The design of the winglets for BLOODHOUND SSC began by applying the simple lifting line theory model to establish the approximate wing size required for the estimated loading. The previous experience, gained with Thrust SSC accelerating to supersonic speed, showed that maintaining a constant vertical loading on the vehicle is very challenging, if not impossible, without the use of movable aero-surfaces. The rapid transients in forces and moments that are produced will require contributions from the winglets, to ensure that the front and rear wheel loadings remain within prescribed bounds. When the approximate wing area had been established, wings of simple shape were employed in the full vehicle CFD simulations. As the behaviour of the full vehicle was better understood, it was possible to more accurately describe the workload necessary from the winglets.

 

The winglets have a symmetric cross section, as they may be required to generate both positive and negative vertical loads, a 30^o leading edge sweep, to minimise wave drag, an aspect ratio of 2:1 and a taper of 50%, implying that the tip chord length is half that of the root chord. The lift and drag response of these wings was then analysed in order to fix the front and rear winglet areas. As of September 2008, these parameters are still to be finalised and will form a basis for pre-programming their actuation for running BLOODHOUND SSC.

 

BLOODHOUND Design   Engine Intake Design   Wheel Design   Nose Design   Base Drag   Winglet Design   Vehicle Sensitivity Analysis