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Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination

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dc.contributor.authorMugler, John P.en
dc.contributor.departmentAeronautical Engineeringen
dc.date.accessioned2017-03-10T18:28:45Zen
dc.date.available2017-03-10T18:28:45Zen
dc.date.issued1958en
dc.description.abstractAn investigation was conducted in the Langley 8-foot transonic tunnels to determine the aerodynamic loading characteristics of a thin conical cambered low-aspect-ratio delta wing in combination with a basic body and a body indented symmetrically for a Mach number of 1.2 in accordance with the supersonic area rule. The tests were conducted at Mach numbers from 0.60 to 1.12 and at 1.43 and at angles of attack generally from -4° to 20°. The wing vas conically cambered over the outboard 15 percent of each semispan. The wing had an aspect ratio of 2.31, 60° sweepback of the leading edge, and had NACA 65A003 airfoil sections parallel to the model plane of symmetry over the uncambered portion. The results of this investigation indicate that a leading-edge separation vortex forms at moderate angles of attack and causes the shape of the span load distribution to change markedly. Significant center of pressure movements are noted at transonic speeds. Indenting the body in accordance with the supersonic area rule had little effect on the aerodynamic loading characteristics. Comparisons with expert mental data for a similar plane wing indicates that the cambered wing is considerably more effective than the plane wing in utilizing the leading edge suction forces to produce thrust. A comparison between experimental and theoretical results indicates fair agreement around sonic speeds.en
dc.description.degreeMaster of Scienceen
dc.format.extent63 leavesen
dc.format.mimetypeapplication/pdfen
dc.identifier.urihttp://hdl.handle.net/10919/76118en
dc.language.isoen_USen
dc.publisherVirginia Polytechnic Instituteen
dc.relation.isformatofOCLC# 26432693en
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subject.lccLD5655.V855 1958.M834en
dc.subject.lcshTransonic planes -- Wingsen
dc.titleAnalysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combinationen
dc.typeThesisen
dc.type.dcmitypeTexten
thesis.degree.disciplineAeronautical Engineeringen
thesis.degree.grantorVirginia Polytechnic Instituteen
thesis.degree.levelmastersen
thesis.degree.nameMaster of Scienceen

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