{"id":{"repo_id":"mit","oai_identifier":"oai:dspace.mit.edu:1721.1/113724"},"canonical_url":"https://search.dev.ndltd.org/etd/mit/oai:dspace.mit.edu:1721.1/113724","repository":{"repo_id":"mit","name":"MIT","base_url":"https://dspace.mit.edu/oai/request"},"display":{"title":"A doublet panel method for generalized supersonic lifting surfaces","abstract":"An improved doublet panel method for calculating the aerodynamic properties of lifting surfaces in supersonic flows is derived and implemented. The lifting surfaces are discretized into an arbitrary number of doublet panels with unknown singularity strength, whose perturbation velocity potentials satisfy the supersonic Prandtl-Glauert equation. To prevent field singularities in the potential and velocity, the doublet strength of each panel is piecewise linear and continuous in the streamwise direction. In addition, the panels can be swept at different angles at their leading and trailing edges, allowing for generalized lifting surfaces to be analyzed. The component of the perturbation velocity that is normal to the lifting surface at each specified control point induced by each doublet panel is calculated. Applying the flow tangency boundary condition at the control points forms a linear system that is solved for the difference in doublet strength between the trailing and leading edges of each panel. The perturbation velocity components of this method are compared to those of the Woodward method. The numerical solutions of this method are compared to the analytical solutions of some test cases. Convergence is obtained for both the lift coefficient and the perturbation velocity component distribution.","abstract_html":"An improved doublet panel method for calculating the aerodynamic properties of lifting surfaces in supersonic flows is derived and implemented. The lifting surfaces are discretized into an arbitrary number of doublet panels with unknown singularity strength, whose perturbation velocity potentials satisfy the supersonic Prandtl-Glauert equation. To prevent field singularities in the potential and velocity, the doublet strength of each panel is piecewise linear and continuous in the streamwise direction. In addition, the panels can be swept at different angles at their leading and trailing edges, allowing for generalized lifting surfaces to be analyzed. The component of the perturbation velocity that is normal to the lifting surface at each specified control point induced by each doublet panel is calculated. Applying the flow tangency boundary condition at the control points forms a linear system that is solved for the difference in doublet strength between the trailing and leading edges of each panel. The perturbation velocity components of this method are compared to those of the Woodward method. The numerical solutions of this method are compared to the analytical solutions of some test cases. Convergence is obtained for both the lift coefficient and the perturbation velocity component distribution.","abstract_has_math":false,"creators":["Hoskin, Dominique (Dominique Sampson)"],"institution":"Massachusetts Institute of Technology","degree_name":null,"degree_level":null,"degree_discipline":null,"degree_department":"Massachusetts Institute of Technology. Department of Aeronautics and Astronautics.","school":null,"contributors":[],"advisors":["Mark Drela."],"committee_chairs":[],"committee_members":[],"year":2017,"date_issued":"2017","date_published":"2017","updated_at":"2026-07-22T22:21:32Z","subjects":["Aeronautics and Astronautics."],"languages":["eng"],"rights":["MIT theses are protected by copyright. They may be viewed, downloaded, or printed from this source but further reproduction or distribution in any format is prohibited without written permission."],"rights_urls":["http://dspace.mit.edu/handle/1721.1/7582"],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/1721.1/113724","outbound_label":"Handle","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor.advisor","label":"Advisor","values":["Mark Drela."]},{"key":"dc:contributor.department","label":"Department","values":["Massachusetts Institute of Technology. Department of Aeronautics and Astronautics."]},{"key":"dc:contributor.other","label":"Dc Contributor Other","values":["Massachusetts Institute of Technology. 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They may be viewed, downloaded, or printed from this source but further reproduction or distribution in any format is prohibited without written permission."]},{"key":"dc:rights.uri","label":"Rights URI","values":["http://dspace.mit.edu/handle/1721.1/7582"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier.uri","label":"Identifier URI","values":["http://hdl.handle.net/1721.1/113724"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2017.","This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.","Cataloged from student-submitted PDF version of thesis.","Includes bibliographical references (page 153)."]},{"key":"dc:description.abstract","label":"Abstract","values":["An improved doublet panel method for calculating the aerodynamic properties of lifting surfaces in supersonic flows is derived and implemented. The lifting surfaces are discretized into an arbitrary number of doublet panels with unknown singularity strength, whose perturbation velocity potentials satisfy the supersonic Prandtl-Glauert equation. To prevent field singularities in the potential and velocity, the doublet strength of each panel is piecewise linear and continuous in the streamwise direction. In addition, the panels can be swept at different angles at their leading and trailing edges, allowing for generalized lifting surfaces to be analyzed. The component of the perturbation velocity that is normal to the lifting surface at each specified control point induced by each doublet panel is calculated. Applying the flow tangency boundary condition at the control points forms a linear system that is solved for the difference in doublet strength between the trailing and leading edges of each panel. The perturbation velocity components of this method are compared to those of the Woodward method. The numerical solutions of this method are compared to the analytical solutions of some test cases. Convergence is obtained for both the lift coefficient and the perturbation velocity component distribution."]},{"key":"dc:description.degree","label":"Dc Description Degree","values":["S.M."]},{"key":"dc:title","label":"Title","values":["A doublet panel method for generalized supersonic lifting surfaces"]}]}],"canonical_facts":{"dc:contributor.advisor":["Mark Drela."],"dc:contributor.department":["Massachusetts Institute of Technology. Department of Aeronautics and Astronautics."],"dc:contributor.other":["Massachusetts Institute of Technology. Department of Aeronautics and Astronautics."],"dc:creator":["Hoskin, Dominique (Dominique Sampson)"],"dc:date.accessioned":["2018-02-16T19:27:14Z"],"dc:date.available":["2018-02-16T19:27:14Z"],"dc:date.issued":["2017"],"dc:description":["Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2017.","This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.","Cataloged from student-submitted PDF version of thesis.","Includes bibliographical references (page 153)."],"dc:description.abstract":["An improved doublet panel method for calculating the aerodynamic properties of lifting surfaces in supersonic flows is derived and implemented. The lifting surfaces are discretized into an arbitrary number of doublet panels with unknown singularity strength, whose perturbation velocity potentials satisfy the supersonic Prandtl-Glauert equation. To prevent field singularities in the potential and velocity, the doublet strength of each panel is piecewise linear and continuous in the streamwise direction. In addition, the panels can be swept at different angles at their leading and trailing edges, allowing for generalized lifting surfaces to be analyzed. The component of the perturbation velocity that is normal to the lifting surface at each specified control point induced by each doublet panel is calculated. Applying the flow tangency boundary condition at the control points forms a linear system that is solved for the difference in doublet strength between the trailing and leading edges of each panel. The perturbation velocity components of this method are compared to those of the Woodward method. The numerical solutions of this method are compared to the analytical solutions of some test cases. Convergence is obtained for both the lift coefficient and the perturbation velocity component distribution."],"dc:description.degree":["S.M."],"dc:identifier.uri":["http://hdl.handle.net/1721.1/113724"],"dc:language.iso":["eng"],"dc:publisher":["Massachusetts Institute of Technology"],"dc:rights":["MIT theses are protected by copyright. They may be viewed, downloaded, or printed from this source but further reproduction or distribution in any format is prohibited without written permission."],"dc:rights.uri":["http://dspace.mit.edu/handle/1721.1/7582"],"dc:subject":["Aeronautics and Astronautics."],"dc:title":["A doublet panel method for generalized supersonic lifting surfaces"],"dc:type":["Thesis"]},"updated_at":"2026-07-22T22:21:32Z"}