PRESSURE RECOVERY MEASUREMENTS ACROSS A TWO-DIMENSIONAL HYPERSONIC INLET WITH VARIABLE GEOMETRY
The report describes the experimental measurement of pressure recovery across a simulated combustion chamber duct of a two-dimensional hypersonic inlet with variable geometry. The model tested was a wedge type inlet which generated a single external shock wave. The program was conducted in the twent...
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| creator | Tabakoff,Widen McDonel,James D |
| description | The report describes the experimental measurement of pressure recovery across a simulated combustion chamber duct of a two-dimensional hypersonic inlet with variable geometry. The model tested was a wedge type inlet which generated a single external shock wave. The program was conducted in the twenty-inch hypersonic wind tunnel. Testing was at a nominal free stream Mach number of 14 and free stream Reynolds number of 721,000 per foot. (Author) |
| format | Report |
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The model tested was a wedge type inlet which generated a single external shock wave. The program was conducted in the twenty-inch hypersonic wind tunnel. Testing was at a nominal free stream Mach number of 14 and free stream Reynolds number of 721,000 per foot. (Author)</description><language>eng</language><subject>AERODYNAMIC CONFIGURATIONS ; COMBUSTION CHAMBERS ; GEOMETRY ; HYPERSONIC CHARACTERISTICS ; HYPERSONIC DIFFUSERS ; HYPERSONIC WIND TUNNELS ; MEASUREMENT ; PRESSURE ; RAMJET ENGINES ; RAMJET INLETS ; SIMULATION ; TRANSDUCERS ; TWO DIMENSIONAL FLOW</subject><creationdate>1965</creationdate><rights>APPROVED FOR PUBLIC RELEASE</rights><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>230,776,881,27544,27545</link.rule.ids><linktorsrc>$$Uhttps://apps.dtic.mil/sti/citations/AD0617620$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Tabakoff,Widen</creatorcontrib><creatorcontrib>McDonel,James D</creatorcontrib><creatorcontrib>CINCINNATI UNIV OHIO</creatorcontrib><title>PRESSURE RECOVERY MEASUREMENTS ACROSS A TWO-DIMENSIONAL HYPERSONIC INLET WITH VARIABLE GEOMETRY</title><description>The report describes the experimental measurement of pressure recovery across a simulated combustion chamber duct of a two-dimensional hypersonic inlet with variable geometry. The model tested was a wedge type inlet which generated a single external shock wave. The program was conducted in the twenty-inch hypersonic wind tunnel. Testing was at a nominal free stream Mach number of 14 and free stream Reynolds number of 721,000 per foot. (Author)</description><subject>AERODYNAMIC CONFIGURATIONS</subject><subject>COMBUSTION CHAMBERS</subject><subject>GEOMETRY</subject><subject>HYPERSONIC CHARACTERISTICS</subject><subject>HYPERSONIC DIFFUSERS</subject><subject>HYPERSONIC WIND TUNNELS</subject><subject>MEASUREMENT</subject><subject>PRESSURE</subject><subject>RAMJET ENGINES</subject><subject>RAMJET INLETS</subject><subject>SIMULATION</subject><subject>TRANSDUCERS</subject><subject>TWO DIMENSIONAL FLOW</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1965</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNqFyb0KwjAUQOEuDqK-gcN9gUJVqHNMryaQn3JvbMkURCsUxKV5f6zg7nTgO8sitYTMV0IglL5DimBRfMGiCwxCkuc5EHpfNnpG1t4JAyq2SOydlqCdwQC9Dgo6QVqcDMIFvcVAcV0snrfXNGx-XRXbMwapykce72nK43vISTRVvTvW--rwZ38Aswcw4Q</recordid><startdate>196505</startdate><enddate>196505</enddate><creator>Tabakoff,Widen</creator><creator>McDonel,James D</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>196505</creationdate><title>PRESSURE RECOVERY MEASUREMENTS ACROSS A TWO-DIMENSIONAL HYPERSONIC INLET WITH VARIABLE GEOMETRY</title><author>Tabakoff,Widen ; McDonel,James D</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_AD06176203</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1965</creationdate><topic>AERODYNAMIC CONFIGURATIONS</topic><topic>COMBUSTION CHAMBERS</topic><topic>GEOMETRY</topic><topic>HYPERSONIC CHARACTERISTICS</topic><topic>HYPERSONIC DIFFUSERS</topic><topic>HYPERSONIC WIND TUNNELS</topic><topic>MEASUREMENT</topic><topic>PRESSURE</topic><topic>RAMJET ENGINES</topic><topic>RAMJET INLETS</topic><topic>SIMULATION</topic><topic>TRANSDUCERS</topic><topic>TWO DIMENSIONAL FLOW</topic><toplevel>online_resources</toplevel><creatorcontrib>Tabakoff,Widen</creatorcontrib><creatorcontrib>McDonel,James D</creatorcontrib><creatorcontrib>CINCINNATI UNIV OHIO</creatorcontrib><collection>DTIC Technical Reports</collection><collection>DTIC STINET</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Tabakoff,Widen</au><au>McDonel,James D</au><aucorp>CINCINNATI UNIV OHIO</aucorp><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>PRESSURE RECOVERY MEASUREMENTS ACROSS A TWO-DIMENSIONAL HYPERSONIC INLET WITH VARIABLE GEOMETRY</btitle><date>1965-05</date><risdate>1965</risdate><abstract>The report describes the experimental measurement of pressure recovery across a simulated combustion chamber duct of a two-dimensional hypersonic inlet with variable geometry. The model tested was a wedge type inlet which generated a single external shock wave. The program was conducted in the twenty-inch hypersonic wind tunnel. Testing was at a nominal free stream Mach number of 14 and free stream Reynolds number of 721,000 per foot. (Author)</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng |
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| source | DTIC Technical Reports |
| subjects | AERODYNAMIC CONFIGURATIONS COMBUSTION CHAMBERS GEOMETRY HYPERSONIC CHARACTERISTICS HYPERSONIC DIFFUSERS HYPERSONIC WIND TUNNELS MEASUREMENT PRESSURE RAMJET ENGINES RAMJET INLETS SIMULATION TRANSDUCERS TWO DIMENSIONAL FLOW |
| title | PRESSURE RECOVERY MEASUREMENTS ACROSS A TWO-DIMENSIONAL HYPERSONIC INLET WITH VARIABLE GEOMETRY |
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