Determination of Vortex Paths by Series Expansion Technique with Application to Cruciform Wings

A series method of determining two-dimensional vortex paths is considered and applied to the computation of vortex positions behind a slender equal-span cruciform wing at any angle of bank as a function of the distance behind the trailing edge. Calculated paths are shown for four bank angles. For a...

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Schlagworte:	Aircraft AQ M00-08-2314 CRUCIFORM WINGS EXPANSION Guided Missiles INCOMPRESSIBLE FLOW SERIES(MATHEMATICS) TAIL ASSEMBLIES TRAILING EDGES VORTICES
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creator	Alksne, Alberta Y
description	A series method of determining two-dimensional vortex paths is considered and applied to the computation of vortex positions behind a slender equal-span cruciform wing at any angle of bank as a function of the distance behind the trailing edge. Calculated paths are shown for four bank angles. For a bank angle of 45 deg comparison is made with the results of a closed expression given in NACA TN 2605. For other bank angles water-tank experiments provide qualitative comparison. Satisfactory agreement is found for a sufficient distance downstream to include most practical missile-tail positions. The interference forces on an equal-span interdigitated cruciform tail behind a slender equal-span cruciform wing are calculated for four angles of bank from the vortex positions found by use of the series.
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Calculated paths are shown for four bank angles. For a bank angle of 45 deg comparison is made with the results of a closed expression given in NACA TN 2605. For other bank angles water-tank experiments provide qualitative comparison. Satisfactory agreement is found for a sufficient distance downstream to include most practical missile-tail positions. The interference forces on an equal-span interdigitated cruciform tail behind a slender equal-span cruciform wing are calculated for four angles of bank from the vortex positions found by use of the series.</description><language>eng</language><subject>Aircraft ; AQ M00-08-2314 ; CRUCIFORM WINGS ; EXPANSION ; Guided Missiles ; INCOMPRESSIBLE FLOW ; SERIES(MATHEMATICS) ; TAIL ASSEMBLIES ; TRAILING EDGES ; VORTICES</subject><creationdate>1956</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/ADA377341$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Alksne, Alberta Y</creatorcontrib><creatorcontrib>NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CENTER</creatorcontrib><title>Determination of Vortex Paths by Series Expansion Technique with Application to Cruciform Wings</title><description>A series method of determining two-dimensional vortex paths is considered and applied to the computation of vortex positions behind a slender equal-span cruciform wing at any angle of bank as a function of the distance behind the trailing edge. Calculated paths are shown for four bank angles. For a bank angle of 45 deg comparison is made with the results of a closed expression given in NACA TN 2605. For other bank angles water-tank experiments provide qualitative comparison. Satisfactory agreement is found for a sufficient distance downstream to include most practical missile-tail positions. The interference forces on an equal-span interdigitated cruciform tail behind a slender equal-span cruciform wing are calculated for four angles of bank from the vortex positions found by use of the series.</description><subject>Aircraft</subject><subject>AQ M00-08-2314</subject><subject>CRUCIFORM WINGS</subject><subject>EXPANSION</subject><subject>Guided Missiles</subject><subject>INCOMPRESSIBLE FLOW</subject><subject>SERIES(MATHEMATICS)</subject><subject>TAIL ASSEMBLIES</subject><subject>TRAILING EDGES</subject><subject>VORTICES</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1956</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNqFi7EKwjAUALM4iPoHDu8HHCRC59BWHAWLjiHGF_OgTWLyivXvRXR3uuHu5kI3yJgHCoYpBogOzjEzTnA07AtcX3DCTFignZIJ5dN0aH2gx4jwJPagUurJfneOUOfRkot5gAuFe1mKmTN9wdWPC7Het1192NyYrC5MAVmrRsmqkrut_KPfGl86Cg</recordid><startdate>195604</startdate><enddate>195604</enddate><creator>Alksne, Alberta Y</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>195604</creationdate><title>Determination of Vortex Paths by Series Expansion Technique with Application to Cruciform Wings</title><author>Alksne, Alberta Y</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_ADA3773413</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1956</creationdate><topic>Aircraft</topic><topic>AQ M00-08-2314</topic><topic>CRUCIFORM WINGS</topic><topic>EXPANSION</topic><topic>Guided Missiles</topic><topic>INCOMPRESSIBLE FLOW</topic><topic>SERIES(MATHEMATICS)</topic><topic>TAIL ASSEMBLIES</topic><topic>TRAILING EDGES</topic><topic>VORTICES</topic><toplevel>online_resources</toplevel><creatorcontrib>Alksne, Alberta Y</creatorcontrib><creatorcontrib>NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH 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>Alksne, Alberta Y</au><aucorp>NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CENTER</aucorp><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>Determination of Vortex Paths by Series Expansion Technique with Application to Cruciform Wings</btitle><date>1956-04</date><risdate>1956</risdate><abstract>A series method of determining two-dimensional vortex paths is considered and applied to the computation of vortex positions behind a slender equal-span cruciform wing at any angle of bank as a function of the distance behind the trailing edge. Calculated paths are shown for four bank angles. For a bank angle of 45 deg comparison is made with the results of a closed expression given in NACA TN 2605. For other bank angles water-tank experiments provide qualitative comparison. Satisfactory agreement is found for a sufficient distance downstream to include most practical missile-tail positions. The interference forces on an equal-span interdigitated cruciform tail behind a slender equal-span cruciform wing are calculated for four angles of bank from the vortex positions found by use of the series.</abstract><oa>free_for_read</oa></addata></record>
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subjects	Aircraft AQ M00-08-2314 CRUCIFORM WINGS EXPANSION Guided Missiles INCOMPRESSIBLE FLOW SERIES(MATHEMATICS) TAIL ASSEMBLIES TRAILING EDGES VORTICES
title	Determination of Vortex Paths by Series Expansion Technique with Application to Cruciform Wings
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