Navier-Stokes Solution for a NACA 0012 Airfoil with Mass Flux (Fan)
STOL aircraft use a variety of mechanisms to augment lift. Small fans with vectored exhaust imbedded in an aircraft wing could increase lift and reduce drag. The aim of this thesis is to investigate the two-dimensional effect of a small 'fan in wing' on the flow field and on the lift and d...
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| description | STOL aircraft use a variety of mechanisms to augment lift. Small fans with vectored exhaust imbedded in an aircraft wing could increase lift and reduce drag. The aim of this thesis is to investigate the two-dimensional effect of a small 'fan in wing' on the flow field and on the lift and drag behavior of a NACA 0012 airfoil. Numerical solutions are obtained for a Mach number of 0.3 and a Reynolds number of one million. The parameters examined are angle of attack, fan ejection angle and suction velocity. The numerical code used is based on the Beam-Warming implicit factorization algorithm for solving the two- dimensional mass-averaged compressible Navier-Stokes equations for viscous, unsteady flows. Keywords: Drag reduction, Lift augmentation, Computational fluid dynamics, Mass transfer, Vectored blowing, Theses. |
| format | Report |
| fullrecord | <record><control><sourceid>dtic_1RU</sourceid><recordid>TN_cdi_dtic_stinet_ADA205771</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>ADA205771</sourcerecordid><originalsourceid>FETCH-dtic_stinet_ADA2057713</originalsourceid><addsrcrecordid>eNrjZHD2SyzLTC3SDS7Jz04tVgjOzyktyczPU0jLL1JIVPBzdHZUMDAwNFJwzCxKy8_MUSjPLMlQ8E0sLlZwyymtUNBwS8zT5GFgTUvMKU7lhdLcDDJuriHOHropJZnJ8cUlmXmpJfGOLo5GBqbm5obGBKQBUtYskw</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>report</recordtype></control><display><type>report</type><title>Navier-Stokes Solution for a NACA 0012 Airfoil with Mass Flux (Fan)</title><source>DTIC Technical Reports</source><creator>Boyles, Paul D</creator><creatorcontrib>Boyles, Paul D ; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING</creatorcontrib><description>STOL aircraft use a variety of mechanisms to augment lift. Small fans with vectored exhaust imbedded in an aircraft wing could increase lift and reduce drag. The aim of this thesis is to investigate the two-dimensional effect of a small 'fan in wing' on the flow field and on the lift and drag behavior of a NACA 0012 airfoil. Numerical solutions are obtained for a Mach number of 0.3 and a Reynolds number of one million. The parameters examined are angle of attack, fan ejection angle and suction velocity. The numerical code used is based on the Beam-Warming implicit factorization algorithm for solving the two- dimensional mass-averaged compressible Navier-Stokes equations for viscous, unsteady flows. Keywords: Drag reduction, Lift augmentation, Computational fluid dynamics, Mass transfer, Vectored blowing, Theses.</description><language>eng</language><subject>AERODYNAMIC DRAG ; AERODYNAMIC LIFT ; Aerodynamics ; AIRFOILS ; ALGORITHMS ; ANGLE OF ATTACK ; ANGLES ; AUGMENTATION ; BEAM WARMING ALGORITHM ; BLOWING ; BOUNDARY LAYER CONTROL ; CODING ; COMPRESSIBLE FLOW ; COMPUTATIONAL FLUID DYNAMICS ; COMPUTATIONS ; DRAG REDUCTION ; EJECTION ; EMBEDDING ; FACTOR ANALYSIS ; FAN IN WING ; FANS ; FLOW FIELDS ; FLUID DYNAMICS ; FLUX(RATE) ; LIFT AUGMENTATION ; MASS FLOW ; MASS TRANSFER ; NACA-0012 AIRFOIL ; NAVIER STOKES EQUATIONS ; NUMERICAL ANALYSIS ; REYNOLDS NUMBER ; SHORT TAKEOFF AIRCRAFT ; SOLUTIONS(GENERAL) ; SUBSONIC CHARACTERISTICS ; SUCTION ; THESES ; TWO DIMENSIONAL ; UNSTEADY FLOW ; V/STOL ; VELOCITY ; VERTICAL BLOWING ; VERTICAL ORIENTATION ; VISCOUS FLOW ; WINGS</subject><creationdate>1988</creationdate><rights>Approved for public release; distribution is unlimited.