Abstract
This paper serves as a summary of our recent work on LES for supersonic MVG. An implicitly implemented large eddy simulation (ILES) by using the fifth‐order WENO scheme is applied to study the flow around the microramp vortex generator (MVG) at Mach 2.5 and Re θ = 1440. A number of new discoveries on the flow around supersonic MVG have been made including spiral points, surface separation topology, source of the momentum deficit, inflection surface, Kelvin‐Helmholtz instability, vortex ring generation, ring‐shock interaction, 3D recompression shock structure, and influence of MVG decline angles. Most of the new discoveries, which were made in 2009, were confirmed by experiment conducted by the UTA experimental team in 2010. A new 5‐pair‐vortex‐tube model near the MVG is given based on the ILES observation. The vortex ring‐shock interaction is found as the new mechanism of the reduction of the separation zone induced by the shock‐boundary layer interaction.
Highlights
It is well known that for the supersonic ramp jet flow, shock boundary layer interaction (SBLI) can significantly degrade the quality of the flow field by triggering largescale separation, causing total pressure loss, making the flow unsteady and distorted, and can even make an engine unable to start
In order to improve the “health” of the boundary layer, a series of new devices named as micro vortex generator is designed for flow control, which is with a height approximately 20–40% of the boundary layer thickness
The mechanism of microramp vortex generator (MVG) flow control from his work was described as that a pair of counter-rotating primary streamwise vortices is generated by MVG, which is mainly located within the boundary layer and travel downstream for a considerable distance
Summary
It is well known that for the supersonic ramp jet flow, shock boundary layer interaction (SBLI) can significantly degrade the quality of the flow field by triggering largescale separation, causing total pressure loss, making the flow unsteady and distorted, and can even make an engine unable to start. The mechanism of MVG flow control from his work was described as that a pair of counter-rotating primary streamwise vortices is generated by MVG, which is mainly located within the boundary layer and travel downstream for a considerable distance. An implicit LES for MVG to control the shock-boundary layer interaction around a 24 degree ramp at Mach number of 2.5 and Reynolds number of 1440 has been carried out in 2009 [12]. The new findings include (1) spiral points and flow topology around MVG, (2) new theory of five pairs of vortices near MVG, (3) origin of momentum deficit, (4) inflection points (surface for 3D) and Kelvin-Helmholtz- (KH-) type instability, (5) vortex ring generation, (6) ringshock interaction and separation reduction, (7) 3D recompressed shock structure, and (8) effects of trailing-edge decline angles.
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