Propulsion considerations for supersonic oblique flying wings

Propulsion considerations unique to the supersonic oblique flying wing, including cycle selection, sizing, and integration were investigated via the development and interrogation of aerodynamic and propulsive synthesis models. These models were an amalgamation of computational tools (MSES), linearized theory, parametric estimation, and quasi D thermodynamic cycle analysis. Lift-to-drag ratio, thrust specific fuel consumption, and nacelle wave drag were examined as intermediate figures of merit that would ultimately impact the final performance metric-namely, range parameter and specific excess power. It was found that higher bypass ratio engines could yield an increase in the range parameter up until a critical mach number, above which the increasing nacelle drag would offset the TSFC reductions to yield a net degradation in range performance. Between the baseline TF30-type cycle and its BPR 2.4 modified variant, this critical mach number was found to be at approximately M 2.0 for TT4/TT2 = 5, and M 2.2 for TT4/TT2 = 6.

Department dc:contributor.department

Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.

Grantor dc:publisher

Massachusetts Institute of Technology

Year dc:date.issued

2006

Author dc:creator

• Shinagawa, Yuto

Advisor dc:contributor.advisor

• Alan H. Epstein.

• Aeronautics and Astronautics.

Statement dc:rights

• M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.

Licence dc:rights.uri

• http://dspace.mit.edu/handle/1721.1/7582

Language dc:language.iso

eng

Handle dc:identifier.uri

http://hdl.handle.net/1721.1/35565

OAI identifier oai:identifier

oai:dspace.mit.edu:1721.1/35565