ON SLENDER AIRFOIL THEORY FOR NON-EQUILIBRIUM FLOW

An exact theory for non-equilibrium flow past a thin airfoil is given. Green's function technique is used to solve the boundary value problem for the governing third order equation. Upon satisfying the boundary condition on the airfoil surface an integral equation is obtained which has an exact...

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1. Verfasser:	Ryhming,Inge L
Format:	Report
Sprache:	eng
Schlagworte:	AIRFOILS BOUNDARY LAYER GAS FLOW GREENS FUNCTIONS INTEGRAL EQUATIONS MATHEMATICAL ANALYSIS PARTIAL DIFFERENTIAL EQUATIONS SUPERSONIC FLOW
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description	An exact theory for non-equilibrium flow past a thin airfoil is given. Green's function technique is used to solve the boundary value problem for the governing third order equation. Upon satisfying the boundary condition on the airfoil surface an integral equation is obtained which has an exact solution. The final expression for the velocity potential shows that the solution is dependent not only on the slope of the airfoil but also on its curvature. As an ex-AMPLE, THE SUPERSONIC FLOW PAST A WEDGE IS CONSIDERED. (Author)
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Green's function technique is used to solve the boundary value problem for the governing third order equation. Upon satisfying the boundary condition on the airfoil surface an integral equation is obtained which has an exact solution. The final expression for the velocity potential shows that the solution is dependent not only on the slope of the airfoil but also on its curvature. As an ex-AMPLE, THE SUPERSONIC FLOW PAST A WEDGE IS CONSIDERED. (Author)</description><language>eng</language><subject>AIRFOILS ; BOUNDARY LAYER ; GAS FLOW ; GREENS FUNCTIONS ; INTEGRAL EQUATIONS ; MATHEMATICAL ANALYSIS ; PARTIAL DIFFERENTIAL EQUATIONS ; SUPERSONIC FLOW</subject><creationdate>1961</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>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>230,780,885,27567,27568</link.rule.ids><linktorsrc>$$Uhttps://apps.dtic.mil/sti/citations/AD0265130$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Ryhming,Inge L</creatorcontrib><creatorcontrib>GENERAL DYNAMICS/CONVAIR SAN DIEGO CALIF</creatorcontrib><title>ON SLENDER AIRFOIL THEORY FOR NON-EQUILIBRIUM FLOW</title><description>An exact theory for non-equilibrium flow past a thin airfoil is given. Green's function technique is used to solve the boundary value problem for the governing third order equation. Upon satisfying the boundary condition on the airfoil surface an integral equation is obtained which has an exact solution. The final expression for the velocity potential shows that the solution is dependent not only on the slope of the airfoil but also on its curvature. As an ex-AMPLE, THE SUPERSONIC FLOW PAST A WEDGE IS CONSIDERED. (Author)</description><subject>AIRFOILS</subject><subject>BOUNDARY LAYER</subject><subject>GAS FLOW</subject><subject>GREENS FUNCTIONS</subject><subject>INTEGRAL EQUATIONS</subject><subject>MATHEMATICAL ANALYSIS</subject><subject>PARTIAL DIFFERENTIAL EQUATIONS</subject><subject>SUPERSONIC FLOW</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1961</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNrjZDDy91MI9nH1c3ENUnD0DHLz9_RRCPFw9Q-KVHDzD1Lw8_fTdQ0M9fTxdAryDPVVcPPxD-dhYE1LzClO5YXS3Awybq4hzh66KSWZyfHFJZl5qSXxji4GRmamhsYGxgSkAfmxI98</recordid><startdate>196110</startdate><enddate>196110</enddate><creator>Ryhming,Inge L</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>196110</creationdate><title>ON SLENDER AIRFOIL THEORY FOR NON-EQUILIBRIUM FLOW</title><author>Ryhming,Inge L</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_AD02651303</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1961</creationdate><topic>AIRFOILS</topic><topic>BOUNDARY LAYER</topic><topic>GAS FLOW</topic><topic>GREENS FUNCTIONS</topic><topic>INTEGRAL EQUATIONS</topic><topic>MATHEMATICAL ANALYSIS</topic><topic>PARTIAL DIFFERENTIAL EQUATIONS</topic><topic>SUPERSONIC FLOW</topic><toplevel>online_resources</toplevel><creatorcontrib>Ryhming,Inge L</creatorcontrib><creatorcontrib>GENERAL DYNAMICS/CONVAIR SAN DIEGO CALIF</creatorcontrib><collection>DTIC Technical Reports</collection><collection>DTIC STINET</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Ryhming,Inge L</au><aucorp>GENERAL DYNAMICS/CONVAIR SAN DIEGO CALIF</aucorp><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>ON SLENDER AIRFOIL THEORY FOR NON-EQUILIBRIUM FLOW</btitle><date>1961-10</date><risdate>1961</risdate><abstract>An exact theory for non-equilibrium flow past a thin airfoil is given. 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subjects	AIRFOILS BOUNDARY LAYER GAS FLOW GREENS FUNCTIONS INTEGRAL EQUATIONS MATHEMATICAL ANALYSIS PARTIAL DIFFERENTIAL EQUATIONS SUPERSONIC FLOW
title	ON SLENDER AIRFOIL THEORY FOR NON-EQUILIBRIUM FLOW
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