Final Report Summary - L-CROR CTS (Low speed aerodynamic test of large CROR aircraft model in a closed test section)
In the framework of the CleanSky project designated with the acronym L-CROR CTS (proposal reference No. 323543 - Call identifier: SP1-JTI-CS-2012-01 - Topic addressed: JTI-CS-2012-1-SFWA-02-028) low-speed aerodynamic test are carried out on a large CROR aircraft model. The test is performed in the closed test section of the DNW-LLF low speed wind tunnel. AIRBUS has designed and manufactured a 1:7 scale model of a future A320 like aircraft with CROR. The test is conducted in August and September of 2012.
Main objectives for the test are as follows:
- Establish a data base in order to obtain handling quality data for an aircraft with two CROR's at the tail section:
i. HTP
ii. elevator
iii. rudder
iv. aileron.
- Measure aero-elastic data for the HTP and VTP.
Project context and objectives:
The test has been performed on a 1:7 scale powered Airbus model. The model has been mounted on the ventral sting and located at tunnel centre line. The powered model has been provided with two sets of counter-rotating propellers (four propellers in total) which are driven by four Airbus owned TPS units (compressed air). At maximum thrust setting the four engines consume about 11 kg/s in total.
The fuselage was provided with the six components b668 main balance for measurement of the overall model forces and moments. To reduce parasitic drive air effects on the main balance, airline bridges RALD2010 and RALD2001 were mounted around the main balance in the air supply respectively air return line. The pressure level in the supply airline bridges was about 80 bar.
The propeller forces and moments were measured with four six components rotating shaft balances (RSBs). The RSB data were acquired and processed inside the model in responsibility of the topic manager.
The test was performed in the 8 m x 6 m closed test section of the DNW-LLF.
Project results:
Scientific results
For the successful execution of the test with the current wind tunnel model, equipped with four highly instrumented propellers a dedicated signal transmission system was developed and made available. Traditional slip ring systems would not have been able to transfer the huge amount of unsteady signals from a rotating system to the data acquisition computers.
Technological results
Performance and handling quality assessment at full span scale in a world class wind tunnel facility of a future single aisle transport aircraft equipped with counter rotating engines.
Potential impact:
The tests have been a substantial (and critical) intermediate step in the development of a new European single aisle transport aircraft. In that respect, the test cleared grounds for the preparation of a first flight of a test aircraft. Furthermore the topic manager now is in a position to assess the efficiency of this new engine concept based on the CROR operating conditions for the tests as carried out.
Dissemination of results has been performed by the topic manager to the SFWA partners as part of WP2245 to validate numerical tools.
Main objectives for the test are as follows:
- Establish a data base in order to obtain handling quality data for an aircraft with two CROR's at the tail section:
i. HTP
ii. elevator
iii. rudder
iv. aileron.
- Measure aero-elastic data for the HTP and VTP.
Project context and objectives:
The test has been performed on a 1:7 scale powered Airbus model. The model has been mounted on the ventral sting and located at tunnel centre line. The powered model has been provided with two sets of counter-rotating propellers (four propellers in total) which are driven by four Airbus owned TPS units (compressed air). At maximum thrust setting the four engines consume about 11 kg/s in total.
The fuselage was provided with the six components b668 main balance for measurement of the overall model forces and moments. To reduce parasitic drive air effects on the main balance, airline bridges RALD2010 and RALD2001 were mounted around the main balance in the air supply respectively air return line. The pressure level in the supply airline bridges was about 80 bar.
The propeller forces and moments were measured with four six components rotating shaft balances (RSBs). The RSB data were acquired and processed inside the model in responsibility of the topic manager.
The test was performed in the 8 m x 6 m closed test section of the DNW-LLF.
Project results:
Scientific results
For the successful execution of the test with the current wind tunnel model, equipped with four highly instrumented propellers a dedicated signal transmission system was developed and made available. Traditional slip ring systems would not have been able to transfer the huge amount of unsteady signals from a rotating system to the data acquisition computers.
Technological results
Performance and handling quality assessment at full span scale in a world class wind tunnel facility of a future single aisle transport aircraft equipped with counter rotating engines.
Potential impact:
The tests have been a substantial (and critical) intermediate step in the development of a new European single aisle transport aircraft. In that respect, the test cleared grounds for the preparation of a first flight of a test aircraft. Furthermore the topic manager now is in a position to assess the efficiency of this new engine concept based on the CROR operating conditions for the tests as carried out.
Dissemination of results has been performed by the topic manager to the SFWA partners as part of WP2245 to validate numerical tools.