This paper presents a thermodynamical and aerodynamical analyses of the behaviour of a hypothetical lightweight combat aircraft operating on a single engine afterburning turbojet. An airframe was selected for the aircraft thus specifying the aerodynamical characteristics. Then an engine was developed to achieve the basic criteria for the fulfillment of certain predefined mission requirements such as taking off from a runway of specified length, supercruising at particular Mach number, performing high g combat turns, etc. The engine and the airframe were coupled to form a basic aircraft. The capabilities of this aircraft were reviewed thereafter at distinct stages of flight and its capability as an interceptor aircraft was analysed. After careful consideration of all the aspects of the theoretical aircraft, it was concluded that it fulfilled the numerous mandatory requirements demanded for an interceptor aircraft.
Preliminary design analysis of a lightweight combat aircraft
2008-04-01
7 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Preliminary design analysis of a lightweight combat aircraft
Online Contents | 2008
|Preliminary design analysis of a lightweight combat aircraft
Tema Archiv | 2008
|Supersonic combat aircraft design
AIAA | 1979
|Engineering Index Backfile | 1953
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