Abstract
The flying-wing aircraft is a promising concept for the mid or long-term commercial aviation due to its excellent performance in aerodynamic and structure, which has been studied by a number of investigators both experimentally and computationally. However, the conditions in wind-tunnel testing do not necessarily reflect those observed in free flight, the support structure interference is an important factor to affect experimental data collected from wind tunnels. Support interference characteristics of a flying-wing model from subsonic to supersonic speed is investigated by numerical simulation methods. Results show that grid convergence is obtained with the series of grids, which implies that the solutions are in the asymptotic range. The support has a relatively small effect on aerodynamic characteristics of flying-wing aircraft at low speed while has a relatively large effect on drag at transonic speed and supersonic speed.
Export citation and abstract BibTeX RIS
Content from this work may be used under the terms of the Creative Commons Attribution 3.0 licence. Any further distribution of this work must maintain attribution to the author(s) and the title of the work, journal citation and DOI.