JoKHeR: NPSE Simulations of Hypersonic Crossflow Instability

Kuehl, Joseph; Pérez, Eduardo; Reed, Helen L.

doi:10.2514/6.2012-921

Cited by 38 publications

(22 citation statements)

References 18 publications

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“…2 (upper panels) for three different-frequency second modes (234, 285, and 345 kHz, respectively), along with homogeneous base flow acoustic impedance (dashed lines), and dimensional linear-stability-theory calculated growth rates (per meter) as a function of frequency (bottom panel). The LST code used is that based on an updated version of the JoKHeR nonlinear parabolized stability equations code [38,39]. LST eigenmodes are calculated 35 cm from the cone tip in a frequency range from 235 to 345.…”

Section: Confirmation Of Energy Sourcementioning

confidence: 99%

Thermoacoustic Interpretation of Second-Mode Instability

Kuehl

2018

AIAA Journal

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A thermoacoustic interpretation of Mack's second-mode instability is proposed. It is demonstrated that the fundamental mechanism of second-mode wave growth in hypersonic boundary layers is consistent with standingwave thermoacoustically driven instability. The resonant nature of such modes is sustained by an acoustic impedance well between the wall (infinite impedance) and near the sonic line (secondary peak in impedance). A Lagrangian approach is adopted to show that such resonant standing waves derive energy from the base flow through thermoacoustic Reynolds stress, which results from the divergence of acoustic power inside the impedance well, and thermodynamic work. This treatment does not represent a complete energy closure (due to the neglect of viscosity), but it does provide insight toward a fundamental energy source and the physical mechanisms governing Mack's acoustic second mode.

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Section: Confirmation Of Energy Sourcementioning

confidence: 99%

Thermoacoustic Interpretation of Second-Mode Instability

Kuehl

2018

AIAA Journal

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“…Numerous efforts 1,4,6,9,12,18,23,25,28,29,[30][31][32][33][34][35] have provided insight into the stability and transition of such systems, though as a testimony to the complexity of the problem, considerable uncertainty still exists. Other 3-D geometries such as the elliptic cone have also provided insight 18,[36][37][38][39][40][41][42][43] .…”

Section: Geometrymentioning

confidence: 99%

“…Furthermore, experiments in the Braunschweig facility 1 have measured first-and second-mode instabilities on regions of a yawed straight cone usually associated with crossflow. These examples motivate the need for development and application of nonlinear parabolized stability equation (NPSE) tools [20][21][22][23][24][25] .…”

Section: Introductionmentioning

confidence: 99%

Instabilities on a Hypersonic Yawed Straight Cone

Pérez

Reed

Kuehl

2013

43rd Fluid Dynamics Conference

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Our current activities focus on providing linear and nonlinear parabolized stability equation analysis of the hypersonic crossflow and second-mode instability over a 7˚-halfangle yawed straight cone. A study is conducted to complement the experiments at Mach 6 in the Hypersonic Ludwieg Tube at Braunschweig 1 . Multiple instabilities can be simultaneously present in a 3-D boundary layer. For azimuthal angle 70° and x=0.36 m, analysis following Mack 2 suggests that the low-frequency disturbances observed are related to traveling crossflow. Simultaneously, a second mode is predicted with frequency range well predicted by LPSE.

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“…It has been shown previously on a slender cone at angle-of-attack that crossflow disturbances travel along the direction of the velocity vector located at the inflection in the crossflow profile. 4 In the present work streamtraces were calculated by extracting the velocity vector located at the inflection of the crossflow generalized momentum profile. The generalized momentum profile is chosen over the velocity profile to account for possible density gradients in the boundary layer.…”

Section: Resultsmentioning

confidence: 99%

Analysis of Crossflow Instability on HIFiRE-5 using Direct Numerical Simulation

Dinzl

Candler

2015

53rd AIAA Aerospace Sciences Meeting

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Direct Numerical Simulation is being used to study crossflow instabilities on the Hypersonic International Flight Research Experimentation program flight 5 vehicle. The simulations replicate a 38.1% scale model at the 1090 kPa flight conditions used for experiments at the Boeing/AFOSR Mach 6 Quiet Tunnel. In this paper special attention is given to the development of a baseflow for the problem. Due to the extreme sensitivity of crossflow instability, disturbances are seeded very easily and can pollute the baseflow. Several computations designed to limit this phenomenon while still resolving the mean flow physics are presented. A simulation of a quarter of the HIFiRE-5 forebody with 216 million elements is being performed. Once completed, the development and breakdown of crossflow vortices will be analyzed, with attention given to spanwise wavenumber evolution, nonlinear interaction and modification of the mean flow, and the fostering of secondary instabilities.

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JoKHeR: NPSE Simulations of Hypersonic Crossflow Instability

Cited by 38 publications

References 18 publications

Thermoacoustic Interpretation of Second-Mode Instability

Thermoacoustic Interpretation of Second-Mode Instability

Instabilities on a Hypersonic Yawed Straight Cone

Analysis of Crossflow Instability on HIFiRE-5 using Direct Numerical Simulation

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