A Wind Tunnel Study of a Sting-Mounted Circulation Control Wing
This wind tunnel study investigated the feasibility of testing a sting mounted circulation control wing. A 20% thick, 8.5% cambered rectangular wing was designed, built, and tested in the AFIT 5-ft wind tunnel. Lift, drag, equivalent drag, and pitching moment coefficients were obtained at Reynolds n...
Gespeichert in:
| 1. Verfasser: | |
|---|---|
| Format: | Report |
| Sprache: | eng |
| Schlagworte: | |
| Online-Zugang: | Volltext bestellen |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | |
|---|---|
| container_issue | |
| container_start_page | |
| container_title | |
| container_volume | |
| creator | Trainor, John W |
| description | This wind tunnel study investigated the feasibility of testing a sting mounted circulation control wing. A 20% thick, 8.5% cambered rectangular wing was designed, built, and tested in the AFIT 5-ft wind tunnel. Lift, drag, equivalent drag, and pitching moment coefficients were obtained at Reynolds numbers of 600,000 and 900,000. The force and moment results achieved indicate supercirculation was not present. Flow visualization with nylon tufts displayed extreme flow disruption at the trailing edge, due to free-stream impingement on both the sting and blowing air supply hoses. The available blowing air supply was not strong enough to produce a jet flow with the momentum needed to overcome this disruption. Wing model design changes were recommended to alleviate this problem. |
| format | Report |
| fullrecord | <record><control><sourceid>dtic_1RU</sourceid><recordid>TN_cdi_dtic_stinet_ADA216248</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>ADA216248</sourcerecordid><originalsourceid>FETCH-dtic_stinet_ADA2162483</originalsourceid><addsrcrecordid>eNrjZLB3VAjPzEtRCCnNy0vNUQguKU2pVMhPU0gEMjPz0nV980vzSlJTFJwzi5JLcxJLMvPzFJzz80qK8nNAGtN5GFjTEnOKU3mhNDeDjJtriLOHbkpJZnJ8MdCM1JJ4RxdHI0MzIxMLYwLSACfVLQk</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>report</recordtype></control><display><type>report</type><title>A Wind Tunnel Study of a Sting-Mounted Circulation Control Wing</title><source>DTIC Technical Reports</source><creator>Trainor, John W</creator><creatorcontrib>Trainor, John W ; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING</creatorcontrib><description>This wind tunnel study investigated the feasibility of testing a sting mounted circulation control wing. A 20% thick, 8.5% cambered rectangular wing was designed, built, and tested in the AFIT 5-ft wind tunnel. Lift, drag, equivalent drag, and pitching moment coefficients were obtained at Reynolds numbers of 600,000 and 900,000. The force and moment results achieved indicate supercirculation was not present. Flow visualization with nylon tufts displayed extreme flow disruption at the trailing edge, due to free-stream impingement on both the sting and blowing air supply hoses. The available blowing air supply was not strong enough to produce a jet flow with the momentum needed to overcome this disruption. Wing model design changes were recommended to alleviate this problem.</description><language>eng</language><subject>Aerodynamics ; AIR FLOW ; AIR SUPPLIES ; BLOWERS ; CIRCULATION CONTROL WING ; COEFFICIENTS ; DISPLAY SYSTEMS ; DRAG ; FEASIBILITY STUDIES ; FLOW ; FLOW VISUALIZATION ; FREE STREAM ; IMPINGEMENT ; JET FLOW ; MOMENTS ; MOMENTUM ; NYLON ; PITCH(MOTION) ; THESES ; TRAILING EDGES ; V/STOL ; VERTICAL TAKEOFF AIRCRAFT ; WIND TUNNELS ; WINGS</subject><creationdate>1989</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/ADA216248$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Trainor, John W</creatorcontrib><creatorcontrib>AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING</creatorcontrib><title>A Wind Tunnel Study of a Sting-Mounted Circulation Control Wing</title><description>This wind tunnel study investigated the feasibility of testing a sting mounted circulation control wing. A 20% thick, 8.5% cambered rectangular wing was designed, built, and tested in the AFIT 5-ft wind tunnel. Lift, drag, equivalent drag, and pitching moment coefficients were obtained at Reynolds numbers of 600,000 and 900,000. The force and moment results achieved indicate supercirculation was not present. Flow visualization with nylon tufts displayed extreme flow disruption at the trailing edge, due to free-stream impingement on both the sting and blowing air supply hoses. The available blowing air supply was not strong enough to produce a jet flow with the momentum needed to overcome this disruption. Wing model design changes were recommended to alleviate this problem.