Investigation of the stability characteristics of a compressible boundary layer on a flat plate at high mach number

1992 ◽  
Vol 33 (5) ◽  
pp. 653-657 ◽  
Author(s):  
S. E. Grubin ◽  
I. N. Simakin ◽  
V. N. Trigub
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Flat Plate ◽  
Compressible Boundary Layer ◽  
High Mach Number ◽  
High Mach ◽  
The Stability

2D and 3D Stability of Cavity Flows in High Mach Number Regimes

2019 ◽  
Author(s):  
Parshwanath S. Doshi ◽  
Rajesh Ranjan ◽  
Datta V. Gaitonde
Keyword(s):  
Stability Analysis ◽  
Mach Number ◽  
Stokes Equations ◽  
Navier Stokes ◽  
Cavity Flows ◽  
Flame Holder ◽  
High Mach Number ◽  
Eddy Simulation ◽  
High Mach ◽  
The Stability

Abstract The stability characteristics of an open cavity flow at very high Mach number are examined with BiGlobal stability analysis based on the eigenvalues of the linearized Navier-Stokes equations. During linearization, all possible first-order terms are retained without any approximation, with particular emphasis on extracting the effects of compressibility on the flowfield. The method leverages sparse linear algebra and the implicitly restarted shift-invert Arnoldi algorithm to extract eigenvalues of practical physical consequence. The stability dynamics of cavity flows at four Mach numbers between 1.4 and 4 are considered at a Reynolds number of 502. The basic states are obtained through Large Eddy Simulation (LES). Frequency results from the stability analysis show good agreement when compared to the theoretical values using Rossiter’s formula. An examination of the stability modes reveals that the shear layer is increasingly decoupled from the cavity as the Mach number is increased. Additionally, the outer lobes of the Rossiter modes are observed to get stretched and tilted in the direction of the freestream. Future efforts will extend the present analysis to examine current and potential cavity flame holder configurations, which often have downstream walls inclined to the vertical.

A High Mach Number Turbulent Boundary-Layer Study

AIAA Journal ◽  
1976 ◽  
Vol 14 (9) ◽  
pp. 1159-1160 ◽  
Author(s):  
E. Backx ◽  
B.E. Richards
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Turbulent Boundary Layer ◽  
High Mach Number ◽  
High Mach

Comparison of Boundary Layer Similarity Transformations for High Mach Number Flows

2019 ◽  
Author(s):  
Nicholas J. DiGregorio ◽  
Tomasz G. Drozda ◽  
Cyrus K. Madnia
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
High Mach Number ◽  
Similarity Transformations ◽  
High Mach

scholarly journals Influence of surface sublimation on boundary layer stability at high Mach number

2019 ◽  
Vol 1404 ◽  
pp. 012079
Author(s):  
S A Gaponov ◽  
A N Semenov ◽  
B V Smorodsky
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Boundary Layer Stability ◽  
High Mach Number ◽  
High Mach

Optical refraction from high Mach number turbulent boundary layer structures

1998 ◽  
Author(s):  
P. Erbland ◽  
M. Etz ◽  
W. Lempert ◽  
A. Smits ◽  
R. Miles
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Turbulent Boundary Layer ◽  
High Mach Number ◽  
Optical Refraction ◽  
Layer Structures ◽  
High Mach

scholarly journals Instability wave–streak interactions in a high Mach number boundary layer at flight conditions

2018 ◽  
Vol 858 ◽  
pp. 474-499 ◽  
Author(s):  
Pedro Paredes ◽  
Meelan M. Choudhari ◽  
Fei Li
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Boundary Layer Flow ◽  
Free Stream ◽  
Instability Wave ◽  
Instability Waves ◽  
High Mach Number ◽  
Layer Flow ◽  
High Mach ◽  
Optimal Disturbances

The interaction of stationary streaks undergoing non-modal growth with modally unstable instability waves in a high Mach number boundary-layer flow is studied using numerical computations. The geometry and flow conditions are selected to match a relevant trajectory location from the ascent phase of the HIFiRE-1 flight experiment; namely, a $7^{\circ }$ half-angle, circular cone with $2.5$ mm nose radius, free-stream Mach number equal to $5.30$, unit Reynolds number equal to $13.42~\text{m}^{-1}$ and wall-to-adiabatic temperature ratio of approximately $0.35$ over most of the vehicle. This paper investigates the nonlinear evolution of initially linear optimal disturbances that evolve into finite-amplitude streaks, followed by an analysis of the modal instability characteristics of the perturbed, streaky boundary-layer flow. The investigation is performed with a stationary, full Navier–Stokes equations solver and the plane-marching parabolized stability equations (PSE), in conjunction with partial-differential-equation-based planar eigenvalue analysis. The overall effect of streaks is to reduce the peak amplification factors of instability waves, indicating a possible downstream shift in the onset of laminar–turbulent transition. The present study confirms previous findings that the mean-flow distortion of the nonlinear streak perturbation reduces the amplification rates of the Mack-mode instability. More importantly, however, the present results demonstrate that the spanwise varying component of the streak can produce a larger effect on the Mack-mode amplification. The analysis of planar and oblique Mack-mode waves modulated by the presence of the streaks shows that the planar Mack mode still dominates the instability characteristics of the flow. The study with selected azimuthal wavenumbers for the stationary streaks reveals that a wavenumber of approximately $1.4$ times larger than the optimal wavenumber is more effective in stabilizing the planar Mack-mode instabilities. In the absence of unstable first-mode waves for the present cold-wall condition, transition onset is expected to be delayed until the peak streak amplitude increases to nearly 35 % of the free-stream velocity, when intrinsic instabilities of the boundary-layer streaks begin to dominate the transition process. For streak amplitudes below that limit a significant net stabilization is achieved, yielding a potential transition delay that can exceed 100 % of the length of the laminar region in the uncontrolled case.

Stability and transition of a supersonic laminar boundary layer on an insulated flat plate

1960 ◽  
Vol 9 (2) ◽  
pp. 257-299 ◽  
Author(s):  
John Laufer ◽  
Thomas Vrebalovich
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Mach Number ◽  
Flat Plate ◽  
Laminar Boundary Layer ◽  
Amplification Coefficient ◽  
Unit Distance ◽  
The Stability ◽  
Stability Limits ◽  
Supersonic Laminar

Self-excited oscillations have been discovered experimentally in a supersonic laminar boundary layer along a flat plate. By the use of appropriate measuring techniques, the damping and amplification of the oscillations are studied and the stability limits determined at free-stream Mach numbers 1·6 and 2·2. The wave-like nature of the oscillations is demonstrated and their wave velocities are measured using a specially designed ‘disturbance generator’. It is shown empirically that the stability limits expressed in terms of the boundary-layer-thickness Reynolds number are independent of the Mach number and dependent only on the oscillation frequency. The main effect of compressibility is an increase in wave velocity with Mach number. This has the consequence that the disturbances, although possessing the same dimensionless amplification coefficient as in the incompressible case, have less time (per unit distance) to grow in amplitude. Thus, the adiabatic compressible boundary layer is shown to be more stable than the incompressible one. In general, the experiments confirm the basic assumptions and predictions of the existing stability theory and also suggest the desirability of improvement in the theory in certain phases of the problem. Finally, on the basis of these results a rough estimate of the transition Reynolds number is made in the compressible flow range.

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