Aerodynamic Development of a Ground Run-Up Enclosure for Propeller Transport Aircraft
2006; American Institute of Aeronautics and Astronautics; Volume: 43; Issue: 3 Linguagem: Inglês
10.2514/1.16633
ISSN1533-3868
Autores Tópico(s)Aerodynamics and Fluid Dynamics Research
ResumoThe development of a four-sided ground run-up enclosure is described for the Lockheed Martin C-130 Hercules and Fokker 50 as operated by the Royal Netherlands Airforce. The primary goal of the facility is to obtain up to 14 dB(A) noise insertion loss, requiring high sound barrier walls all around the aircraft. Besides, the aircraft operator required the facility to be operational 97% of the time. For Eindhoven airport—the intended building location— this means that the facility must be functional at outside wind speeds up to 21 kn, independent of wind direction. Under these wind conditions the engine torque fluctuations for the C-130 should stay below 2% with maximum takeoff power set on all four engines simultaneously. The paper highlights the aerodynamic design considerations behind the facility and the development and validation in two wind tunnels, the DNW-LST and the DNW-LLF. It is shown that the required overall operational availability has been obtained, despite a small overrun of the torque fluctuation limit for crosswind directions. The design employs a single aircraft line-up direction. Although the facility has been designed in particular for the C-130 aircraft, it could be adapted to fit aircraft like the Boeing 737.
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