Overview
The noise shielding empennage designs for rear fuselage mounted engines are promising enough to further investigate. Significant noise reduction is one of the main goals of the Clean Sky Smart Fixed Wing Aircraft (SFWA) project.
In order to determine the merits of several alternative designs, extensive wind tunnel testing with enhanced state-of-the-art measuring techniques will be performed.
Tests will be performed on full model with engine jet simulation. Several types of empennages will be tested in order to assess the noise shielding merits of these innovative designs. The acoustic tests will be done in the 8mx6m open test section of DNW-LLF. Furthermore, the aerodynamic interaction of the empennage with the jet exhaust will be tested with the full model in the 8mx6m closed test section, with and without ground effect.
Funding
Results
Final Report Summary - PLAAT (Aeroacoustic and aerodynamic wind tunnel tests at low speed for a turbofan model equipped with TPS)
Executive Summary:
In the framework of the CleanSky project designated with the acronym PLAAT (Proposal reference number: 326011 - Call identifier: SP1-JTI-CS-2012-02 - Topic addressed: JTI-CS-2012-02-SFWA-02-031) low-speed aerodynamic tests were carried out on a typical business jet aircraft model, designated as the LOSPA model. The tests were performed in the closed 8 m x 6 m test section and the open jet test section of the DNW-LLF low-speed wind tunnel. The LOSPA model can be equipped with a conventional cross-tail or a U-shaped tail. Furthermore the model can be equipped with powered (compressed air) engine simulators, provided by DNW and ONERA. The tests were conducted in December of 2014 and March/April of 2015.
Project Context and Objectives:
In the framework of the CleanSky project designated with the acronym PLAAT (Proposal reference number: 326011 - Call identifier: SP1-JTI-CS-2012-02 - Topic addressed: JTI-CS-2012-02-SFWA-02-031) low-speed aerodynamic tests were carried out on a typical business jet aircraft model, designated as the LOSPA model. The tests were performed in the closed 8 m x 6 m test section and the open jet test section of the DNW-LLF low-speed wind tunnel. The LOSPA model can be equipped with a conventional cross-tail or a U-shaped tail. Furthermore the model can be equipped with powered (compressed air) engine simulators, provided by DNW and ONERA. The tests were conducted in December of 2014 and March/April of 2015.
The main objectives for the tests were as follows:
Aerodynamic test
- Check the aerodynamic interaction of various tail configurations with the engine jet exhaust tested with the full model in the 8mx6m closed test section, with and without ground effect.
Aero-acoustic test
- acoustic reference measurements on an isolated powered engine simulator
- airframe noise measurements on the unpowered LOSPA aircraft model
- acoustic efficiency measurements with a single powered engine simulator installed on the LOSPA aircraft model (D3.1/WP3.4)
Project Results:
Obtained data about the aerodynamic and aero-acoustic characteristics of a newly developed U-tail, acoustic measurements and propulsion simulations are successfully combined.
Combined aerodynamic and aero-acoustic measurements in a large low speed environment performed on a business jet model.
Potential Impact:
The tests formed a critical step in the development of future business jet aircraft and the design rules of engine over horizontal tail configurations.