Inlet as part of aircraft engine plays important role in controlling the rate of airflow
entering to the engine. The shape of inlet has to be designed in such away to make the
rate of airflow does not change too much with angle of attack and also not much
pressure losses at the time, the airflow entering to the compressor section. It is therefore
understanding on the flow pattern inside the inlet is important. The present work
presents on the use of the Fourth Order Runge Kutta – Harten Yee TVD scheme
for
the flow analysis inside inlet. The flow is assumed as an inviscid quasi two dimensional
compressible flow. As an initial stage of computer code development, here uses three
generic inlet models. The first inlet model to allow the problem in hand solved as the
case of inlet with expansion wave case. The second inlet model will relate to the case of
expansion compression wave. The last inlet model concerns with the inlet which
produce series of weak shock wave and end up with a normal shock wave. The
comparison result for the same test case with Fluent Software
[1, 2]
indicates that the
developed computer code based on the Fourth Order Runge Kutta – Harten – Yee TVD
scheme are very close to each other. However for complex inlet geometry, the problem
is in the way how to provide an appropriate mesh model