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dc.contributor.advisorKish, Brian
dc.contributor.authorCasciola, Nicholas
dc.date.accessioned2019-03-20T16:05:08Z
dc.date.available2019-03-20T16:05:08Z
dc.date.created2018-12
dc.date.issued2018-12
dc.date.submittedDecember 2018
dc.identifier.urihttp://hdl.handle.net/11141/2749
dc.descriptionThesis (M.S.) - Florida Institute of Technology, 2018en_US
dc.description.abstractAerodynamic modeling is an important part of aircraft design and of aircraft testing. Generally, this is done through CFD models and Wind Tunnel tests prior to the aircrafts first flight but building the models using flight test data is also very important. It is used to verify theoretical models generated from the computer and wind tunnel tests. They are also useful for building simulators, particularly those in modeling and analyzing airport traffic patterns. These tests used a Piper Pa-28-161 Warrior II owned by the Florida Tech Flight Test Engineering program. It has a 160hp Lycoming engine. The test pilot was Dave Schwarz with Nicholas Casciola and Gary Greeman acting as Flight Test Engineers. The tests took place on April 27th, 2018 East of the Orlando-Melbourne International Airport (KMLB). The stability and control parameters were estimated using least squares, equation error, stepwise, and output-error regression methods. These parameters were not accurately estimated here due to several reasons. The first being the lack of a filter on several sets of input data. The next would be that no initial heading was recorded at the start of each maneuver; this means that yaw angle could not be found. The final piece to improve the models is to correct for the sensor locations in the aircraft. If the sensors are not over the cg of the aircraft, then corrections need to be made to adjust for the inertial effects of the moment arm caused by that distance.en_US
dc.format.mimetypeapplication/pdf
dc.language.isoen_USen_US
dc.rightsCC BY 4.0en_US
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/legalcodeen_US
dc.titleAerodynamic Model of the Piper Warrior II Based on Flight Test Dataen_US
dc.typeThesisen_US
dc.date.updated2019-02-06T16:08:38Z
thesis.degree.nameMasters of Science in Aerospace Engineeringen_US
thesis.degree.levelMastersen_US
thesis.degree.disciplineAerospace Engineeringen_US
thesis.degree.departmentAerospace, Physics and Space Sciencesen_US
thesis.degree.grantorFlorida Institute of Technologyen_US
dc.type.materialtext


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