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1. Identity statement
Reference TypeConference Paper (Conference Proceedings)
Sitemtc-m16b.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier6qtX3pFwXQZGivnK2Y/M6eCs
Repositorysid.inpe.br/mtc-m17@80/2006/08.08.14.31
Last Update2015:06.10.18.37.04 (UTC) marciana
Metadata Repositorysid.inpe.br/mtc-m17@80/2006/08.08.14.31.27
Metadata Last Update2018:06.05.03.43.59 (UTC) administrator
Secondary KeyINPE--PRE/
Citation KeySantos:2006:AnImAe
TitleAngle-of-attack impact on the aerothermodynamic performance of flat-nose power-law bodies in hypersonic airflow
Year2006
Access Date2024, Mar. 29
Secondary TypePRE CI
Number of Files1
Size512 KiB
2. Context
AuthorSantos, Wilson Fernando Nogueira dos
GroupLCP-INPE-MCT-BR
AffiliationInstituto Nacional de Pesquisas Espaciais, Laboratório Associado de Combustão e Propulsão (INPE.LCP)
Author e-Mail Addresswilson@lcp.inpe.br
Conference NameInternational Council of the Aeronautical Sciences.
Conference LocationHamburg, Germany
Date2006-09-03
Book TitleProceedings
Tertiary TypeOral Session
History (UTC)2006-08-08 14:31:27 :: simone -> administrator ::
2012-10-22 20:56:56 :: administrator -> simone ::
2013-02-20 15:19:50 :: simone -> administrator :: 2006
2015-05-21 16:34:40 :: administrator -> marciana :: 2006
2015-06-10 18:37:04 :: marciana -> administrator :: 2006
2018-06-05 03:43:59 :: administrator -> marciana :: 2006
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typepublisher
AbstractThis work describes a computational investigation on rarefied hypersonic flow past flat-nose power-law leading edges at incidence. Positive angle-of-attack effects on the aerodynamic surface quantities have been investigated by employing the Direct Simulation Monte Carlo (DSMC) Method. A method that properly accounts for the non-equilibrium aspects of the flow that arise near the leading-edge nose and that are especially important at high Mach numbers. The study is of great importance since it is impossible to achieve ideally sharp leading edges of airframes such as waverider vehicles. The results presented highlight the sensitivity of heat flux, drag and lift to changes not only on the angle of attack but also on the afterbody surface of the leading edges defined by power-law shapes. The analysis showed that positive angle of attack causes the expected asymmetry in the flow patterns as the stagnation point moves from the symmetry axis to the windward side of the leading edges.
AreaCOMB
Arrangementurlib.net > BDMCI > Fonds > Produção anterior à 2021 > LABCP > Angle-of-attack impact on...
doc Directory Contentaccess
source Directory Contentthere are no files
agreement Directory Contentthere are no files
4. Conditions of access and use
data URLhttp://urlib.net/ibi/6qtX3pFwXQZGivnK2Y/M6eCs
zipped data URLhttp://urlib.net/zip/6qtX3pFwXQZGivnK2Y/M6eCs
Languageen
Target Filesantos_angle.PDF
User Groupadministrator
marciana
simone
Reader Groupadministrator
marciana
Visibilityshown
Read Permissionallow from all
Update Permissionnot transferred
5. Allied materials
Next Higher Units8JMKD3MGPCW/3ET38CH
Host Collectionlcp.inpe.br/ignes/2004/02.12.18.39
cptec.inpe.br/walmeida/2003/04.25.17.12
6. Notes
Empty Fieldsarchivingpolicy archivist callnumber copyholder copyright creatorhistory descriptionlevel dissemination doi e-mailaddress edition editor format isbn issn keywords label lineage mark mirrorrepository nextedition notes numberofvolumes orcid organization pages parameterlist parentrepositories previousedition previouslowerunit progress project publisher publisheraddress resumeid rightsholder schedulinginformation secondarydate secondarymark serieseditor session shorttitle sponsor subject tertiarymark type url volume
7. Description control
e-Mail (login)marciana
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