</description><subject>Aerodynamics</subject><subject>AIR FLOW</subject><subject>AIR SUPPLIES</subject><subject>BLOWERS</subject><subject>CIRCULATION CONTROL WING</subject><subject>COEFFICIENTS</subject><subject>DISPLAY SYSTEMS</subject><subject>DRAG</subject><subject>FEASIBILITY STUDIES</subject><subject>FLOW</subject><subject>FLOW VISUALIZATION</subject><subject>FREE STREAM</subject><subject>IMPINGEMENT</subject><subject>JET FLOW</subject><subject>MOMENTS</subject><subject>MOMENTUM</subject><subject>NYLON</subject><subject>PITCH(MOTION)</subject><subject>THESES</subject><subject>TRAILING EDGES</subject><subject>V/STOL</subject><subject>VERTICAL TAKEOFF AIRCRAFT</subject><subject>WIND TUNNELS</subject><subject>WINGS</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1989</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNrjZLB3VAjPzEtRCCnNy0vNUQguKU2pVMhPU0gEMjPz0nV980vzSlJTFJwzi5JLcxJLMvPzFJzz80qK8nNAGtN5GFjTEnOKU3mhNDeDjJtriLOHbkpJZnJ8MdCM1JJ4RxdHI0MzIxMLYwLSACfVLQk</recordid><startdate>198912</startdate><enddate>198912</enddate><creator>Trainor, John W</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>198912</creationdate><title>A Wind Tunnel Study of a Sting-Mounted Circulation Control Wing</title><author>Trainor, John W</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_ADA2162483</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1989</creationdate><topic>Aerodynamics</topic><topic>AIR FLOW</topic><topic>AIR SUPPLIES</topic><topic>BLOWERS</topic><topic>CIRCULATION CONTROL WING</topic><topic>COEFFICIENTS</topic><topic>DISPLAY SYSTEMS</topic><topic>DRAG</topic><topic>FEASIBILITY STUDIES</topic><topic>FLOW</topic><topic>FLOW VISUALIZATION</topic><topic>FREE STREAM</topic><topic>IMPINGEMENT</topic><topic>JET FLOW</topic><topic>MOMENTS</topic><topic>MOMENTUM</topic><topic>NYLON</topic><topic>PITCH(MOTION)</topic><topic>THESES</topic><topic>TRAILING EDGES</topic><topic>V/STOL</topic><topic>VERTICAL TAKEOFF AIRCRAFT</topic><topic>WIND TUNNELS</topic><topic>WINGS</topic><toplevel>online_resources</toplevel><creatorcontrib>Trainor, John W</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>Trainor, John W</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>A Wind Tunnel Study of a Sting-Mounted Circulation Control Wing</btitle><date>1989-12</date><risdate>1989</risdate><abstract>This wind tunnel study investigated the feasibility of testing a sting mounted circulation control wing. A 20% thick, 8.5% cambered rectangular wing was designed, built, and tested in the AFIT 5-ft wind tunnel. Lift, drag, equivalent drag, and pitching moment coefficients were obtained at Reynolds numbers of 600,000 and 900,000. The force and moment results achieved indicate supercirculation was not present. Flow visualization with nylon tufts displayed extreme flow disruption at the trailing edge, due to free-stream impingement on both the sting and blowing air supply hoses. The available blowing air supply was not strong enough to produce a jet flow with the momentum needed to overcome this disruption. Wing model design changes were recommended to alleviate this problem.</abstract><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | eng |
| recordid | cdi_dtic_stinet_ADA216248 |
| source | DTIC Technical Reports |
| subjects | Aerodynamics AIR FLOW AIR SUPPLIES BLOWERS CIRCULATION CONTROL WING COEFFICIENTS DISPLAY SYSTEMS DRAG FEASIBILITY STUDIES FLOW FLOW VISUALIZATION FREE STREAM IMPINGEMENT JET FLOW MOMENTS MOMENTUM NYLON PITCH(MOTION) THESES TRAILING EDGES V/STOL VERTICAL TAKEOFF AIRCRAFT WIND TUNNELS WINGS |
| title | A Wind Tunnel Study of a Sting-Mounted Circulation Control Wing |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-02-03T17%3A02%3A01IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-dtic_1RU&rft_val_fmt=info:ofi/fmt:kev:mtx:book&rft.genre=unknown&rft.btitle=A%20Wind%20Tunnel%20Study%20of%20a%20Sting-Mounted%20Circulation%20Control%20Wing&rft.au=Trainor,%20John%20W&rft.aucorp=AIR%20FORCE%20INST%20OF%20TECH%20WRIGHT-PATTERSON%20AFB%20OH%20SCHOOL%20OF%20ENGINEERING&rft.date=1989-12&rft_id=info:doi/&rft_dat=%3Cdtic_1RU%3EADA216248%3C/dtic_1RU%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true |