PSE and Spatial Biglobal Instability Analysis of HIFiRE-5 Geometry

Kocian, Travis S.; Moyes, Alexander; Mullen, Charles D.; Reed, Helen L.

doi:10.2514/6.2016-3346

Cited by 5 publications

(3 citation statements)

References 9 publications

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“…Transition in high-speed boundary layers and stability analysis techniques Previous studies of transition to turbulence in high-speed boundary layers have spanned laboratory experiments (Demetriades 1960;Kendall 1975;Kosinov, Maslov & Shevelkov 1990;Schneider 2001;Laurence et al 2012;Parziale, Shepherd & Hornung 2015) and flight data (Schneider 1999;Kimmel & Adamczak 2017). Numerical efforts included various levels of fidelity, such as direct numerical simulations (Guarini et al 2000;Martin 2007;Li, Fu & Ma 2010), large-eddy simulations (Yan, Knight & Zheltovodov 2002;Grilli, Hickel & Adams 2013;Chen et al 2017;Nichols et al 2017) and parabolized stability equations (Oliviero et al 2015;Kocian et al 2016). Furthermore, high-speed transition has been investigated over various geometries including flat plates (Graziosi & Brown 2002;Joo & Durbin 2012), cones (Germain & Hornung 1997;Balakumar & Owens 2010;Ward et al 2012;Sivasubramanian & Fasel 2015) and realistic flight-vehicle geometries (Schneider 2006).…”

Section: Introductionmentioning

confidence: 99%

Sensitivity of high-speed boundary-layer stability to base-flow distortion

Park

Zaki

2018

J. Fluid Mech.

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The linear stability of high-speed boundary layers can be altered by distortions to the base velocity and temperature profiles. An analytic expression for the sensitivity is derived for parallel and spatially developing boundary layers, the latter using linear parabolized stability equations and their adjoint. Both the slow mode, S, and the fast mode, F, are investigated at Mach number 4.5. The mode S is more sensitive with respect to distortion in base velocity than in base temperature. The sensitivity is largest within the boundary layer away from the wall. Near the critical layer, where the phase speed of the mode equals the base streamwise velocity, the sensitivity to the base streamwise velocity is negative. For the mode F, there is a discontinuous jump in the sensitivity when the phase speed is below unity, and a critical layer is established. The sensitivity of the two modes increases with the Reynolds number, but there is a sudden drop and a jump in the sensitivities of the modes S and F, respectively, near the synchronization point where the phase speeds of the two modes are equal. Furthermore, the maximum uncertainty bounds are obtained for the distorted base state that maximizes the destabilization or stabilization of the modes by solving the Lagrangian optimization problem for the sensitivity. The sensitivity of the flow stability to surface heating is then studied, and changes in growth rate and the$N$-factor are evaluated. The formulation provides a clear physical interpretation of these changes, and establishes uncertainty bounds for stability predictions for a given level of uncertainty in wall temperature.

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Section: Introductionmentioning

confidence: 99%

Sensitivity of high-speed boundary-layer stability to base-flow distortion

Park

Zaki

2018

J. Fluid Mech.

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“…Second mode has been observed to be particularly sensitive to acoustic freestream disturbances typical of hypersonic facilities. As discussed above, the quiet flow, Re = 11.8 × 10 6 /m computations of Kocian et al (2016) showed initial growth of second mode instabilities that is overtaken by the nonlinear effects of the stationary vortices and their secondary instabilities. It could be that in the presence of elevated freestream disturbances this second mode instability is stronger in its interaction with the developing stationary crossflow leading to this earlier breakdown and diffuse front observed.…”

Section: Within the Ace Facilitymentioning

confidence: 67%

“…The TAMU Computational Stability and Transition Lab has conducted several studies which are relevant for comparison to the present results. In analysis similar to that of Moyes et al (2017) for the right-circular cone under hypersonic conditions, Kocian et al (2016) and Kocian et al (2017) present stability analysis for the crossflow dominated shoulder region of the 2:1 elliptic cone HIFiRE-5 geometry. speed experiments in that increased initial amplitude lead to earlier saturation of stationary waves and decreased the saturation disturbance amplitude.…”

Section: Computational Resultsmentioning

confidence: 97%

Influence of Environmental Disturbances on Hypersonic Crossflow Instability on the HIFiRE-5 Elliptic Cone

Neel

Leidy

Tichenor

et al. 2018

2018 AIAA Aerospace Sciences Meeting

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Crossflow instabilities on a 2:1 elliptic cone in hypersonic flow have been investigated in the M6QT and ACE wind tunnels at the Texas A&M National Aerothermochemistry and Hypersonics Laboratory. Experiments on a PEEK 38.1% scale model of the HIFiRE-5 flight test geometry were conducted to investigate the development of crossflow instabilities as well as to characterize the freestream and surface conditions responsible for their initial amplitudes. The freestream environment was varied not only by testing the model in both quiet and conventional tunnels but also by passively changing the fluctuation levels experienced in the conventional facility through systematic model placement. ACE freestream measurements, using a Kulite pressure transducer mounted in a pitot probe configuration and a hot-wire anemometer, indicated that fluctuation levels at the upstream model station were half those at the downstream stations. Fast-response PCB and Kulite surface mounted pressure transducers allowed examination of pressure fluctuation amplitudes and

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