VISCOUS-INVISCID ANALYSIS OF TRANSONIC AND LOW REYNOLDS-NUMBER AIRFOILS by Drela, M, Giles, M

Numerical study comparing RANS and LES approaches on a circulation control airfoil by Rumsey, C, Nishino, T

“…A numerical study over a nominally two-dimensional circulation control airfoil is performed using a largeeddy simulation code and two Reynolds-averaged Navier-Stokes codes. …”

Effect of Jet Nozzle Lip Momentum Loss on Circulation Control Airfoil Performance by Nishino, T, Shariff, K

“…Large eddy simulations of flow around a circulation control airfoil (using a Coanda jet blowing over its trailing surface) are performed to investigate the influence of jet nozzle lip thickness on airfoil performance. …”

Numerical study comparing RANS and LES approaches on a circulation control airfoil by Rumsey, C, Nishino, T

“…A numerical study over a nominally two-dimensional circulation control airfoil is performed using a large-eddy simulation code and two Reynolds-averaged Navier-Stokes codes. …”

Numerical study of wind-tunnel sidewall effects on circulation control airfoil flows by Nishino, T, Shariff, K

“…The airfoil model spans the entire tunnel and the span-to-chord ratio of the model is 3.26. …”

A navier-stokes analysis of airfoils in oscillating transonic cascades for the prediction of aerodynamic damping by Abhari, R, Giles, M

“…A numerical study on a generic transonic compressor rotor was performed in which the impact of varying the amplitude of the airfoil oscillation on the normalized predicted magnitude and phase of the unsteady pressure around the airfoil was studied. …”

Large-eddy simulations of a turbulent Coanda jet on a circulation control airfoil by Nishino, T, Hahn, S, Shariff, K

“…Large-eddy simulations are performed of a turbulent Coanda jet separating from a rounded trailing edge of a simplified circulation control airfoil model. The freestream Reynolds number based on the airfoil chord is 0.49 × 106, the jet Reynolds number based on the jet slot height is 4470, and the ratio of the peak jet velocity to the freestream velocity is 3.96. …”

Numerical study of airfoil stall cells using a very wide computational domain by Manni, L, Nishino, T, Delafin, P

“…The formation of stall cells over a NACA 0012 airfoil at a Reynolds number of one million has been investigated numerically, using unsteady Reynolds-averaged Navier–Stokes (URANS) and delayed detached-eddy simulation (DDES) approaches. …”

Calculation of the turbulence characteristics of flow around a circulation control airfoil using les (invited paper) by Nishino, T, Hahn, S, Shariff, K

“…Large-eddy simulations of high-Reynolds-number flow around a non-cambered, ellipticleading- edge circulation control airfoil (using a Coanda wall jet blowing over a rounded trailing edge) are performed to investigate detailed turbulence characteristics of the flow. …”

Parameterising the impact of roughness evolution on wind turbine performance by Kelly, J, Willden, R, Vogel, C

“…This study examined 51 sets of experimental data across 16 airfoils to identify trends in roughened airfoil performance. …”

Verification and validation of OpenFOAM for high-lift aircraft flows by Ashton, N, Skaperdas, V

“…A range of cases are investigated, including a zero-pressure gradient flat plate, a NACA0012 airfoil at varying angles of attack, a DSMA661 airfoil, a NASA High-Lift Common Research Model, and a Japan Aerospace Exploration Agency (JAXA) standard model (JSM) high-lift aircraft model. …”

On two-dimensional sonic-subsonic flow by Chen, G, Dafermos, C, Slemrod, M, Wang, D

“…It follows that the set of subsonic irrotational solutions to the Euler equations is compact; thus flows with sonic points over an obstacle, such as an airfoil, may be realized as limits of sequences of strictly subsonic flows. …”

Aeroelastic modelling of long-span suspension bridges by Graham, J, Limebeer, D, Zhao, X

“…The 2D aerodynamic modelling of long-span suspension bridges is considered. We use thin airfoil theory from the aircraft industry and a sectional bridge model with an integrated controllable trailing-edge flap. …”

Adjoint and defect error bounding and correction for functional estimates by Pierce, N, Giles, M

“…Superconvergent drag estimates are obtained for subsonic Euler flow over a lifting airfoil. © 2004 Elsevier Inc. All rights reserved.…”

Radical guide vane design and optimization by Rife, M, Barbarossa, F, Di Mare, L, Parry, A, Green, J

“…Design targets are achieved by manipulating both airfoil geometry and position within the cascade. …”

Impact and mitigation of blade surface roughness effects on wind turbine performance by Kelly, J, Vogel, C, Willden, R

“…The aerodynamic lift and drag data for the clean and roughened airfoils are taken from previous experimental work. …”

Tuning turbine rotor design for very large wind farms by Nishino, T, Hunter, W

“…The example solutions, obtained using a simplified but still realistic NREL S809 airfoil performance curve, illustrate how the aerodynamically optimal rotor design may change depending on the farm density. …”

The effects of combustor cooling features on nozzle guide vane film cooling experiments by Holgate, N, Ireland, P, Romero, E

“…It is found that dilution port injection can create significant effectiveness benefits at the difficult-to-cool vane stagnation region due to the more turbulent hot mainstream enhancing the mixing of film coolant jets that have left the airfoil surface.</p> <br/> <p>Also explored are the implications of endwall film cooling for infrared vane surface temperature measurements. …”

Blade tip heat transfer and aerodynamics in a large scale turbine cascade with moving endwall by Palafox, P, Oldfield, M, Ireland, P, Jones, T, LaGraff, J, ASME

“…Analysis of pressure measurements on the blade airfoil surface and tip surface along with PIV velocity flow fields in the gap give an understanding of the heat transfer mechanism. …”

EBFOG: deposition, erosion, and detachment on high-pressure turbine vanes by Casari, N, Pinelli, M, Suman, A, di Mare, L, Montomoli, F

“…The model is demonstrated on a HPT vane. The airfoil shape evolution over the exposure time as a consequence of the impinging particles has been carefully monitored. …”