A method for designing a non-waisted fuselage for supersonic wing/fuselage configurations that increases the fuselage volume and improves the supersonic aerodynamic performance compared to a conventional waisted-fuselage configuration. The method entails removing the waisted region of an existing waisted-fuselage configuration by linearly reconstructing cross-sections between the endpoints representing the waisted cross-sectional area portion to create a modified fuselage configuration without waisting. This configuration will have increased fuselage volume and improved supersonic aerodynamic performance. The fuselage camber can then be optimized using non-linear aerodynamic methods to further increase the supersonic aerodynamic performance.
Non-waisted fuselage design for supersonic aircraft
1999-05-04
Sonstige
Keine Angabe
Englisch
Europäisches Patentamt | 2019
|SUPERSONIC AIRCRAFT WITH IN-FUSELAGE CARGO COMPARTMENTS
Europäisches Patentamt | 2016
|Europäisches Patentamt | 2021
|STUD - STRAIGHT, WAISTED, .4375-14 X .4375-20UNF-3A
SAE Technical Papers | 2019