تلخیص
Shock/shock and shockwave/ boundary layer
interactions are important features of hypersonic flow fields.
These features commonly motivate a considerable region of
separation followed by reattachment. The pressure loads
produced by the shock/shock and shock wave/ boundary layer
interactions and the high heating loads encountered at
reattachment play a significant role in control surface
effectiveness and structural integrity of the hypersonic vehicle.
Consequently, CFD tools are under improvement for predicting
the details of such complex flows, combined with validating
experiments and verifying against basic theoretical relations. In
present studies, complex hypersonic flow test cases, namely,
compression corner, backward step, and double cone, containing
shock/shock and shock wave/ boundary layer interactions are
solved by using two different schemes, namely, TVD and low
dissipative high resolution artificial compression methods (ACM).
Comparison of numerical results against the available
experimental data shows that the low dissipative, high resolution
ACM provides better results than the TVD scheme. Separation
vortex size calculated by low dissipative high resolution ACM
method is larger than the size of the separation vortex calculated
by the TVD scheme, depicts that the low dissipative high
resolution ACM method induces less numerical dissipation and
therefore more appropriate for complex shock/shock and shock
wave/ boundary layer interactions flows.
Dr. Mukkarum Husain, Dr. Chun Hian Lee. (2012) Numerical Simulation of Complex Hypersonic Flows, Journal of Space Technology , Volume 2, Issue 1.
-
Views
574 -
Downloads
39
اگلا مقالہ