Computation of Nozzle Flow in a N2O/HTPB Hybrid Rocket Motor

Computation of Nozzle Flow in a N2O/HTPB Hybrid Rocket Motor

Author(s):

H. Tian ( Beijing University of Aeronautics and Astronautics, Beijing, China (prc) )
G. Cai

Publication title:

AIAA meeting papers on disc

Title of ser.:

AIAA Paper : AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Ser. no.:

2007

Pub. Year:

2007

No.:

2007-5370

Paper no.:

AIAA Paper 2007-5370

Pub. info.:

Reston, Va.: American Institute of Aeronautics and Astronautics

ISSN:

10877215

Language:

English

Call no.:

A07400/200716 [CD-ROM 2007 Disc 16]

Type:

Technical Paper

Details

TDL ID:	ZA00049508
Series ID:	PA00000151
Conf. info. (Name):	AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Conf. info. (Number):	43rd
Conf. info. (Venue):	Cincinnati, OH
Conf. info. (Date):	2007.07.08-2007.07.11
Note for article:	43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Cincinnati, OH, July 8-11, 2007

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