Rolling Motion of a Delta Wing

Vortex breakdown is a sensitive aerodynamic phenomenon that was used to investigate the need for closely coupled flight simulation. The DLR Aerosum delta wing has been used for validation studies for fixed, forced rolling and free-to-roll cases. The wing was fitted with trailing edge flaps. The flap deflections were then used to generate roll responses. In the closely coupled simulation asymmetric vortex breakdown allowed a non-zero trim point to be found when the flap were returned to the undeflected. These trim points were not found found for motion simulation using conventionally derivative type aerodynamic models calculated from forced CFD simulations.


  1. Arthur, M.T., Allan, M., Ceresola, N., Kompenhans, J., Fritz, W., Boelens, O.J. and Pranata, B.B. (2005) Exploration of the Free Rolling Motion of a Delta Wing Configuration in a Vortical Flow. RTO-MP-AVT-123. NATO RTO, Hungary
  2. Boelens, O.J., Prananta, B.B., Soemartwoto, Allan, M.R., Badcock, K.J. and Fritz, W. (2005) Towards an aero-servo-elastic simulation capability for high performance fighter aircraft. RTO-MP-AVT-123. NATO RTO, Hungary

4flight_flapmotiondl.jpg (193kB)

4flight_rollpressuredl.jpg (48kB)

Flap Motion

Roll Response and Surface Pressure


Contact: Ken Badcock