Aerodynamic measurements of the landing gear

Aerodynamic measurements were taken over models of
the Boeing 777 high fidelity isolated landing gear at
a free-stream Mach number of 0.16. Noise control
devices (NCD) were developed at Virginia Tech to
reduce noise by shielding gear components, reducing
wake interactions and by streamlining the flow around
certain landing gear components. Aerodynamic
measurements were performed to understand the flow
over the landing gear and also changes in the flow
between Baseline and NCD configurations (without
and with Noise Control Devices respectively).
Hot-film, Pitot-static measurements and flow
visualization using tufts were performed over an
isolated 26% scale-model high fidelity landing gear
for the Baseline and NCD configurations. Contours
of turbulence intensity, normalized wake velocity and
normalized total pressure loss for both
configurations are compared. The Baseline
configuration was also compared with the NASA Ames
study. Hot-film measurements are also compared to
Microphone Phased Array results which were acquired
at Virginia Tech. A novel technique for processing
hot-film measurements by breaking turbulence into
octave bands as acoustic measurements is presented.

Autorentext

Aditya Ringshia was born in Mumbai, India and completed hisBachelors in Engineering from Mumbai University. He completed twoMasters in Engineering from Michigan Tech University and VirginiaTech. His areas of expertise during the two masters were inAutoimotive Transmissions, Aerodynamics, Aeroacoustics,Turbo-Propulsion and Data Acquisition.

Klappentext

Aerodynamic measurements were taken over models ofthe Boeing 777 high fidelity isolated landing gear ata free-stream Mach number of 0.16. Noise controldevices (NCD) were developed at Virginia Tech toreduce noise by shielding gear components, reducingwake interactions and by streamlining the flow aroundcertain landing gear components. Aerodynamicmeasurements were performed to understand the flowover the landing gear and also changes in the flowbetween 'Baseline' and 'NCD' configurations (withoutand with Noise Control Devices respectively).Hot-film, Pitot-static measurements and flowvisualization using tufts were performed over anisolated 26% scale-model high fidelity landing gearfor the 'Baseline' and 'NCD' configurations. Contoursof turbulence intensity, normalized wake velocity andnormalized total pressure loss for bothconfigurations are compared. The 'Baseline'configuration was also compared with the NASA Amesstudy. Hot-film measurements are also compared toMicrophone Phased Array results which were acquiredat Virginia Tech. A novel technique for processinghot-film measurements by breaking turbulence intooctave bands as acoustic measurements is presented.