Verification and testing

The RBF4AERO Benchmark Technology (WP2) brings into the aircraft engineering design novel numerical strategies and approaches introducing clear elements of innovation. As such, it needs to implement an accurate verification and testing effort in order to evaluate its capabilities and its actual applicability to the design optimization phase. In the RBF4AERO project, this objective will be achieved by pursuing two different pilot lines:

  1. verification of RBF4AERO optimization approach against documented low- and medium-size computational models (WP4);
  2. testing of RBF4AERO optimization performances against real case applications of industrial  use (WP5).

The background knowledge from End Users as well as experimental data available on literature and produced within the project (WP3) will be exploited for these evaluations.


The verification of RBF4AERO Benchmark Technology is the first step to demonstrate the effectiveness and reliability of the numerical optimization procedure. The verification activities will be accomplished by Project partners at their remote developing platforms.

In particular, the proposed numerical procedures will be tested on literature reference cases as well as on computational models already implemented by Consortium partners. In the verification task a first set of studies will be carried out concerning the following test cases:

  • 2D airfoil design;
  • 3D airfoil design;
  • DLR-F6;
  • Turbine blade cooling optimization;
  • Wing root-body blending on a glider;
  • Small aircraft underwing nacelle;
  • Aircraft propeller optimization.

The complementary scope of the verification activities is the effective support to the Benchmark Technology development through the use of its most advanced functionalities in view of characterizing its usability and helping in the bug tracking and fixing.



The testing of RBF4AERO Benchmark Technology aims at demonstrating the effectiveness and applicability of the methodology to the aircraft design and optimization analyses using computational models with a size suitable for industrial purpose.

The testing phase will be mainly performed by project’s End Users that are expected to operate on their own computational infrastructures through their CAE tools and carry out real test case applications.

Considering testing targets, the complexity of analysed models will be increased in relation to the multidisciplinary of the numerical investigations (aerodynamics, structure, thermal, acoustics, etc) as well as in the accuracy of such models.

Furthermore the performance of the Benchmark Technology in terms of time savings and results accuracy will be demonstrated.

Optimizations studies at the highest level of complexity will be carried out on well detailed 3D test case geometries. In particular, the following applications will be considered:

  • Payload Fairing;
  • Cooling optimization;
  • Mid-size business jet;
  • Subsonic vehicle winglet;
  • Turboprop engine exhaust system;
  • New small-size aircraft configuration optimization.

The obtained numerical results will support, and in turn will be supported by, the experimental testing activities. This comparative investigation will deal with three specific applications:

  • Low Pressure Turbine (LPT) stage optimization;
  • Optimization of a Contra-Rotating Open Rotor (CROR);
  • Turbine Internal Cooling (TIC).

In this context of the Project, experimental results will be compared with numerical results of the optimal morphed configuration and the numerical analyses will produce the optimal solution to be manufactured and tested.