</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/ADA205771$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Boyles, Paul D</creatorcontrib><creatorcontrib>AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING</creatorcontrib><title>Navier-Stokes Solution for a NACA 0012 Airfoil with Mass Flux (Fan)</title><description>STOL aircraft use a variety of mechanisms to augment lift. Small fans with vectored exhaust imbedded in an aircraft wing could increase lift and reduce drag. The aim of this thesis is to investigate the two-dimensional effect of a small 'fan in wing' on the flow field and on the lift and drag behavior of a NACA 0012 airfoil. Numerical solutions are obtained for a Mach number of 0.3 and a Reynolds number of one million. The parameters examined are angle of attack, fan ejection angle and suction velocity. The numerical code used is based on the Beam-Warming implicit factorization algorithm for solving the two- dimensional mass-averaged compressible Navier-Stokes equations for viscous, unsteady flows. Keywords: Drag reduction, Lift augmentation, Computational fluid dynamics, Mass transfer, Vectored blowing, Theses.</description><subject>AERODYNAMIC DRAG</subject><subject>AERODYNAMIC LIFT</subject><subject>Aerodynamics</subject><subject>AIRFOILS</subject><subject>ALGORITHMS</subject><subject>ANGLE OF ATTACK</subject><subject>ANGLES</subject><subject>AUGMENTATION</subject><subject>BEAM WARMING ALGORITHM</subject><subject>BLOWING</subject><subject>BOUNDARY LAYER CONTROL</subject><subject>CODING</subject><subject>COMPRESSIBLE FLOW</subject><subject>COMPUTATIONAL FLUID DYNAMICS</subject><subject>COMPUTATIONS</subject><subject>DRAG REDUCTION</subject><subject>EJECTION</subject><subject>EMBEDDING</subject><subject>FACTOR ANALYSIS</subject><subject>FAN IN WING</subject><subject>FANS</subject><subject>FLOW FIELDS</subject><subject>FLUID DYNAMICS</subject><subject>FLUX(RATE)</subject><subject>LIFT AUGMENTATION</subject><subject>MASS FLOW</subject><subject>MASS TRANSFER</subject><subject>NACA-0012 AIRFOIL</subject><subject>NAVIER STOKES EQUATIONS</subject><subject>NUMERICAL ANALYSIS</subject><subject>REYNOLDS NUMBER</subject><subject>SHORT TAKEOFF AIRCRAFT</subject><subject>SOLUTIONS(GENERAL)</subject><subject>SUBSONIC CHARACTERISTICS</subject><subject>SUCTION</subject><subject>THESES</subject><subject>TWO DIMENSIONAL</subject><subject>UNSTEADY FLOW</subject><subject>V/STOL</subject><subject>VELOCITY</subject><subject>VERTICAL BLOWING</subject><subject>VERTICAL ORIENTATION</subject><subject>VISCOUS FLOW</subject><subject>WINGS</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1988</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNrjZHD2SyzLTC3SDS7Jz04tVgjOzyktyczPU0jLL1JIVPBzdHZUMDAwNFJwzCxKy8_MUSjPLMlQ8E0sLlZwyymtUNBwS8zT5GFgTUvMKU7lhdLcDDJuriHOHropJZnJ8cUlmXmpJfGOLo5GBqbm5obGBKQBUtYskw</recordid><startdate>198812</startdate><enddate>198812</enddate><creator>Boyles, Paul D</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>198812</creationdate><title>Navier-Stokes Solution for a NACA 0012 Airfoil with Mass Flux (Fan)</title><author>Boyles, Paul D</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_ADA2057713</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1988</creationdate><topic>AERODYNAMIC