{"id":{"repo_id":"mit","oai_identifier":"oai:dspace.mit.edu:1721.1/47728"},"canonical_url":"https://search.dev.ndltd.org/etd/mit/oai:dspace.mit.edu:1721.1/47728","repository":{"repo_id":"mit","name":"MIT","base_url":"https://dspace.mit.edu/oai/request"},"display":{"title":"Evaluation of aircraft performance algorithms in Federal Aviation Administration's Integrated Noise Model","abstract":"The Integrated Noise Model (INM) has been the Federal Aviation Administration's (FAA) standard tool since 1978 for determining the predicted noise impact in the vicinity of airports. A review of the aircraft performance algorithms in the INM was conducted and improved models for true airspeed, takeoff/climb thrust, level-flight thrust, and climb performance were developed. The true airspeed model with air compressibility correction provides an accurate prediction over a wide range of operating conditions. The quadratic takeoff/climb thrust model as a function of Mach number, altitude, and temperature and the level-flight thrust model derived from the minimum-thrust-flight condition provide an accurate prediction within considered airspeed and altitude range. The climb models for constant equivalent/calibrated airspeed as well as constant climb rate climbs introduce the flight path angle correction factor as a function of altitude, airspeed, and temperature as opposed to constant correction factor used in INM. Comparison of flight profiles predicted by the proposed methods and INM with the flight profiles provided by the Delta Airlines shows that the errors in overall ground distance traversed as well as noise contour shapes are reduced by implementing the proposed models.","abstract_html":"The Integrated Noise Model (INM) has been the Federal Aviation Administration's (FAA) standard tool since 1978 for determining the predicted noise impact in the vicinity of airports. A review of the aircraft performance algorithms in the INM was conducted and improved models for true airspeed, takeoff/climb thrust, level-flight thrust, and climb performance were developed. The true airspeed model with air compressibility correction provides an accurate prediction over a wide range of operating conditions. The quadratic takeoff/climb thrust model as a function of Mach number, altitude, and temperature and the level-flight thrust model derived from the minimum-thrust-flight condition provide an accurate prediction within considered airspeed and altitude range. The climb models for constant equivalent/calibrated airspeed as well as constant climb rate climbs introduce the flight path angle correction factor as a function of altitude, airspeed, and temperature as opposed to constant correction factor used in INM. Comparison of flight profiles predicted by the proposed methods and INM with the flight profiles provided by the Delta Airlines shows that the errors in overall ground distance traversed as well as noise contour shapes are reduced by implementing the proposed models.","abstract_has_math":false,"creators":["Su, Wei-Nian, 1971-"],"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":["John-Paul Clarke."],"committee_chairs":[],"committee_members":[],"year":1999,"date_issued":"1999","date_published":"1999","updated_at":"2026-07-22T22:21:31Z","subjects":["Aeronautics and Astronautics"],"languages":["eng"],"rights":["M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission."],"rights_urls":["http://dspace.mit.edu/handle/1721.1/7582"],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/1721.1/47728","outbound_label":"Handle","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor.advisor","label":"Advisor","values":["John-Paul Clarke."]},{"key":"dc:contributor.department","label":"Department","values":["Massachusetts Institute of Technology. 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A review of the aircraft performance algorithms in the INM was conducted and improved models for true airspeed, takeoff/climb thrust, level-flight thrust, and climb performance were developed. The true airspeed model with air compressibility correction provides an accurate prediction over a wide range of operating conditions. The quadratic takeoff/climb thrust model as a function of Mach number, altitude, and temperature and the level-flight thrust model derived from the minimum-thrust-flight condition provide an accurate prediction within considered airspeed and altitude range. The climb models for constant equivalent/calibrated airspeed as well as constant climb rate climbs introduce the flight path angle correction factor as a function of altitude, airspeed, and temperature as opposed to constant correction factor used in INM. Comparison of flight profiles predicted by the proposed methods and INM with the flight profiles provided by the Delta Airlines shows that the errors in overall ground distance traversed as well as noise contour shapes are reduced by implementing the proposed models."]},{"key":"dc:description.degree","label":"Dc Description Degree","values":["S.M."]},{"key":"dc:title","label":"Title","values":["Evaluation of aircraft performance algorithms in Federal Aviation Administration's Integrated Noise Model"]}]}],"canonical_facts":{"dc:contributor.advisor":["John-Paul Clarke."],"dc:contributor.department":["Massachusetts Institute of Technology. Department of Aeronautics and Astronautics"],"dc:creator":["Su, Wei-Nian, 1971-"],"dc:date.accessioned":["2009-10-01T15:35:35Z"],"dc:date.available":["2009-10-01T15:35:35Z"],"dc:date.issued":["1999"],"dc:description":["Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.","Includes bibliographical references (leaf 110)."],"dc:description.abstract":["The Integrated Noise Model (INM) has been the Federal Aviation Administration's (FAA) standard tool since 1978 for determining the predicted noise impact in the vicinity of airports. A review of the aircraft performance algorithms in the INM was conducted and improved models for true airspeed, takeoff/climb thrust, level-flight thrust, and climb performance were developed. The true airspeed model with air compressibility correction provides an accurate prediction over a wide range of operating conditions. The quadratic takeoff/climb thrust model as a function of Mach number, altitude, and temperature and the level-flight thrust model derived from the minimum-thrust-flight condition provide an accurate prediction within considered airspeed and altitude range. The climb models for constant equivalent/calibrated airspeed as well as constant climb rate climbs introduce the flight path angle correction factor as a function of altitude, airspeed, and temperature as opposed to constant correction factor used in INM. Comparison of flight profiles predicted by the proposed methods and INM with the flight profiles provided by the Delta Airlines shows that the errors in overall ground distance traversed as well as noise contour shapes are reduced by implementing the proposed models."],"dc:description.degree":["S.M."],"dc:identifier.uri":["http://hdl.handle.net/1721.1/47728"],"dc:language.iso":["eng"],"dc:publisher":["Massachusetts Institute of Technology"],"dc:rights":["M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission."],"dc:rights.uri":["http://dspace.mit.edu/handle/1721.1/7582"],"dc:subject":["Aeronautics and Astronautics"],"dc:title":["Evaluation of aircraft performance algorithms in Federal Aviation Administration's Integrated Noise Model"],"dc:type":["Thesis"]},"updated_at":"2026-07-22T22:21:31Z"}