Design, Development and Validation of a Cessna Citation X Aerodynamic Model using OpenVSP Software

摘要

This study was done with the intent of studying Morphing Wing benefits on the Cessna Citation X business aircraft. The Morphing Wing regards a technique that aims to replace a conventional wing by a wing able to change its shape during the flight. By morphing, the wing should have better aerodynamic performance than the conventional wing, increases lift forces and reduces drag forces. Consequently, this technique should give excellent performance results with a reduction in the fuel consumption. In order to measure the impact of the Morphing Wing on Cessna Citation X performance, its complete performance model was established. This performance model is composed of two sub-models; an aerodynamic and an engine sub-model. In this paper, only the aerodynamic sub-model is explained. Because of the fact that the project aims to show the benefits obtained from the morphing shape of the wing, the aerodynamic sub-model must emphasize a direct cause-and-effect relationship between a geometrical deformation and a variation in the aerodynamic performance. Accordingly, the aerodynamic sub-model was designed using the aerodynamic solver OpenVSP. OpenVSP is an handy and prompt solver developed by NASA and can be found under NASA Open Source Agreement since 2012. The geometrical shape of the Cessna Citation X (wing, body and vertical-tail) business aircraft was digitized from its 3D drawings. Then, this geometry was provided to OpenVSP, and aerodynamic coefficients computations were done for flight conditions corresponding to the cruise regime (Mach numbers from 0.6 to 0.9). Lift and drag coefficients obtained with OpenVSP have been compared with their experimental values obtained from a Level D Research Aircraft Flight Simulator of the Cessna Citation X, which constitutes a reliable source.