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dc.contributor.advisorNewberry, Conrad F.
dc.contributor.advisorBowles, Jeffrey V.
dc.contributor.authorCedrun, Mark E.
dc.dateJune, 1994
dc.date.accessioned2013-04-26T18:58:56Z
dc.date.available2013-04-26T18:58:56Z
dc.date.issued1994-06
dc.identifier.urihttp://hdl.handle.net/10945/30832
dc.description.abstractLow-speed wind tunnel tests were conducted to determine the subsonic aerodynamic characteristics of an optimized supersonic (Mach 6) conical-flow waverider designed for a deck-launched intercept mission. These tests are part of the continuing waverider research being conducted by the Naval Postgraduate School and the NASA Ames Research Center. The tests consisted of performing Alpha and Beta sweeps, at different dynamic pressures, with a 15 inch aluminum waverider model in the NPS low-speed wind tunnel. Force and moment data were then collected using a six-degree-of-freedom sting balance. Coefficients of lift, drag and pitch were calculated from the data and compared to theory and existing waverider subsonic aerodynamic performance data. Flow visualization using tufts was also done. The results of the experiments show that waverider exhibits high lift characteristics at positive angles of attack. The design also compares favorably with both subsonic thin airfoil theory and the results of the delta wing and subsonic waverider analysis done by Vanhoy. However, flow visualization showed that vortex bursting occurred at a dynamic pressure of 12. llbf at +/-15 degrees angle of attack. Based upon the data collected in this analysis, the development of an actual waverider aircraft using the NPS/NASA ames waverider design as a baseline is a plausible endeavor.en_US
dc.description.urihttp://archive.org/details/lowspeedwindtunn1094530832
dc.format.extent96 p.;28 cm.en_US
dc.language.isoen_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. As such, it is in the public domain, and under the provisions of Title 17, United States Code, Section 105, may not be copyrighted.en_US
dc.titleLow-speed wind tunnel testing of the NPS/NASA Ames Mach 6 optimized waverideren_US
dc.typeThesisen_US
dc.contributor.secondreaderNA
dc.contributor.corporateNA
dc.contributor.departmentAeronautical Engineering
dc.subject.authorNAen_US
dc.description.funderNAen_US
dc.description.recognitionNAen_US
dc.description.serviceU.S. Navy (U.S.N.) author.en_US
etd.thesisdegree.nameM.S. in Aeronautical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAeronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US


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