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Aerodynamics of a Gulfstream G550 Nose Landing Gear ModelIn this paper we discuss detailed steady and unsteady aerodynamic measurements of a Gulfstream G550 nose landing gear model. The quarter-scale, high-fidelity model includes part of the lower fuselage and the gear cavity. The full model configuration allowed for removal of various gear components (e.g. light cluster, steering mechanism, hydraulic lines, etc.) in order to document their effects on the local flow field. The measurements were conducted at a Reynolds number of 7.3 x 10(exp 4) based on the shock strut (piston) diameter and a freestream Mach number of 0.166. Additional data were also collected at lower Mach numbers of 0.12 and 0.145 and correspondingly lower Reynolds numbers. The boundary layer on the piston was tripped to enable turbulent flow separation, so as to better mimic the conditions encountered during flight. Steady surface pressures were gathered from an extensive number of static ports on the wheels, door, fuselage, and within the gear cavity. To better understand the resultant flow interactions between gear components, surface pressure fluctuations were collected via sixteen dynamic pressure sensors strategically placed on various subcomponents of the gear. Fifteen of the transducers were flush mounted on the gear surface at fixed locations, while the remaining one was a mobile transducer that could be placed at numerous varying locations. The measured surface pressure spectra are mainly broadband in nature, lacking any local peaks associated with coherent vortex shedding. This finding is in agreement with off-surface flow measurements using PIV that revealed the flow field to be a collection of separated shear layers without any dominant vortex shedding processes.
Document ID
20090020658
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Neuhart, Dan H. (NASA Langley Research Center Hampton, VA, United States)
Khorrami, Mehdi R. (NASA Langley Research Center Hampton, VA, United States)
Choudhari, Meelan M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 24, 2013
Publication Date
May 11, 2009
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
LF99-8007
Meeting Information
Meeting: 15th AIAA/CEAS Aeroacoustics Conference
Location: Miami, FL
Country: United States
Start Date: May 11, 2009
End Date: May 13, 2009
Sponsors: National Oceanic and Atmospheric Administraion, American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 561581.02.08.07.18.03.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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