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- W2725037210 abstract "In order to initiate the design process for a new aeroengine, it would be necessary that a matching study beperformed between the aircraft under design and its prospective power plant. In this work wing loading andengine thrust reqiurements are determined. Within this context thrust level is determined for a fighter jet whosemission profile is pre-determined.While the mission profile is being decided upon a typical first-day-of-the-war mission scenario for a newgeneration fighter aircraft is considered. Mission legs were handled individually and the solution space isrestricted by drawing the corresponding constraint curve for each one. A point within the feasible solutionsregion is selected regarding the state-of-the-art. For the determined mission profile the appropriate sea levelthrust 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-offweight as ammunition and 58% of its initial take-off weight as fuel. The overall duration for the mission iscalculated to be 98 minutes." @default.
- W2725037210 created "2017-07-14" @default.
- W2725037210 creator A5010857714 @default.
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- W2725037210 date "2011-01-01" @default.
- W2725037210 modified "2023-10-18" @default.
- W2725037210 title "DETERMINATION OF THE THRUST REQUIREMENT FOR A FIGHTER AIRCRAFT ENGINE VIA MISSION ANALYSIS" @default.
- W2725037210 hasPublicationYear "2011" @default.
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