This chapter discusses general characteristics of typical configurations designed for supersonic cruising flight and derives criteria for optimizing design selection variables that have significant effect on the aerodynamic efficiency, in particular the configuration slenderness ratio, the wing loading, and the cruise altitude. Configuration A has a discrete fuselage enclosing the payload in combination with a swept‐back arrow wing. It has a favorable longitudinal variation of the cross section according to the principles of the supersonic area rule. Configuration B is an integrated and blended all‐wing configuration. Its internal volume for payload and fuel is spread out in longitudinal and lateral directions. Apart from the empennage drag, the full‐configuration drag is based on addition of the wing‐alone drag and the fuselage‐alone drag. Many supersonic cruising vehicle configuration design studies have been based on a tailless configuration with relatively low wing loading and aspect ratio ‐ the basic configuration of the Concorde.
Aerodynamic Efficiency of SCV Configurations
2020-07-07
17 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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