Hyper-X flight engine ground testing for flight risk reduction

被引:33
作者
Huebner, LD [1 ]
Rock, KE
Ruf, EG
Witte, DW
Andrews, EH
机构
[1] NASA Langley Res Ctr, Hyperson Airbreathing Prop Branch, Hampton, VA 23681 USA
[2] FDC NYMA Inc, Hyper X Program Off, Hampton, VA 23681 USA
关键词
D O I
10.2514/2.3774
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
Airframe-integrated scramjet engine testing has been completed at Mach 7 flight conditions in the NASA Langley 8-Foot High Temperature Tunnel as part of the NASA Hyper-X program. This test provided engine performance and operability data, as well as design and database verification, for the Mach 7 flight tests of the Hyper-X research vehicle, which will provide the first-ever airframe-integrated scramjet data in flight. The Hyper-X Flight Engine, a duplicate Mach 7 scramjet engine for flight, was mounted on an airframe structure that replicated the entire three-dimensional propulsion flowpath from the vehicle leading edge to the vehicle trailing edge. This model was also tested to verify and validate the complete flightlike engine system. The subsystems that were subjected to flightlike conditions are described, and supporting data are presented. The results from this test help to reduce risk for the Mach 7 flights of the Hyper-X research vehicle.
引用
收藏
页码:844 / 852
页数:9
相关论文
共 8 条
[1]   Hypersonic boundary-layer trip development for Hyper-X [J].
Berry, SA ;
Auslender, AH ;
Dilley, AD ;
Calleja, JF .
JOURNAL OF SPACECRAFT AND ROCKETS, 2001, 38 (06) :853-864
[2]   Integrated aeropropulsive computational fluid dynamics methodology for the Hyper-X flight experiment [J].
Cockrell, CE ;
Engelund, WC ;
Bittner, RD ;
Jentink, TN ;
Dilley, AD ;
Frendi, A .
JOURNAL OF SPACECRAFT AND ROCKETS, 2001, 38 (06) :836-843
[3]  
ENGELUND WC, 1999, 997215 ISABE
[4]  
Hodge J., 2000, P 21 AER MEAS TECHN, P2646
[5]  
Huebner L D, 2000, 20003605 AIAA
[6]  
RAUSCH VL, 1997, INT S AIR BREATH ENG
[7]  
RAUSCH VL, 1999, INT S AIR BREATH ENG
[8]  
ROCK KE, 1999, INT S AIR BREATH ENG