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Numerical study of micro-ramp vortex generator for supersonic ramp flow control at Mach 2.5

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Abstract

An implicit large eddy simulation, implemented using a fifth-order, bandwidth-optimized weighted essentially non-oscillatory scheme, was used to study the flow past a compression ramp at Mach 2.5 and \(\text {Re}_{\theta } = 5760\) with and without a micro-ramp vortex generator (MVG) upstream. The MVG serves as a passive flow control device. The results suggested that MVGs may distinctly reduce the separation zone at the ramp corner and lower the boundary layer shape factor. New findings regarding the MVG-ramp interacting flow included the surface pressure distribution, three-dimensional structures of the re-compression shock waves, surface separation topology, and a new secondary vortex system. The formation of the momentum deficit was studied in depth. A new mechanism was observed wherein a series of vortex rings originated from the MVG-generated high shear at the boundary of the momentum deficit zone. Vortex rings strongly interact with the shock-separated flow and play an important role in the separation zone reduction.

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Abbreviations

M :

Mach number

\(\text {Re}_{\theta }\) :

Reynolds number based on momentum thickness

c :

Micro-ramp vortex generator side length

h :

MVG height

\(\alpha \) :

MVG half angle

\(\beta \) :

MVG declining angle of the trailing edge

\(\delta \) :

Incompressible boundary-layer nominal thickness

\(\delta ^{*}\) :

Incompressible boundary-layer displacement thickness

\(\theta \) :

Incompressible boundary-layer momentum thickness

\(H_{\mathrm{i}}\) :

Incompressible boundary-layer shape factor \(\delta ^{*}/\theta \)

x, y, z :

Spanwise, normal and streamwise coordinate axes

u, v, w :

Spanwise, normal and streamwise velocities

\(p_{0}\) :

Pitot pressure

\(C_{\mathrm{Ptot}_{\mathrm{rc}} }\) :

Pitot pressure recovery coefficient

Pr:

Prandtl number

RANS:

Reynolds-averaged Navier–Stokes

LES:

Large eddy simulation

DNS:

Direct numerical simulation

WENO:

Weighted essentially non-oscillatory scheme

TVB:

Total variation bounded

SBLI:

Shock wave boundary layer interaction

VG:

Vortex generator

MVG:

Micro-ramp VG

SWBLI:

Shock-wave boundary layer interaction

w:

Wall

\(\infty \) :

Free stream

0:

Representing the location at the inlet if without special explanation

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Acknowledgments

This work was supported by AFOSR Grant FA9550-08-1-0201 supervised by John Schmisseur and Opening Project of Shanghai Key Laboratory of Multiphase Flow and Heat Transfer in Power Engineering. The authors are grateful to Texas Advantage Computing Center (TACC) for providing computational hours. The authors thank Frank Lu for providing some experimental snapshots.

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Authors and Affiliations

  1. Department of Mathematics, Huston-Tillotson University, Austin, TX, 78702, USA

    Y. Yan

  2. Shanghai Key Laboratory of Multiphase Flow and Heat Transfer in Power Engineering, Shanghai, 200093, China

    Y. Yan

  3. Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing, 100076, China

    L. Chen

  4. State Key Laboratory of Aerodynamics, Mianyang, Sichuan, 621000, China

    Q. Li

  5. Department of Mathematics, University of Texas at Arlington, Arlington, TX, 76019-0408, USA

    C. Liu

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  1. Y. Yan
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  2. L. Chen
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  4. C. Liu
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Correspondence to C. Liu.

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Communicated by A. Hadjadj and A. Higgins.

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Yan, Y., Chen, L., Li, Q. et al. Numerical study of micro-ramp vortex generator for supersonic ramp flow control at Mach 2.5. Shock Waves 27, 79–96 (2017). https://doi.org/10.1007/s00193-016-0633-4

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