The streamwise lift distribution of a wing-canard-stabilator-body model was varied to study its effect on the near-field sonic boom signature. The investigation was carried out via solving the three-dimensional Euler equation with the OVERFLOW-2 flow solver. The computational meshes were created using the Chimera overset grid topology. The lift distribution was varied by deflecting the canard, then trimming the aircraft with the wing and the stabilator while maintaining a constant lift coefficient of 0.05. A wide range of streamwise lift distributions was simulated. The results show that the relative longitudinal wave propagation speed can be controlled through lift distribution, thus controlling the shock coalescence and sonic boom signature. In addition, validation studies of the computational tools were performed using a wing-body model and the results were compared against the wind-tunnel experimental data. The same model was also used to perform the grid resolution and numerical scheme comparison study.
Analysis of the Effects of Streamwise Lift Distribution on Sonic Boom Signature
Journal of Aircraft ; 50 , 2 ; 354-359
2013-01-25
6 pages
Article (Journal)
Electronic Resource
English
Analysis of the Effects of Streamwise Lift Distribution on Sonic Boom Signature
Online Contents | 2013
|Analysis of the Effects of Streamwise Lift Distribution on Sonic Boom Signature
British Library Conference Proceedings | 2010
|Analysis of the Effects of Streamwise Lift Distribution on Sonic Boom Signature
Online Contents | 2013