The purpose of this research is the conceptual implementation of the actual suction profile on the wing of the airplane. The suction profile generated using numerical study and optimisation for the airfoil is based on the assumption of continuous suction over the wing. In order to fulfil this suction profile all the non-ideal effects need to be quantified. These non-ideal effects arises due to the following factors
- Discrete nature of suction through the porous sheet and interplay of hole generated vortices.
- Pressure loss in the porous sheet and the internal duct system.
The following are the specific objectives and approaches for the 4 years of this project:
- To design the requirements on skin porosity based on the internal and external flow data, transition location, and N factor.
- Pressure loss through different porous sheets are calculated using flow bench, wind tunnel experiments and numerical correlations. A comparison is made, between two different manufacturing methods namely: - Micro laser drilling and 3D printing, to quantify the effect of quality of holes. The 3D printed samples are manufactured in coordination with B3.2 research group.
- To design and characterize the internal suction structure for a wing with suction system.
- Different conceptual designs for the internal core structure are compared experimentally and analytically. Suitable designs are selected that can support the load and provide pressure variation along the chord necessary to maintain the suction velocity. The panels to perform flow bench experiments are manufactured in close cooperation with research group B3
- To formulate reduced order models for 1) internal design of the suction: internal flow data as function of the inner structure of the suction box, 2) aerodynamic performance of the wing with suction BL.
- o Calculation of power to drive the suction system and efficiency of the suction system based on the overall drag reduction.