DRAG</topic><topic>AERODYNAMIC LIFT</topic><topic>Aerodynamics</topic><topic>AIRFOILS</topic><topic>ALGORITHMS</topic><topic>ANGLE OF ATTACK</topic><topic>ANGLES</topic><topic>AUGMENTATION</topic><topic>BEAM WARMING ALGORITHM</topic><topic>BLOWING</topic><topic>BOUNDARY LAYER CONTROL</topic><topic>CODING</topic><topic>COMPRESSIBLE FLOW</topic><topic>COMPUTATIONAL FLUID DYNAMICS</topic><topic>COMPUTATIONS</topic><topic>DRAG REDUCTION</topic><topic>EJECTION</topic><topic>EMBEDDING</topic><topic>FACTOR ANALYSIS</topic><topic>FAN IN WING</topic><topic>FANS</topic><topic>FLOW FIELDS</topic><topic>FLUID DYNAMICS</topic><topic>FLUX(RATE)</topic><topic>LIFT AUGMENTATION</topic><topic>MASS FLOW</topic><topic>MASS TRANSFER</topic><topic>NACA-0012 AIRFOIL</topic><topic>NAVIER STOKES EQUATIONS</topic><topic>NUMERICAL ANALYSIS</topic><topic>REYNOLDS NUMBER</topic><topic>SHORT TAKEOFF AIRCRAFT</topic><topic>SOLUTIONS(GENERAL)</topic><topic>SUBSONIC CHARACTERISTICS</topic><topic>SUCTION</topic><topic>THESES</topic><topic>TWO DIMENSIONAL</topic><topic>UNSTEADY FLOW</topic><topic>V/STOL</topic><topic>VELOCITY</topic><topic>VERTICAL BLOWING</topic><topic>VERTICAL ORIENTATION</topic><topic>VISCOUS FLOW</topic><topic>WINGS</topic><toplevel>online_resources</toplevel><creatorcontrib>Boyles, Paul D</creatorcontrib><creatorcontrib>AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING</creatorcontrib><collection>DTIC Technical Reports</collection><collection>DTIC STINET</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Boyles, Paul D</au><aucorp>AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING</aucorp><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>Navier-Stokes Solution for a NACA 0012 Airfoil with Mass Flux (Fan)</btitle><date>1988-12</date><risdate>1988</risdate><abstract>STOL aircraft use a variety of mechanisms to augment lift. Small fans with vectored exhaust imbedded in an aircraft wing could increase lift and reduce drag. The aim of this thesis is to investigate the two-dimensional effect of a small 'fan in wing' on the flow field and on the lift and drag behavior of a NACA 0012 airfoil. Numerical solutions are obtained for a Mach number of 0.3 and a Reynolds number of one million. The parameters examined are angle of attack, fan ejection angle and suction velocity. The numerical code used is based on the Beam-Warming implicit factorization algorithm for solving the two- dimensional mass-averaged compressible Navier-Stokes equations for viscous, unsteady flows. Keywords: Drag reduction, Lift augmentation, Computational fluid dynamics, Mass transfer, Vectored blowing, Theses.</abstract><oa>free_for_read</oa></addata></record> |
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| source | DTIC Technical Reports |
| subjects | AERODYNAMIC DRAG AERODYNAMIC LIFT Aerodynamics AIRFOILS ALGORITHMS ANGLE OF ATTACK ANGLES AUGMENTATION BEAM WARMING ALGORITHM BLOWING BOUNDARY LAYER CONTROL CODING COMPRESSIBLE FLOW COMPUTATIONAL FLUID DYNAMICS COMPUTATIONS DRAG REDUCTION EJECTION EMBEDDING FACTOR ANALYSIS FAN IN WING FANS FLOW FIELDS FLUID DYNAMICS FLUX(RATE) LIFT AUGMENTATION MASS FLOW MASS TRANSFER NACA-0012 AIRFOIL NAVIER STOKES EQUATIONS NUMERICAL ANALYSIS REYNOLDS NUMBER SHORT TAKEOFF AIRCRAFT SOLUTIONS(GENERAL) SUBSONIC CHARACTERISTICS SUCTION THESES TWO DIMENSIONAL UNSTEADY FLOW V/STOL VELOCITY VERTICAL BLOWING VERTICAL ORIENTATION VISCOUS FLOW WINGS |
| title | Navier-Stokes Solution for a NACA 0012 Airfoil with Mass Flux (Fan) |
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