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Boundary-layer instabilities for a finned cone at Mach=6, $Re=8.4 \times10^6$ [m$^{-1}$], and zero incidence angle are examined using linear stabilitymethods of varying fidelity and maturity, following earlier analysis presentedin [doi.org/10.2514/6.2022-3247]. The geometry and laminar flow conditionscorrespond to experiments conducted at the Boeing Air Force Mach 6 Quiet Tunnel(BAM6QT) at Purdue University. Where possible, a common mean flow is utilizedamong the stability computations, and comparisons are made along the acreage ofthe cone where transition is first observed in the experiment. Stabilityresults utilizing Linear Stability Theory (LST), planar Parabolized StabilityEquations (planar-PSE), One-Way Navier Stokes (OWNS), forced direct numericalsimulation (DNS), and Adaptive Mesh Refinement Wavepacket Tracking (AMR-WPT)are presented. A dominant three-dimensional vortex instability occurring at$\approx$ 250 kHz is identified that correlates well with experimentalmeasurements of transition onset. With the exception of LST, all of thehigher-fidelity linear methods considered in this work were consistent inpredicting the initial growth and general structure of the vortex instabilityas it evolved downstream. Some of the challenges, opportunities, anddevelopment needs of the stability methods considered are discussed.

Linear Analysis of Boundary-Layer Instabilities on a Finned-Cone at Mach 6