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Evaluation of Aircraft Performance Algorithms in Federal Aviation Administration's Integrated Noise Model by Wei-Nian Su

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Evaluation of Aircraft Performance Algorithms in Federal Aviation Administration's Integrated Noise Model by Wei-Nian Su Evaluation of Aircraft Performance Algorithms in Federal Aviation Administration's Integrated Noise Model by Wei-Nian Su B.S. Aerospace Engineering, Iowa State University, 1996 Submitted to the Department of Aeronautics and Astronautics in partial fulfillment of the requirement for the Degree of Master of Science in Aeronautics and Astronautics at the Massachusetts Institute of Technology February, 1999 ©1999 Massachusetts Institute of Technology. All rights reserved. Author........... .................... ,. ....... .. ... ............................................................................ Department of Aeronautics and Astronautics January 14, 1999 Certifie d b y .............................. ............... .............. ..................... V. ... ... ..o..... ... ..C r Certe b( (Professor John-Paul Clarke Department of Aeronautics and Astronautics Thesis Supervisor Accepted by .................................................................... ..... ........ ........ .. .... ...... Professor Jaime Peraire Chairman, epartment Graduate Committee MASSACHUSETTS INSTITUTE OF TECHNOLOGY MAY 1 7 1999 -oWWW LIBRARIES Evaluation of Aircraft Performance Algorithms in Federal Aviation Administration's Integrated Noise Model by Wei-Nian Su Submitted to the Department of Aeronautics and Astronautics Engineering on January 14, 1999 in partial fulfillment of the requirement for the Degree of Master of Science in Aeronautics and Astronautics Engineering 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. Thesis Supervisor: Dr. John-Paul Clarke Title: Charles Stark Draper Assistant Professor of Aeronautics and Astronautics Acknowledgments Over the past two years, I have met many people who have made my time at MIT worthwhile. I would like to take this moment to express my deep gratitude to those who have made it possible for me to achieve this accomplishment. In particular, I would like to extend my appreciation to the following individuals and organizations. First of all, I would like to thank my advisor, Prof. John-Paul Clarke, for his encouragement and guidance throughout this research. I also like to thank Mr. Gregg Fleming from Volpe National Transportation Systems Center for funding my research. In addition, I also like to thank Mr. Jim Brooks from Delta Airline for providing valuable data. Finally, I would like to thank my family members: my father, Mr. Shih-Ping Su, my mother, Mrs. Yue-Ching Lin, my sister, Yua-Hwa Su, my brother, Wei-Ping Su, and my girlfriend, Miss Shine-Yi Wong, for their love and support throughout my study at MIT. This research was funded by Volpe National Transportation Systems Center, U.S. Department of Transportation, and performed in the Flight Transportation Lab. Contents A bstract........................................................................................ ........................................... 2........ A cknow ledgm ents..................................... ................................................................................... 3 Contents........................................................................................ ........................................... 4....... List of Tables..................................................................................... ............................................. List of Figures.................. .................................................................................................. 10 N om enclature....................................................................................... ........................................ 12 Chapter 1. Introduction......................................................... ................................................. 15 1.1 Background of INM .................................................................................. 15 1.2 M otivation............... ......................................................................................... 15 1.3 Overview of Thesis............................................................................................................ 16 Chapter 2. Atmospheric Model and True Airspeed Model.....................................18 2.1 Standard Atm osphere.................................................. ............................................ 18 2.1.1 IN M 's Atm ospheric M odel............................... .......................19 2.2 Airspeed M easurem ent................................................................................................ 20 2.2.1 Previous W ork................................................ .......................................... 21 2.2.2 True A irspeed M odel................................................. .......... ........... 22 2.3 Conclusion of Chapter 2................................................ .......................................... 24 Chapter 3. Takeoff and Clim b Thrust M odel................................................ ......... ......... 25 3.1 Previous W ork............................................................. ................................................ 25 3.2 Quadratic Thrust M odel..................................................... .......................................... 26 3.3 Evaluation of Coefficients.......................................................................................... 31 3.3.1 Ante-Break Equation...................................................... ............................. 31 3.3.2 Post-Break Equation................................................. ........... ............ 33 3.4 V alidation.................................................................................. ................................... 36 3.4.1 Graphical Comparison....................................................................................36 3.4.2 Error A nalysis..................................................... .......................................... 43 3.5 Conclusion of Chapter 3..................................................... ..................................... 45 Chapter 4. Level Flight Thrust Model...................................................................................46 4.1 Previous W ork............................................................. ................................................ 46 4.2 E quation of M otion......................................................... ............................................. 47 4.3 Drag Polar............................................................................................. .......... 48 4.3.1 Drag Polar Model I............................................................49 4.3.2 Drag Polar Model II...........................................................50 4.3.3 Effects of Reynolds Number on Drag Polar.....................................50 4.4 Level-Flight Thrust......................................................... ............................................. 51 4.4.1 Level-Flight Thrust Model I.................................................. 52 4.4.2 Level-Flight Thrust Model II.................................................54 4.5 Validation of Level-Flight Thrust Models.............................. ............... 54 4.5.1 Comparison of Proposed Models with INM Model........................................54 4.5.2 E rror A nalysis..................................................... .......................................... 57 4.5.3 Pro and Con Between Models............................... ......... ........ 60 4.6 C onclusion of Chapter 4................................................. .......................................... 61 Chapter 5. Clim b Performance.................................................. ............................................ 62 5.1 Previous W ork............................................................. ................................................ 62 5.2 Equation of Motion and Flight Path Angle Correction Factor................................ 63 5.3 Evaluation of Flight Path Angle Correction Factor................................. ...... 65 5.3.1 Constant Equivalent Airspeed Climb Model...........................................66 5.3.2 Exact Constant Calibrated Airspeed Climb Model.....................................67 5.3.3 Simplified
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