{"id":{"repo_id":"vt","oai_identifier":"oai:vtechworks.lib.vt.edu:10919/56172"},"canonical_url":"https://search.dev.ndltd.org/etd/vt/oai:vtechworks.lib.vt.edu:10919/56172","repository":{"repo_id":"vt","name":"Virginia Tech","base_url":"https://vtechworks.lib.vt.edu/oai/request"},"display":{"title":"Heat transfer effects on a subsonic delta wing","abstract":"With the advent of the \"Space Shuttle\" concept, it has become necessary to study the effects of heat transfer on the aerodynamic and boundary layer characteristics of a heated delta wing. Thus, a symmetrical 60° delta wing was tested up to twice freestream temperature in the Virginia Tech 6' x 6' stability wind tunnel. Summaries of the characteristics of the flow over the unheated wing and the theoretical effects of heat transfer are included. It has been found that heat transfer effects on the wing's aerodynamic characteristics are negligible at angles of attack up to one-third of the maximum lift angle. Beyond this, lift and pitching moment show a very small decrease and increase, respectively, up to maximum lift while drag increases 15 percent to 25 percent at maximum lift. Further increases in drag occur when the wing is yawed. No decrease in stalling angle of attack with heating is found for all yaw angles.","abstract_html":"With the advent of the "Space Shuttle" concept, it has become necessary to study the effects of heat transfer on the aerodynamic and boundary layer characteristics of a heated delta wing. Thus, a symmetrical 60° delta wing was tested up to twice freestream temperature in the Virginia Tech 6' x 6' stability wind tunnel. Summaries of the characteristics of the flow over the unheated wing and the theoretical effects of heat transfer are included. It has been found that heat transfer effects on the wing's aerodynamic characteristics are negligible at angles of attack up to one-third of the maximum lift angle. Beyond this, lift and pitching moment show a very small decrease and increase, respectively, up to maximum lift while drag increases 15 percent to 25 percent at maximum lift. Further increases in drag occur when the wing is yawed. No decrease in stalling angle of attack with heating is found for all yaw angles.","abstract_has_math":false,"creators":["Blohm, Raymond William"],"institution":"Virginia Polytechnic Institute and State University","degree_name":"Master of Science","degree_level":"masters","degree_discipline":"Aerospace Engineering","degree_department":"Aerospace Engineering","school":null,"contributors":[],"advisors":[],"committee_chairs":[],"committee_members":[],"year":1973,"date_issued":"1973","date_published":"1973","updated_at":"2026-07-22T22:19:49Z","subjects":[],"languages":["en"],"rights":["In Copyright"],"rights_urls":["http://rightsstatements.org/vocab/InC/1.0/"],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/10919/56172","outbound_label":"Handle","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor.department","label":"Department","values":["Aerospace Engineering"]},{"key":"dc:creator","label":"Author","values":["Blohm, Raymond William"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date.accessioned","label":"Dc Date Accessioned","values":["2015-08-07T14:18:04Z"]},{"key":"dc:date.available","label":"Dc Date Available","values":["2015-08-07T14:18:04Z"]},{"key":"dc:date.issued","label":"Date","values":["1973"]},{"key":"dc:publisher","label":"Institution","values":["Virginia Polytechnic Institute and State University"]},{"key":"dc:type","label":"Dc Type","values":["Thesis"]},{"key":"dc:type.dcmitype","label":"Dc Type Dcmitype","values":["Text"]},{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["masters"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Master of Science"]},{"key":"thesis:institution_name","label":"Thesis Institution Name","values":["Virginia Polytechnic Institute and State University"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language.iso","label":"Language (ISO)","values":["en"]},{"key":"dc:rights","label":"Dc Rights","values":["In Copyright"]},{"key":"dc:rights.uri","label":"Rights URI","values":["http://rightsstatements.org/vocab/InC/1.0/"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier.uri","label":"Identifier URI","values":["http://hdl.handle.net/10919/56172"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["With the advent of the \"Space Shuttle\" concept, it has become necessary to study the effects of heat transfer on the aerodynamic and boundary layer characteristics of a heated delta wing. Thus, a symmetrical 60° delta wing was tested up to twice freestream temperature in the Virginia Tech 6' x 6' stability wind tunnel. Summaries of the characteristics of the flow over the unheated wing and the theoretical effects of heat transfer are included. It has been found that heat transfer effects on the wing's aerodynamic characteristics are negligible at angles of attack up to one-third of the maximum lift angle. Beyond this, lift and pitching moment show a very small decrease and increase, respectively, up to maximum lift while drag increases 15 percent to 25 percent at maximum lift. Further increases in drag occur when the wing is yawed. No decrease in stalling angle of attack with heating is found for all yaw angles."]},{"key":"dc:description.degree","label":"Dc Description Degree","values":["Master of Science"]},{"key":"dc:format.mimetype","label":"Dc Format Mimetype","values":["application/pdf"]},{"key":"dc:title","label":"Title","values":["Heat transfer effects on a subsonic delta wing"]}]}],"canonical_facts":{"dc:contributor.department":["Aerospace Engineering"],"dc:creator":["Blohm, Raymond William"],"dc:date.accessioned":["2015-08-07T14:18:04Z"],"dc:date.available":["2015-08-07T14:18:04Z"],"dc:date.issued":["1973"],"dc:description.abstract":["With the advent of the \"Space Shuttle\" concept, it has become necessary to study the effects of heat transfer on the aerodynamic and boundary layer characteristics of a heated delta wing. Thus, a symmetrical 60° delta wing was tested up to twice freestream temperature in the Virginia Tech 6' x 6' stability wind tunnel. Summaries of the characteristics of the flow over the unheated wing and the theoretical effects of heat transfer are included. It has been found that heat transfer effects on the wing's aerodynamic characteristics are negligible at angles of attack up to one-third of the maximum lift angle. Beyond this, lift and pitching moment show a very small decrease and increase, respectively, up to maximum lift while drag increases 15 percent to 25 percent at maximum lift. Further increases in drag occur when the wing is yawed. No decrease in stalling angle of attack with heating is found for all yaw angles."],"dc:description.degree":["Master of Science"],"dc:format.mimetype":["application/pdf"],"dc:identifier.uri":["http://hdl.handle.net/10919/56172"],"dc:language.iso":["en"],"dc:publisher":["Virginia Polytechnic Institute and State University"],"dc:rights":["In Copyright"],"dc:rights.uri":["http://rightsstatements.org/vocab/InC/1.0/"],"dc:title":["Heat transfer effects on a subsonic delta wing"],"dc:type":["Thesis"],"dc:type.dcmitype":["Text"],"thesis:degree_discipline":["Aerospace Engineering"],"thesis:degree_level":["masters"],"thesis:degree_name":["Master of Science"],"thesis:institution_name":["Virginia Polytechnic Institute and State University"]},"updated_at":"2026-07-22T22:19:49Z"}