Dynamic wake models have been used in real-time flight simulations for over thirty years. The models have evolved from the earliest, three-degree-of-freedom models (derived from momentum theory) to full finite-state models derived from potential flow theory by a formal Galerkin method. These models are widely used in industry, but still have some drawbacks that need to be remedied. These drawbacks include: 1.) lack of good convergence both on the disk and off the disk (one can use one or the other but not both), 2.) poor results downstream in the limit of shallow skew angles, 3.) poor convergence inside of the rotor wake, 4.) lack of the effects of wake curvature and wake contraction, and 5.) lack of other important nonlinearities. This thesis uses applications of adjoint theorem, a special change of variable and effective introduction of solution blending to overcome these obstacles. The resultant model is well-behaved in all regimes and is applicable to use in realistic problems of flight simulation, even when only a few states are allowed.
","abstract_html":"<p>Dynamic wake models have been used in real-time flight simulations for over thirty years. The models have evolved from the earliest, three-degree-of-freedom models (derived from momentum theory) to full finite-state models derived from potential flow theory by a formal Galerkin method. These models are widely used in industry, but still have some drawbacks that need to be remedied. These drawbacks include: 1.) lack of good convergence both on the disk and off the disk (one can use one or the other but not both), 2.) poor results downstream in the limit of shallow skew angles, 3.) poor convergence inside of the rotor wake, 4.) lack of the effects of wake curvature and wake contraction, and 5.) lack of other important nonlinearities. This thesis uses applications of adjoint theorem, a special change of variable and effective introduction of solution blending to overcome these obstacles. The resultant model is well-behaved in all regimes and is applicable to use in realistic problems of flight simulation, even when only a few states are allowed.</p>","abstract_has_math":false,"creators":["Huang, Jianzhe"],"institution":null,"degree_name":"Doctor of Philosophy (PhD)","degree_level":"Dissertation","degree_discipline":"Mechanical Engineering & Materials Science","degree_department":null,"school":null,"contributors":["David Peters","Kenneth Jerina, Swami Karunamoorthy, Mark Meacham, Shankar Sastry, Heinz Schaettler"],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2015,"date_issued":"2015-05-15T07:00:00Z","date_published":"2015-05-15T07:00:00Z","updated_at":"2026-07-24T06:13:23Z","subjects":["finite state inflow model","helicopter","nonlinear","wake skew","Engineering"],"languages":["English (en)"],"rights":["I have not registered my thesis with the U.S. Copyright Office, and do not intend to."],"rights_urls":[],"identifier_entries":[{"key":"dc:identifier","label":"Identifier","values":["https://openscholarship.wustl.edu/eng_etds/101"],"render_values":[{"text":"https://openscholarship.wustl.edu/eng_etds/101","href":"https://openscholarship.wustl.edu/eng_etds/101","code":true}]}]},"links":{"outbound_url":"https://doi.org/10.7936/K74M92PW","outbound_label":"DOI","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["David Peters","Kenneth Jerina, Swami Karunamoorthy, Mark Meacham, Shankar Sastry, Heinz Schaettler"]},{"key":"dc:creator","label":"Author","values":["Huang, Jianzhe"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date.available","label":"Dc Date Available","values":["2015-06-18T07:00:00Z"]},{"key":"thesis:degree_discipline","label":"Discipline","values":["Mechanical Engineering & Materials Science","McKelvey School of Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Dissertation"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Doctor of Philosophy (PhD)"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["finite state inflow model","helicopter","nonlinear","wake skew","Engineering"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["English (en)"]},{"key":"dc:rights","label":"Dc Rights","values":["I have not registered my thesis with the U.S. Copyright Office, and do not intend to."]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://doi.org/10.7936/K74M92PW","https://openscholarship.wustl.edu/eng_etds/101"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["Permanent URL: https://doi.org/10.7936/K74M92PW"]},{"key":"dc:description.abstract","label":"Abstract","values":["Dynamic wake models have been used in real-time flight simulations for over thirty years. The models have evolved from the earliest, three-degree-of-freedom models (derived from momentum theory) to full finite-state models derived from potential flow theory by a formal Galerkin method. These models are widely used in industry, but still have some drawbacks that need to be remedied. These drawbacks include: 1.) lack of good convergence both on the disk and off the disk (one can use one or the other but not both), 2.) poor results downstream in the limit of shallow skew angles, 3.) poor convergence inside of the rotor wake, 4.) lack of the effects of wake curvature and wake contraction, and 5.) lack of other important nonlinearities. This thesis uses applications of adjoint theorem, a special change of variable and effective introduction of solution blending to overcome these obstacles. The resultant model is well-behaved in all regimes and is applicable to use in realistic problems of flight simulation, even when only a few states are allowed.
"]},{"key":"dc:title","label":"Title","values":["Potential-flow Inflow Model Including Wake Distortion and Contraction"]}]}],"canonical_facts":{"dc:contributor":["David Peters","Kenneth Jerina, Swami Karunamoorthy, Mark Meacham, Shankar Sastry, Heinz Schaettler"],"dc:creator":["Huang, Jianzhe"],"dc:date.available":["2015-06-18T07:00:00Z"],"dc:description":["Permanent URL: https://doi.org/10.7936/K74M92PW"],"dc:description.abstract":["Dynamic wake models have been used in real-time flight simulations for over thirty years. The models have evolved from the earliest, three-degree-of-freedom models (derived from momentum theory) to full finite-state models derived from potential flow theory by a formal Galerkin method. These models are widely used in industry, but still have some drawbacks that need to be remedied. These drawbacks include: 1.) lack of good convergence both on the disk and off the disk (one can use one or the other but not both), 2.) poor results downstream in the limit of shallow skew angles, 3.) poor convergence inside of the rotor wake, 4.) lack of the effects of wake curvature and wake contraction, and 5.) lack of other important nonlinearities. This thesis uses applications of adjoint theorem, a special change of variable and effective introduction of solution blending to overcome these obstacles. The resultant model is well-behaved in all regimes and is applicable to use in realistic problems of flight simulation, even when only a few states are allowed.
"],"dc:identifier":["https://doi.org/10.7936/K74M92PW","https://openscholarship.wustl.edu/eng_etds/101"],"dc:language":["English (en)"],"dc:rights":["I have not registered my thesis with the U.S. Copyright Office, and do not intend to."],"dc:subject":["finite state inflow model","helicopter","nonlinear","wake skew","Engineering"],"dc:title":["Potential-flow Inflow Model Including Wake Distortion and Contraction"],"thesis:degree_discipline":["Mechanical Engineering & Materials Science","McKelvey School of Engineering"],"thesis:degree_level":["Dissertation"],"thesis:degree_name":["Doctor of Philosophy (PhD)"]},"updated_at":"2026-07-24T06:13:23Z"}