Comparison of Transonic Flow Solutions in C-D Nozzles
The method of characteristics has proven to be a highly accurate and relatively straight forward technique for computing the supersonic flow field in a two-dimensional or axisymmetric nozzle. However, the method of characteristics requires an initial value line traversing the flow in the fully super...
Gespeichert in:
| Hauptverfasser: | , , |
|---|---|
| Format: | Report |
| Sprache: | eng |
| Schlagworte: | |
| Online-Zugang: | Volltext bestellen |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | |
|---|---|
| container_issue | |
| container_start_page | |
| container_title | |
| container_volume | |
| creator | Mary,Robert J , Jr Thompson,H Doyle Hoffman,Joe D |
| description | The method of characteristics has proven to be a highly accurate and relatively straight forward technique for computing the supersonic flow field in a two-dimensional or axisymmetric nozzle. However, the method of characteristics requires an initial value line traversing the flow in the fully supersonic region on which the flow properties are known. A parametric study of the effect of different transonic flow calculation methods for establishing the initial value line for axisymmetric converging-diverging nozzles was conducted. The Mach number and radial velocity distributions along a reference start line were calculated and compared for several different transonic solutions for a series of nozzles with different throat radii of curvature. These initial value lines were then used to initiate a method of characteristics analysis of several geometrically different axisymmetric nozzles in order to investigate the impact on calculated performance. |
| format | Report |
| fullrecord | <record><control><sourceid>dtic_1RU</sourceid><recordid>TN_cdi_dtic_stinet_ADA008003</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>ADA008003</sourcerecordid><originalsourceid>FETCH-dtic_stinet_ADA0080033</originalsourceid><addsrcrecordid>eNrjZDB1zs8tSCzKLM7PU8hPUwgpSswDMjOTFdxy8ssVgvNzSksy8_OKFTLzFJx1XRT88quqclKLeRhY0xJzilN5oTQ3g4yba4izh25KSWZyfHFJZl5qSbyji6OBgYWBgbExAWkAbbIplw</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>report</recordtype></control><display><type>report</type><title>Comparison of Transonic Flow Solutions in C-D Nozzles</title><source>DTIC Technical Reports</source><creator>Mary,Robert J , Jr ; Thompson,H Doyle ; Hoffman,Joe D</creator><creatorcontrib>Mary,Robert J , Jr ; Thompson,H Doyle ; Hoffman,Joe D ; PURDUE UNIV LAFAYETTE IND THERMAL SCIENCES AND PROPULSION CENTER</creatorcontrib><description>The method of characteristics has proven to be a highly accurate and relatively straight forward technique for computing the supersonic flow field in a two-dimensional or axisymmetric nozzle. However, the method of characteristics requires an initial value line traversing the flow in the fully supersonic region on which the flow properties are known. A parametric study of the effect of different transonic flow calculation methods for establishing the initial value line for axisymmetric converging-diverging nozzles was conducted. The Mach number and radial velocity distributions along a reference start line were calculated and compared for several different transonic solutions for a series of nozzles with different throat radii of curvature. These initial value lines were then used to initiate a method of characteristics analysis of several geometrically different axisymmetric nozzles in order to investigate the impact on calculated performance.</description><language>eng</language><subject>AXISYMMETRIC FLOW ; BOUNDARY VALUE PROBLEMS ; CONVERGENT DIVERGENT NOZZLES ; Fluid Mechanics ; METHOD OF CHARACTERISTICS ; NOZZLE AREA RATIO ; NOZZLE GAS FLOW ; Numerical Mathematics ; TRANSONIC FLOW ; TWO DIMENSIONAL FLOW</subject><creationdate>1974</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>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>230,780,885,27566,27567</link.rule.ids><linktorsrc>$$Uhttps://apps.dtic.mil/sti/citations/ADA008003$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Mary,Robert J , Jr</creatorcontrib><creatorcontrib>Thompson,H Doyle</creatorcontrib><creatorcontrib>Hoffman,Joe D</creatorcontrib><creatorcontrib>PURDUE UNIV LAFAYETTE IND THERMAL SCIENCES AND PROPULSION CENTER</creatorcontrib><title>Comparison of Transonic Flow Solutions in C-D Nozzles</title><description>The method of characteristics has proven to be a highly accurate and relatively straight forward technique for computing the supersonic flow field in a two-dimensional or axisymmetric nozzle. However, the method of characteristics requires an initial value line traversing the flow in the fully supersonic region on which the flow properties are known. A parametric study of the effect of different transonic flow calculation methods for establishing the initial value line for axisymmetric converging-diverging nozzles was conducted. The Mach number and radial velocity distributions along a reference start line were calculated and compared for several different transonic solutions for a series of nozzles with different throat radii of curvature. These initial value lines were then used to initiate a method of characteristics analysis of several geometrically different axisymmetric nozzles in order to investigate the impact on calculated performance.