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dc.contributor.authorDierksmeier, Douglas Daviden_US
dc.date.accessioned2017-03-09T21:35:13Z
dc.date.available2017-03-09T21:35:13Z
dc.date.issued1983en_US
dc.identifier.urihttp://hdl.handle.net/10919/76011
dc.description.abstractThe object of this thesis is to determine the directional stability of a tricycle-geared aircraft during the landing roll. The motion of the aircraft is simulated by a computer program based on the appropriate equations of motion. Empirical aircraft and tire data are utilized in order to improve the simulation process. The stability of the aircraft is obtained by analyzing the motion of the vehicle after an initial disturbance about the vertical axis of the aircraft. The influence of the aircraft's velocity and other parameters on the stability is then determined. For the single-engine Cessna, the results show that a steady-state yaw angle is obtained after an initial disturbance. The results are presented graphically to show the effect of various parameters on the aircraft's stability.en
dc.format.extentxv, 69 leavesen_US
dc.format.mimetypeapplication/pdfen_US
dc.language.isoen_USen_US
dc.publisherVirginia Polytechnic Institute and State Universityen_US
dc.relation.isformatofOCLC# 9995454
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subject.lccLD5655.V855 1983.D537en_US
dc.subject.lcshAirplanes -- Landing -- Simulation methodsen_US
dc.subject.lcshStability of airplanes -- Simulation methodsen_US
dc.titleThe stability of an aircraft during the landing rollen_US
dc.typeThesisen_US
dc.contributor.departmentMechanical Engineeringen_US
dc.description.degreeMaster of Scienceen_US
thesis.degree.nameMaster of Scienceen_US
thesis.degree.levelmastersen_US
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen_US
thesis.degree.disciplineMechanical Engineeringen_US
dc.type.dcmitypeTexten_US


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