Non-waisted fuselage design for supersonic aircraft

Details Non-waisted fuselage design for supersonic aircraft Non-waisted fuselage design for supersonic aircraft

1997-12-01

1999-05-04

Jordan, Charles T.

Aeronautics and astronautics

Aircraft structure

Details

244119, B64C 138

Patent

active

058994130

ABSTRACT:
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.

REFERENCES:
patent: 2874922 (1959-02-01), Whitcomb

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