02.2 - Experimental Aerodynamics
INLET DUCT ENGINE TEST FACILITIES IN INDONESIA LOW SPEED TUNNEL (ILST)
S. Subagyo, BBTA3-BPPT, Indonesia
Designing activities covering various aspects of fighter aircrafts are very complex such as aircraft airframe, propulsion system, anti-radar, the problem of structure and materials used. In this paper the author examines the field of propulsion-related air intake inlet. In the area of the inlet piping support incoming airflow to the engine driving the aircraft is a fairly important part. The development forms the inlet piping is also an influence on aircraft flying at Mach number range from 0.3 to 2. Requirements to be met are a form of air inlet piping providers so that the pressure recovery closes to 100% and the value of the Aerodynamic pressure distortion Plane Interface (AIP). Tests prepared on measuring the inlet piping using pressure measurement techniques. There are two types of facilities were assessed for testing aircraft Engine Inlet Duct. The first is based on the numerical simulation techniques with commercial code computational fluid dynamics and the second with air injection technique with the desired flow rate. The study showed that the facilities can be applied in Indonesia Low Speed Tunnel (ILST) for testing in subsonic regime.