all the computations, but van-Leer scheme was also tried in order to study the inuence of numerical schemes on un-steady vortex shedding. Results from a Direct Numerical Simulation (DNS) of the same ow are available for comparison and assessment of turbulence models used in the URANS code. Two-dimensional URANS calculations are carried out

Cited by 0

Helicopter rotor trailing edge noise /

Schlinker, Robert H., Amiet, Roy K., United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch. et al. · The Journal of the Abraham Lincoln Association

Cited by 0Open access

Working with the trailing edge

George Hagman, Susanne Weil · 2019

There comes a point for some patients in psychoanalytic therapy when they experience the treatment as a threat. Often this occurs early on when the vulnerability so necessary to the process feels dangerous to them. Rather than risk a relationship with the analyst they demur, disengage, and assume a “resistant” stance. The analyst may be disoriented, frustrated and perhaps even despairing. A protracted impasse may result. This chapter explores this form of cotransference from the perspective of ISP as being characterized by the interaction of the patient’s and the analyst’s fears of failure and longings for success. With the aid of a dramatic case illustration, the authors show how these reciprocally interacting needs and dreads contribute to the development of treatment impasses as well as opportunities for effective interpretation and therapeutic change.

Cited by 2

Blade Trailing Edge Heat Transfer

Andy Brown, B. Mandjikas, J. M. Mudyiwa · 1980

In this article measurements of heat transfer, pressure loss, and friction factor inside simulated trailing edges of turbine blades are presented. The trailing edges considered are vented and the internal heat transfer surfaces are extended by means of staggered arrays of pillars interconnecting the blade pressure and suction surfaces. A number of pillar arrays and trailing edge configurations are considered, namely pillar pitch to diameter ratios nominally of 2, 3, and 4 and trailing edge included angles of 0, 10, 15, and 20 deg. The range of Reynolds numbers covered based on pillar diameter and maximum velocity through a row of pillars is from 104 to 2 × 105.

Cited by 9

Eigenvalues in trailing edge flows

Capell K. · Queensland's institutional digital repository (The University of Queensland) · 1975

A wake similarity solution for symmetric uniform shear flows merging at the trailing edge of a flat plate has associated with it an eigenfunction problem which was overlooked by Hakkinen and O'Neil (1967). An asymptotic formula for large eigenvalues is obtained and compared with another such formula related to both the Goldstein (1930) inner wake solution and Tillett's (1968) similarity solution for a jet emerging from a two-dimensional channel.

Cited by 0

Improved Trailing Edge Noise Model

Franck Bertagnolio · 2012

The modeling of the surface pressure spectrum under a turbulent boundary layer is investigated in the presence of an adverse pressure gradient along the flow direction. It is shown that discrepancies between measurements and results from a well-known model increase as the pressure gradient increases. This model is modified by introducing anisotropy in the definition of the vertical velocity component spectrum across the boundary layer. The degree of anisotropy is directly related to the strength of the pressure gradient. It is shown that by appropriately normalizing the pressure gradient and by tuning the anisotropy factor, experimental results can be closely reproduced by the modified model. In this section, the original TNO-Blake model is modified in order to account for the effects of a pressure gradient through turbulence anisotropy. The model results are compared with measurements of the surface pressure fluctuations on an airfoil section.

Cited by 0