TY - GEN
T1 - Effect of fan pressure ratio and bypass ratio on business jet range performance
AU - Myose, Roy Y.
AU - Young, Trevor
AU - Heron, Ismael
PY - 2006
Y1 - 2006
N2 - A model for the aircraft performance including a Brayton turbofan engine cycle analysis was developed in order to study the effect of varying the fan pressure ratio and bypass ratio on the range performance of a medium-size business jet. In the classic flight mechanics treatment of aircraft performance, maximizing range requires maximizing CL1/2/CD. This classic approach, however, assumes that thrust specific fuel consumption is a constant. Previous studies, which include the effect of variation in thrust specific fuel consumption, typically seek to determine the optimum flight Mach number under a constant altitude - constant speed flight condition. This project was motivated by a desire to study what effect variations in flight conditions such as speed, lift-to-drag ratio, or thrust settings have on aircraft performance. An increase in range of approximately 2% to 8% was obtained, depending upon the bypass ratio, by maximizing U(L/D)/TSFC compared to the case where CL1/2/CD was maximized.
AB - A model for the aircraft performance including a Brayton turbofan engine cycle analysis was developed in order to study the effect of varying the fan pressure ratio and bypass ratio on the range performance of a medium-size business jet. In the classic flight mechanics treatment of aircraft performance, maximizing range requires maximizing CL1/2/CD. This classic approach, however, assumes that thrust specific fuel consumption is a constant. Previous studies, which include the effect of variation in thrust specific fuel consumption, typically seek to determine the optimum flight Mach number under a constant altitude - constant speed flight condition. This project was motivated by a desire to study what effect variations in flight conditions such as speed, lift-to-drag ratio, or thrust settings have on aircraft performance. An increase in range of approximately 2% to 8% was obtained, depending upon the bypass ratio, by maximizing U(L/D)/TSFC compared to the case where CL1/2/CD was maximized.
UR - http://www.scopus.com/inward/record.url?scp=33846495620&partnerID=8YFLogxK
U2 - 10.2514/6.2006-7706
DO - 10.2514/6.2006-7706
M3 - Conference contribution
AN - SCOPUS:33846495620
SN - 1563478250
SN - 9781563478253
T3 - Collection of Technical Papers - 6th AIAA Aviation Technology, Integration, and Operations Conference
SP - 67
EP - 81
BT - Collection of Technical Papers - 6th AIAA Aviation Technology, Integration, and Operations Conference
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 6th AIAA Aviation Technology, Integration, and Operations Conference
Y2 - 25 September 2006 through 27 September 2006
ER -