</description><subject>AXISYMMETRIC FLOW</subject><subject>BOUNDARY VALUE PROBLEMS</subject><subject>CONVERGENT DIVERGENT NOZZLES</subject><subject>Fluid Mechanics</subject><subject>METHOD OF CHARACTERISTICS</subject><subject>NOZZLE AREA RATIO</subject><subject>NOZZLE GAS FLOW</subject><subject>Numerical Mathematics</subject><subject>TRANSONIC FLOW</subject><subject>TWO DIMENSIONAL FLOW</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1974</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNrjZDB1zs8tSCzKLM7PU8hPUwgpSswDMjOTFdxy8ssVgvNzSksy8_OKFTLzFJx1XRT88quqclKLeRhY0xJzilN5oTQ3g4yba4izh25KSWZyfHFJZl5qSbyji6OBgYWBgbExAWkAbbIplw</recordid><startdate>197410</startdate><enddate>197410</enddate><creator>Mary,Robert J , Jr</creator><creator>Thompson,H Doyle</creator><creator>Hoffman,Joe D</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>197410</creationdate><title>Comparison of Transonic Flow Solutions in C-D Nozzles</title><author>Mary,Robert J , Jr ; Thompson,H Doyle ; Hoffman,Joe D</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_ADA0080033</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1974</creationdate><topic>AXISYMMETRIC FLOW</topic><topic>BOUNDARY VALUE PROBLEMS</topic><topic>CONVERGENT DIVERGENT NOZZLES</topic><topic>Fluid Mechanics</topic><topic>METHOD OF CHARACTERISTICS</topic><topic>NOZZLE AREA RATIO</topic><topic>NOZZLE GAS FLOW</topic><topic>Numerical Mathematics</topic><topic>TRANSONIC FLOW</topic><topic>TWO DIMENSIONAL FLOW</topic><toplevel>online_resources</toplevel><creatorcontrib>Mary,Robert J , Jr</creatorcontrib><creatorcontrib>Thompson,H Doyle</creatorcontrib><creatorcontrib>Hoffman,Joe D</creatorcontrib><creatorcontrib>PURDUE UNIV LAFAYETTE IND THERMAL SCIENCES AND PROPULSION CENTER</creatorcontrib><collection>DTIC Technical Reports</collection><collection>DTIC STINET</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Mary,Robert J , Jr</au><au>Thompson,H Doyle</au><au>Hoffman,Joe D</au><aucorp>PURDUE UNIV LAFAYETTE IND THERMAL SCIENCES AND PROPULSION CENTER</aucorp><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>Comparison of Transonic Flow Solutions in C-D Nozzles</btitle><date>1974-10</date><risdate>1974</risdate><abstract>The method of characteristics has proven to be a highly accurate and relatively straight forward technique for computing the supersonic flow field in a two-dimensional or axisymmetric nozzle. However, the method of characteristics requires an initial value line traversing the flow in the fully supersonic region on which the flow properties are known. A parametric study of the effect of different transonic flow calculation methods for establishing the initial value line for axisymmetric converging-diverging nozzles was conducted. The Mach number and radial velocity distributions along a reference start line were calculated and compared for several different transonic solutions for a series of nozzles with different throat radii of curvature. These initial value lines were then used to initiate a method of characteristics analysis of several geometrically different axisymmetric nozzles in order to investigate the impact on calculated performance.</abstract><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | eng |
| recordid | cdi_dtic_stinet_ADA008003 |
| source | DTIC Technical Reports |
| subjects | AXISYMMETRIC FLOW BOUNDARY VALUE PROBLEMS CONVERGENT DIVERGENT NOZZLES Fluid Mechanics METHOD OF CHARACTERISTICS NOZZLE AREA RATIO NOZZLE GAS FLOW Numerical Mathematics TRANSONIC FLOW TWO DIMENSIONAL FLOW |
| title | Comparison of Transonic Flow Solutions in C-D Nozzles |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-11T20%3A13%3A38IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-dtic_1RU&rft_val_fmt=info:ofi/fmt:kev:mtx:book&rft.genre=unknown&rft.btitle=Comparison%20of%20Transonic%20Flow%20Solutions%20in%20C-D%20Nozzles&rft.au=Mary,Robert%20J%20,%20Jr&rft.aucorp=PURDUE%20UNIV%20LAFAYETTE%20IND%20THERMAL%20SCIENCES%20AND%20PROPULSION%20CENTER&rft.date=1974-10&rft_id=info:doi/&rft_dat=%3Cdtic_1RU%3EADA008003%3C/dtic_1RU%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true |