A new type of TVD schemes for computations of high speed flows

Lee, C. H.; Chu, Yantao

doi:10.2514/6.1993-2773

Cited by 5 publications

(5 citation statements)

References 3 publications

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“…The computational domain for the TVD calculations starts at x = À0.006 m and ends at a very short distance downstream of the leading edge at x = 0.003 m. A total 241 Â 121 grid points are used. A TVD scheme, which follows that used by Lee et al [52], is applied to Eq. (12).…”

Section: Two-dimensional Hypersonic Viscous Flow Over a Flat Plat Witmentioning

confidence: 99%

A high-order cut-cell method for numerical simulation of hypersonic boundary-layer instability with surface roughness

Wang

Zhong

2010

Journal of Computational Physics

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Section: Two-dimensional Hypersonic Viscous Flow Over a Flat Plat Witmentioning

confidence: 99%

A high-order cut-cell method for numerical simulation of hypersonic boundary-layer instability with surface roughness

Wang

Zhong

2010

Journal of Computational Physics

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“…But in the leading edge region of the flat plate, there is a singularity at the tip of the plate and the high-order shock fitting method cannot be used there. Thus a second-order total variation diminishing (TVD) shock-capturing method, which follows that used by Lee et al [19], is employed to calculate a small local flow field around the tip of the flat plate. In actual simulations, the computational domain is divided into 30 zones, with total of 5936 grid points in the streamwise direction and 121 points in the wall-normal direction.…”

Section: B Steady Flow Solution Without Surface Roughnessmentioning

confidence: 99%

Finite roughness effect on modal growth of a hypersonic boundary layer

Fong

Wang

Zhong

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Numerical simulation of roughness effect on modal growth is conducted on a hypersonic flat-plate at Mach 5.92. The steady base flow is firstly simulated by solving compressible Navier-Stokes equations. Stability characteristics of boundary-layer waves are analyzed by linear stability theory (LST). In stability simulations, two-dimensional disturbances corresponding to mode S or mode F at a frequency of 100 kHz are introduced near the leading edge of the flat-plate. Roughness with adjustable height is placed into four locations with respect to the disturbance synchronization point. It is found that upstream of synchronization point, disturbance is amplified by roughness with a stronger strength for taller roughness. On the other hand, disturbance is damped when the roughness is placed at or downstream of synchronization point. Different from upstream cases, tall roughness damps disturbance instead of amplifying it. We believe the relative location of synchronization point and roughness is a candidate to explain roughness delay transition as previous experiments have shown. Our results also show that roughness effect on mode S and mode F are very alike. In addition, a disturbance with a wide bandwidth is planned and will be imposed in the future.

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“…It started from a modification of the flux in the conservation law, and employed a first order scheme to discretize the modified flux to yield the second order TVD scheme. After Harten's work, series of TVD schemes such as Sweby's, Yee's, etc., were developed [2][3][4][5][6][7][8]. Due to the high resolution capability in capturing shock waves, TVD schemes have been widely used in compressible flow simulations.…”

Section: Introductionmentioning

confidence: 99%