CODE-TILT

CONTRIBUTION TO DESIGN OPTIMIZATION OF TILTROTOR COMPONENTS FOR DRAG REDUCTION

Reference: 270609

Call: SP1-JTI-CS-2010-01

Scientist: Ernesto Benini

Department: Industrial Engineering

UNIPD: coordinator

Total cost: 849,600 €

Eu Funding: 670,500 €

Email: ernesto.benini@unipd.it

Project Description

Objectives. This proposal describes a methodology to be used for efficient optimization aimed at drag reduction of some components of a tiltrotor fuselage, i.e. nose, wing/fuselage junction, sponsons and tail surfaces. Specific objectives of such activity are to:

  1. set up a comprehensive and automatic design tool, integrating the software in use at the GRC Consortium and an in-house optimizer already developed by the applicants;
  2. implement efficient and robust optimization strategies for obtainment of optimal geometries using reasonable computing time;
  3. implement, test and run such tool within the industrial design procedure currently available at the GRC Consortium;
  4. apply such tool for drag reduction of the above mentioned components in order to improve the overall aircraft aerodynamic efficiency, while guaranteeing compliance with industrial constraints and needs.

Methodology. Objectives i) and iii) will be achieved by means of a dedicated programming activity where the software tools will be integrated together and with the proprietary optimization tool by the applicants. This will result in a procedure where geometrical and grid manipulation, as well as CFD analyses will form an automaticloop.Objective ii) will be guaranteed by the capability of the optimizer to handle complex multiobjective problems; the optimization chain will be conceived in such a way that the user can interact with the optimizer and monitor the whole process as it takes place. Objective iv) will be pursued mainly by means of shape modifications for drag reduction, but, due to the product oriented character of this activity, also complementary techniques (i.e. riblets, vortex generators, Hybrid Laminar Flow Control, gaster bump, sweeping jets, winglets, wing strakes, upper surface spoilers) may be considered and discussed with the leading industry, if a pure numerical shape optimization would lead to unfeasible solutions with respect industrial constraints.  

Partners

Coordinator: Università degli Studi di Padova

Participants: HIT09 Srl