论文信息 - Shock Control Bumps on Flexible and Trimmed Transport Aircraft in Transonic Flow

Shock Control Bumps on Flexible and Trimmed Transport Aircraft in Transonic Flow

Shock control bumps are a means to reduce wave drag that occurs at the upper limit of civil transport aircrafts flight envelope. An SCB was optimized for and applied to the rigid wing-body DLR F11 model. The effect of the SCB on the trim drag of the F11 configuration with an attached horizontal tail plane was investigated. Flexibility of the wing-body model was considered and the influence of aeroelasticity on the SCB performance was examined. RANS simulations with the DLR FLOWer code showed, that both the influence of trimming as well as of aeroelasticity is negligible for SCB design.

Ewald Krämer | Thorsten Lutz | Benedikt Konig | Martin Pätzold

[1] Norbert Kroll,et al. MEGAFLOW - A Numerical Flow Simulation Tool For Transport Aircraft Design , 2002 .

[2] Siegfried Wagner,et al. Parallel Numerical Optimisation of Adaptive Transonic Airfoils , 2003 .

[3] Siegfried Wagner,et al. Investigations on Shock Control Bumps for Inflnite Swept Wings , 2004 .

[4] E. Stanewsky. Drag reduction by shock and boundary layer control : results of the project EUROSHOCK II, supported by the European Union, 1996-1999 , 2002 .