An Experimental Investigation of Ground Effect on a Quad Tilt Rotor in Hover and Low Speed Forward Flight

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dc.contributor.advisorSchmitz, Fredric Hen_US
dc.contributor.authorRadhakrishnan, Anand Men_US
dc.contributor.departmentAerospace Engineeringen_US
dc.contributor.publisherDigital Repository at the University of Marylanden_US
dc.contributor.publisherUniversity of Maryland (College Park, Md.)en_US
dc.date.accessioned2007-02-01T20:21:09Z
dc.date.available2007-02-01T20:21:09Z
dc.date.issued2006-11-06en_US
dc.description.abstractThe performance of a Quad Tilt Rotor (QTR) in helicopter mode was experimentally studied in ground effect (IGE) and out of ground effect (OGE). A 0.03 geometrically scaled fuselage/wing model of the QTR was tested in hover and very low speed forward flight. Fixed-pitch propellers were used to model the rotors. In order to avoid the boundary layer problems associated with wind tunnel testing of rotorcraft IGE, a unique moving setup was developed for testing in forward flight. The effect of ground proximity was tested by varying the height of the model above the ground. Download on the airframe; thrust, torque and rpm of the rotors, and pressures along the centerline of the bottom of the fuselage were measured. The downwash distributions of the rotors were measured and found to compare well with V-22 rotor measurements. Tuft flow visualization was used to identify the physical processes causing changes in the download and pressure measurements. An uncertainty analysis was performed on the measured quantities to determine the 95% confidence levels. A strong download (9% of the rotor thrust) was observed in hover, OGE. The download reduced substantially IGE and become an upload (9% of the rotor thrust), when the wheels of the QTR were on the ground. The upload IGE was found to be caused by the entrapment of the rotor wakes under the fuselage. The upload was observed to persist in forward flight IGE, but reduced slightly at certain low skew angles. The measured downloads, coupled with power measurements, indicate that for a given power, the available vehicle thrust greatly increases IGE. Therefore, the QTR displays a potential for significant increase in payload carrying capacity by operating IGE.en_US
dc.format.extent8280056 bytes
dc.format.mimetypeapplication/pdf
dc.identifier.urihttp://hdl.handle.net/1903/4094
dc.language.isoen_US
dc.subject.pqcontrolledEngineering, Aerospaceen_US
dc.subject.pquncontrolledQuad Tilt Rotoren_US
dc.subject.pquncontrolledGround Effecten_US
dc.subject.pquncontrolledAerodynamicsen_US
dc.subject.pquncontrolledQTRen_US
dc.subject.pquncontrolledTiltrotoren_US
dc.subject.pquncontrolledDownloaden_US
dc.titleAn Experimental Investigation of Ground Effect on a Quad Tilt Rotor in Hover and Low Speed Forward Flighten_US
dc.typeDissertationen_US

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