DETERMINATION OF THE THRUST REQUIREMENT FOR A FIGHTER AIRCRAFT ENGINE VIA MISSION ANALYSIS

  • Serdar Duman
  • Onur Tunçer
Keywords: Mission Analysis, Constraint Analysis, Thrust Loading, Wing Loading

Abstract

In order to initiate the design process for  a new aeroengine, it would be necessary that a matching study be performed between the aircraft under design and its prospective power plant. In this work wing loading and  engine thrust reqiurements are determined. Within this context thrust level is determined for a fighter jet whose mission profile is pre-determined.

While the mission profile is being decided upon a typical first-day-of-the-war mission scenario for a new generation fighter aircraft is considered. Mission legs were handled individually and the solution space is restricted by drawing the corresponding constraint curve for each one. A point within the feasible solutions region is selected regarding the state-of-the-art. For the determined mission profile the appropriate sea level thrust to take-off weight ratio / happens to be around 1.2. At the design point the selected thrust loading  is 7.0 kPa. As a result of mission analysis it has been observed that the aircaft spends 1.9% of its take-off weight as ammunition and 58% of its initial take-off weight as fuel. The overall duration for the mission is calculated to be 98 minutes.

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Published
2011-01-24
How to Cite
[1]
S. Duman and O. Tunçer, “DETERMINATION OF THE THRUST REQUIREMENT FOR A FIGHTER AIRCRAFT ENGINE VIA MISSION ANALYSIS”, JAST, vol. 5, no. 1, pp. 27-39, Jan. 2011.
Section
Articles