Abstract
In this paper, a code is developed in C++ programming language aiming to select and introduce a well-chosen propulsion system for appropriate operation in an aircraft. By using a suitable turbocharged engine, the inlet pressure of the engine manifold will increase to a level equal to the pressure at sea level. Therefore, the aircraft engine will not notice the drop of pressure caused by the increase in altitude. Consequently, the engine power will not be reduced. On the other hand, at high altitude, using only one turbocharger is not adequate to supply engine inlet pressure and flow rate equivalent to sea level conditions, requiring the use of more turbochargers. The code developed in this study will be able to introduce the appropriate turbocharged engine based on the flight altitude and the required power engine of an air vehicle. The altitude defined in this code ranges from 5 to 30 kilometers, which leads to a selection of one to three turbochargers plus a number of intercoolers, according to user input parameters. The objective function of this optimization problem is defined as a function of turbochargers efficiency. However, this objective function can be modified according to the user requests and requirements.
Highlights
The quest of achieving high flight altitudes for an aerial vehicle has always been pursued by diverse researchers
To display the functionality of the code in different flying altitudes, the code outputs will be presented for three of them, which correspond to the use of one, two, and three turbochargers, respectively
The code output introduces the best turbocharger for the flight altitude supplying the power required by the user
Summary
The quest of achieving high flight altitudes for an aerial vehicle has always been pursued by diverse researchers. Regardless of the aircraft type, it is important to choose an appropriate propulsion system to provide the required power for desired flight altitude. Air breathing engines require a sufficient amount of air intake to perform desirably. The engine power will be reduced, preventing the aircraft from achieving higher flight altitudes. The maximum power of an air breathing engine is only available while operating at sea level and, by increasing the flight altitude, this power will be continuously reduced, such that, from a certain altitude on, there will not be sufficient amount of air for engine combustion process. The desirable engine performance will not be attainable at high altitudes. One is not able to exceed a certain altitude while employing only a single specific engine, once it is associated with air pressure
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