Aerodynamic Measurements in a Wind Tunnel on Scale Models of a 777 Main Landing Gear

Simple item page
dc.contributor.authorRingshia, Aditya K.en
dc.contributor.committeechairNg, Wing Faien
dc.contributor.committeecochairBurdisso, Ricardo A.en
dc.contributor.committeememberDevenport, William J.en
dc.contributor.departmentMechanical Engineeringen
dc.date.accessioned2014-03-14T20:43:35Zen
dc.date.adate2006-11-20en
dc.date.available2014-03-14T20:43:35Zen
dc.date.issued2006-08-07en
dc.date.rdate2006-11-20en
dc.date.sdate2006-08-16en
dc.description.abstractAerodynamic measurements were taken over models of the Boeing 777 high fidelity isolated landing gear in the 6- by 6-foot Virginia Tech Stability Wind Tunnel (VT-SWT) at a free-stream Mach number of 0.16. Noise control devices (NCD) were developed at Virginia Tech [9] 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 conducted by Horne et al [7]. Hot-film measurements are also compared to Microphone Phased Array results which were acquired at Virginia Tech by Ravetta [8]. A novel technique for processing hot-film measurements by breaking turbulence into octave bands as acoustic measurements is presented. Particle Image Velocimetry (PIV) measurements were taken at six different locations over the 13% scale-model landing gear with no door and at a truck angle of zero degrees. Results are compared to PIV measurements taken over the wheels of a four-wheel landing gear by Lazos [10-12]. PIV results such as average velocity contours and vectors, streamlines and instantaneous velocity contours and vectors are presented. Results presented from PIV and flow visualization are in good agreement with results from Lazos [10-12].en
dc.description.degreeMaster of Scienceen
dc.identifier.otheretd-08162006-155652en
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-08162006-155652/en
dc.identifier.urihttp://hdl.handle.net/10919/34583en
dc.publisherVirginia Techen
dc.relation.haspartThesis_cover.pdfen
dc.relation.haspartThesis_part1.pdfen
dc.relation.haspartThesis_part2.pdfen
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subjectParticle Image Velocimetryen
dc.subjectPitot-static Measurementsen
dc.subjectLanding Gearen
dc.subjectHot Film Measurementsen
dc.subjectFlow Visualization using Tuftsen
dc.titleAerodynamic Measurements in a Wind Tunnel on Scale Models of a 777 Main Landing Gearen
dc.typeThesisen
thesis.degree.disciplineMechanical Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.levelmastersen
thesis.degree.nameMaster of Scienceen

Files

Original bundle
Now showing 1 - 3 of 3
Thumbnail Image
Name:
Thesis_cover.pdf
Size:
10.2 KB
Format:
Adobe Portable Document Format
Download
Thumbnail Image
Name:
Thesis_part1.pdf
Size:
58.18 KB
Format:
Adobe Portable Document Format
Download
Thumbnail Image
Name:
Thesis_part2.pdf
Size:
8.37 MB
Format:
Adobe Portable Document Format
Download

Collections

Masters Theses