Developing an Aircraft Propeller Model for Real-Time Implementation

Abstract

In this thesis, a real-time capable propeller model based on blade element momentum theory is developed to predict the thrust and torque loads experienced by an aircraft in different environment conditions and flight maneuvers. The progressing landscape of aerospace engineering demands a high fidelity propeller model that accurately and efficiently predicts the propeller performance during different flight conditions. An indispensable application of the developed propeller model is to capture any design flaws earlier during the development phase so as to rectify them before the flight test or production of the actual aircraft. Furthermore, it allows the engineers to assimilate the data and outcomes of the simulations that are physically not achievable or very challenging in nature. The outcomes of the propeller model has the capability to facilitate the selection of a suitable kind and size of propellers for a particular aircraft. Software tests are carried out for the developed software library underpinning the propeller model. Strategies to enhance the code performance are implemented and investigated. Validation of the developed model is carried out with respect to the available experimental data in order establish its credibility and commend its ability to imitate real-world scenarios. The model is adapted to deliver real-time results, thereby sustaining the model based development and paving the way for future enhancements in aircraft design.