{"id":{"repo_id":"nps","oai_identifier":"oai:calhoun.nps.edu:10945/1639"},"canonical_url":"https://search.dev.ndltd.org/etd/nps/oai:calhoun.nps.edu:10945/1639","repository":{"repo_id":"nps","name":"Naval Postgraduate School","base_url":"https://calhoun.nps.edu/server/oai/request"},"display":{"title":"Supersonic flow field visualization studies of the MŠ= 6 price waverider planform","abstract":"Supersonic tests of the conical flow derived MŠʻ = 6 (design) Price waverider planform were conducted using the Naval Postgraduate School wind tunnel. These tests are part of a continuing effort to study the characteristics of waverider configured vehicles. Two sting-mounted, flat-plate stainless-steel Price waverider planform models were utilized for testing in the NPS 4-inch by 4-inch cross section supersonic blowdown wind tunnel. Tests at Mach numbers of MŠʻ = 1.7, 2.8 and 4 were attempted but flowfield studies were only completed at MŠʻ = 4. Sting mount flow blockage (choked flow) prevented test section starting at freestream test Mach numbers of MŠʻ = 1.7 and 2.8. Horizontal (side-view) and vertical (top-view) mounted shadowgraph pictures and pressure sensitive paint images were taken at pitch angles of ⠭¿ = 0Šʺ, 2Šʺ and 4Šʺ. The Mach 4 shadowgraph and pressure sensitive paint results correlate well with previous CFD results using the three-dimensional Price waverider model. The choked flow tests at MŠʻ = 1.7 and 2.8 are discussed in detail; suggestions are given for future work in this Mach number test spectrum.","abstract_html":"Supersonic tests of the conical flow derived MŠʻ = 6 (design) Price waverider planform were conducted using the Naval Postgraduate School wind tunnel. These tests are part of a continuing effort to study the characteristics of waverider configured vehicles. Two sting-mounted, flat-plate stainless-steel Price waverider planform models were utilized for testing in the NPS 4-inch by 4-inch cross section supersonic blowdown wind tunnel. Tests at Mach numbers of MŠʻ = 1.7, 2.8 and 4 were attempted but flowfield studies were only completed at MŠʻ = 4. Sting mount flow blockage (choked flow) prevented test section starting at freestream test Mach numbers of MŠʻ = 1.7 and 2.8. Horizontal (side-view) and vertical (top-view) mounted shadowgraph pictures and pressure sensitive paint images were taken at pitch angles of ⠭¿ = 0Šʺ, 2Šʺ and 4Šʺ. The Mach 4 shadowgraph and pressure sensitive paint results correlate well with previous CFD results using the three-dimensional Price waverider model. The choked flow tests at MŠʻ = 1.7 and 2.8 are discussed in detail; suggestions are given for future work in this Mach number test spectrum.","abstract_has_math":false,"creators":["Garcia, Karl"],"institution":"Monterey, California. Naval Postgraduate School","degree_name":null,"degree_level":null,"degree_discipline":null,"degree_department":"Aeronautical Engineering","school":null,"contributors":[],"advisors":["Newberry, Conrad F."],"committee_chairs":[],"committee_members":[],"year":2001,"date_issued":"2001-09","date_published":"2001-09","updated_at":"2026-07-27T20:25:42Z","subjects":[],"languages":[],"rights":["This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States."],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://hdl.handle.net/10945/1639","outbound_label":"Handle","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor.advisor","label":"Advisor","values":["Newberry, Conrad F."]},{"key":"dc:contributor.department","label":"Department","values":["Aeronautical Engineering"]},{"key":"dc:creator","label":"Author","values":["Garcia, Karl"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date.accessioned","label":"Dc Date Accessioned","values":["2012-03-14T17:32:33Z"]},{"key":"dc:date.available","label":"Dc Date Available","values":["2012-03-14T17:32:33Z"]},{"key":"dc:date.issued","label":"Date","values":["2001-09"]},{"key":"dc:publisher","label":"Institution","values":["Monterey, California. Naval Postgraduate School"]},{"key":"dc:type","label":"Dc Type","values":["Thesis"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:rights","label":"Dc Rights","values":["This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States."]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier.uri","label":"Identifier URI","values":["https://hdl.handle.net/10945/1639"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["Supersonic tests of the conical flow derived MŠʻ = 6 (design) Price waverider planform were conducted using the Naval Postgraduate School wind tunnel. These tests are part of a continuing effort to study the characteristics of waverider configured vehicles. Two sting-mounted, flat-plate stainless-steel Price waverider planform models were utilized for testing in the NPS 4-inch by 4-inch cross section supersonic blowdown wind tunnel. Tests at Mach numbers of MŠʻ = 1.7, 2.8 and 4 were attempted but flowfield studies were only completed at MŠʻ = 4. Sting mount flow blockage (choked flow) prevented test section starting at freestream test Mach numbers of MŠʻ = 1.7 and 2.8. Horizontal (side-view) and vertical (top-view) mounted shadowgraph pictures and pressure sensitive paint images were taken at pitch angles of ⠭¿ = 0Šʺ, 2Šʺ and 4Šʺ. The Mach 4 shadowgraph and pressure sensitive paint results correlate well with previous CFD results using the three-dimensional Price waverider model. The choked flow tests at MŠʻ = 1.7 and 2.8 are discussed in detail; suggestions are given for future work in this Mach number test spectrum."]},{"key":"dc:title","label":"Title","values":["Supersonic flow field visualization studies of the MŠ= 6 price waverider planform"]}]}],"canonical_facts":{"dc:contributor.advisor":["Newberry, Conrad F."],"dc:contributor.department":["Aeronautical Engineering"],"dc:creator":["Garcia, Karl"],"dc:date.accessioned":["2012-03-14T17:32:33Z"],"dc:date.available":["2012-03-14T17:32:33Z"],"dc:date.issued":["2001-09"],"dc:description.abstract":["Supersonic tests of the conical flow derived MŠʻ = 6 (design) Price waverider planform were conducted using the Naval Postgraduate School wind tunnel. These tests are part of a continuing effort to study the characteristics of waverider configured vehicles. Two sting-mounted, flat-plate stainless-steel Price waverider planform models were utilized for testing in the NPS 4-inch by 4-inch cross section supersonic blowdown wind tunnel. Tests at Mach numbers of MŠʻ = 1.7, 2.8 and 4 were attempted but flowfield studies were only completed at MŠʻ = 4. Sting mount flow blockage (choked flow) prevented test section starting at freestream test Mach numbers of MŠʻ = 1.7 and 2.8. Horizontal (side-view) and vertical (top-view) mounted shadowgraph pictures and pressure sensitive paint images were taken at pitch angles of ⠭¿ = 0Šʺ, 2Šʺ and 4Šʺ. The Mach 4 shadowgraph and pressure sensitive paint results correlate well with previous CFD results using the three-dimensional Price waverider model. The choked flow tests at MŠʻ = 1.7 and 2.8 are discussed in detail; suggestions are given for future work in this Mach number test spectrum."],"dc:identifier.uri":["https://hdl.handle.net/10945/1639"],"dc:publisher":["Monterey, California. Naval Postgraduate School"],"dc:rights":["This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States."],"dc:title":["Supersonic flow field visualization studies of the MŠ= 6 price waverider planform"],"dc:type":["Thesis"]},"updated_at":"2026-07-27T20:25:42Z"}