Drag prediction method of powered-on civil aircraft based on thrust drag bookkeeping  

作　　者：Zhang Yufei Chen Haixin Fu Song Zhang Miao Zhang Meihong 

机构地区：[1]School of Aerospace Engineering, Tsinghua University [2]Shanghai Aircraft Design and Research Institute

出　　处：《Chinese Journal of Aeronautics》2015年第4期1023-1033,共11页中国航空学报（英文版）

基　　金：supported by the National Key Basic Research Program of China (No.2014CB744801);the National Natural Science Foundation of China (Nos.11102098 and 11372160);the Aeronautical Science Foundation of China (No.2013ZA58002)

摘　　要：A drag prediction method based on thrust drag bookkeeping（TDB） is introduced for civil jet propulsion/airframe integration performance analysis.The method is derived from the control volume theory of a powered-on nacelle.Key problem of the TDB is identified to be accurate prediction of velocity coefficient of the powered-on nacelle.Accuracy of CFD solver is validated by test cases of the first AIAA Propulsion Aerodynamics Workshop.Then the TDB method is applied to thrust and drag decomposing of a realistic aircraft.A linear relation between the computations assumed free stream Mach number and the velocity coefficient result is revealed.The thrust losses caused by nozzle internal drag and pylon scrubbing are obtained by the isolated nacelle and mapped on to the in-flight whole configuration analysis.Effects of the powered-on condition are investigated by comparing through-flow configuration with powered-on configuration.The variance on aerodynamic coefficients and pressure distribution is numerically studied.A drag prediction method based on thrust drag bookkeeping（TDB） is introduced for civil jet propulsion/airframe integration performance analysis.The method is derived from the control volume theory of a powered-on nacelle.Key problem of the TDB is identified to be accurate prediction of velocity coefficient of the powered-on nacelle.Accuracy of CFD solver is validated by test cases of the first AIAA Propulsion Aerodynamics Workshop.Then the TDB method is applied to thrust and drag decomposing of a realistic aircraft.A linear relation between the computations assumed free stream Mach number and the velocity coefficient result is revealed.The thrust losses caused by nozzle internal drag and pylon scrubbing are obtained by the isolated nacelle and mapped on to the in-flight whole configuration analysis.Effects of the powered-on condition are investigated by comparing through-flow configuration with powered-on configuration.The variance on aerodynamic coefficients and pressure distribution is numerically studied.

关 键 词：Discharge coefficient Drag prediction Powered-on configuration Thrust drag bookkeeping Velocity coefficient 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程] V271.1