Sting Interference Effects on the SDM Aircraft as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0.3 through 1.3
An investigation was conducted to determine the effects of sting-support interference on the measurement of pitch damping, yaw-damping, pitching-moment slope, yawing-moment slope, pitching moment, and base pressure. The model was the Standard Dynamics Model (SDM). The forced oscillation technique wa...
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| creator | Cyran,F B Chaney,M J |
| description | An investigation was conducted to determine the effects of sting-support interference on the measurement of pitch damping, yaw-damping, pitching-moment slope, yawing-moment slope, pitching moment, and base pressure. The model was the Standard Dynamics Model (SDM). The forced oscillation technique was used to obtain data at Mach numbers 0.3 to 1.3 and Reynolds numbers, based on the model mean aerodynamic chord (MAC), of 0.3 million to 3.1 million. Amplitudes of oscillation were 1.0, 1.5, and 2.0 deg, and the reduced frequency parameter ranged from 0.009 to 0.032 radians.
Prepared in cooperation with ARO, Inc., Tullahoma, TN. |
| format | Report |
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Prepared in cooperation with ARO, Inc., Tullahoma, TN.</description><language>eng</language><subject>Aerodynamic chord ; AERODYNAMIC STABILITY ; Aerodynamics ; ANGLE OF ATTACK ; BASE PRESSURE ; DAMPING ; INTERFERENCE ; JET FIGHTERS ; LPN-ARO-P41C-H7 ; MACH NUMBER ; MEASUREMENT ; PE65807F ; PITCH(MOTION) ; SCALE MODELS ; SDM(Standard Dynamic Model) ; STATIC STABILITY ; STING MOUNTS ; Test Facilities, Equipment and Methods ; TEST METHODS ; WIND TUNNEL MODELS ; WING BODY CONFIGURATIONS ; YAW</subject><creationdate>1980</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/ADA110324$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Cyran,F B</creatorcontrib><creatorcontrib>Chaney,M J</creatorcontrib><creatorcontrib>ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN</creatorcontrib><title>Sting Interference Effects on the SDM Aircraft as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0.3 through 1.3</title><description>An investigation was conducted to determine the effects of sting-support interference on the measurement of pitch damping, yaw-damping, pitching-moment slope, yawing-moment slope, pitching moment, and base pressure. The model was the Standard Dynamics Model (SDM). The forced oscillation technique was used to obtain data at Mach numbers 0.3 to 1.3 and Reynolds numbers, based on the model mean aerodynamic chord (MAC), of 0.3 million to 3.1 million. Amplitudes of oscillation were 1.0, 1.5, and 2.0 deg, and the reduced frequency parameter ranged from 0.009 to 0.032 radians.
Prepared in cooperation with ARO, Inc., Tullahoma, TN.</description><subject>Aerodynamic chord</subject><subject>AERODYNAMIC STABILITY</subject><subject>Aerodynamics</subject><subject>ANGLE OF ATTACK</subject><subject>BASE PRESSURE</subject><subject>DAMPING</subject><subject>INTERFERENCE</subject><subject>JET FIGHTERS</subject><subject>LPN-ARO-P41C-H7</subject><subject>MACH NUMBER</subject><subject>MEASUREMENT</subject><subject>PE65807F</subject><subject>PITCH(MOTION)</subject><subject>SCALE MODELS</subject><subject>SDM(Standard Dynamic Model)</subject><subject>STATIC STABILITY</subject><subject>STING MOUNTS</subject><subject>Test Facilities, Equipment and Methods</subject><subject>TEST METHODS</subject><subject>WIND TUNNEL MODELS</subject><subject>WING BODY CONFIGURATIONS</subject><subject>YAW</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1980</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNqFjjFqw1AQRNW4CHZukGIuEGNFuYAc2diFQkDpzeprv7VgfcHuyqDb5KiRIX2qKeY9Zp6yn8YlXXFOzhpZOQXGIUYObhgTvGc0VY1SNChFBxkqXthBEndoZ9RMNikPnB5GRDUnGiSgcWrlJj4vvMqdXO5soNRhT8b4UraHhzgqago9PqehZTXstsUyq-N07ZFvi022inQzfv7LdfZyPHx_nF47l3Cx5T37pazKPN8Vb-_FP_UvfaVPiw</recordid><startdate>198010</startdate><enddate>198010</enddate><creator>Cyran,F B</creator><creator>Chaney,M J</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>198010</creationdate><title>Sting Interference Effects on the SDM Aircraft as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0.3 through 1.3</title><author>Cyran,F B ; Chaney,M J</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_ADA1103243</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1980</creationdate><topic>Aerodynamic chord</topic><topic>AERODYNAMIC STABILITY</topic><topic>Aerodynamics</topic><topic>ANGLE OF ATTACK</topic><topic>BASE PRESSURE</topic><topic>DAMPING</topic><topic>INTERFERENCE</topic><topic>JET FIGHTERS</topic><topic>LPN-ARO-P41C-H7</topic><topic>MACH NUMBER</topic><topic>MEASUREMENT</topic><topic>PE65807F</topic><topic>PITCH(MOTION)</topic><topic>SCALE MODELS</topic><topic>SDM(Standard Dynamic Model)</topic><topic>STATIC STABILITY</topic><topic>STING MOUNTS</topic><topic>Test Facilities, Equipment and Methods</topic><topic>TEST METHODS</topic><topic>WIND TUNNEL MODELS</topic><topic>WING BODY CONFIGURATIONS</topic><topic>YAW</topic><toplevel>online_resources</toplevel><creatorcontrib>Cyran,F B</creatorcontrib><creatorcontrib>Chaney,M J</creatorcontrib><creatorcontrib>ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN</creatorcontrib><collection>DTIC Technical Reports</collection><collection>DTIC STINET</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Cyran,F B</au><au>Chaney,M J</au><aucorp>ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN</aucorp><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>Sting Interference Effects on the SDM Aircraft as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0.3 through 1.3</btitle><date>1980-10</date><risdate>1980</risdate><abstract>An investigation was conducted to determine the effects of sting-support interference on the measurement of pitch damping, yaw-damping, pitching-moment slope, yawing-moment slope, pitching moment, and base pressure. The model was the Standard Dynamics Model (SDM). The forced oscillation technique was used to obtain data at Mach numbers 0.3 to 1.3 and Reynolds numbers, based on the model mean aerodynamic chord (MAC), of 0.3 million to 3.1 million. Amplitudes of oscillation were 1.0, 1.5, and 2.0 deg, and the reduced frequency parameter ranged from 0.009 to 0.032 radians.
Prepared in cooperation with ARO, Inc., Tullahoma, TN.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng |
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| source | DTIC Technical Reports |
| subjects | Aerodynamic chord AERODYNAMIC STABILITY Aerodynamics ANGLE OF ATTACK BASE PRESSURE DAMPING INTERFERENCE JET FIGHTERS LPN-ARO-P41C-H7 MACH NUMBER MEASUREMENT PE65807F PITCH(MOTION) SCALE MODELS SDM(Standard Dynamic Model) STATIC STABILITY STING MOUNTS Test Facilities, Equipment and Methods TEST METHODS WIND TUNNEL MODELS WING BODY CONFIGURATIONS YAW |
| title | Sting Interference Effects on the SDM Aircraft as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0.3 through 1.3 |
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