Linear stability of hypersonic flow over a parabolic leading edge

1997 ◽  
Author(s):  
Sean Hu ◽  
Sean Hu ◽  
Xiaolin Zhong ◽  
Xiaolin Zhong
Keyword(s):  
Hypersonic Flow ◽  
Linear Stability ◽  
Leading Edge

INFLUENCE OF THE PLATE LEADING-EDGE SHAPE AND THICKNESS ON THE BOUNDARY LAYER LAMINAR-TURBULENT TRANSITION IN HYPERSONIC FLOW

2019 ◽  
Vol 50 (5) ◽  
pp. 461-481
Author(s):  
Sergei Vasilyevich Aleksandrov ◽  
Evgeniya Andreevna Aleksandrova ◽  
Volf Ya. Borovoy ◽  
Andrey Vyacheslavovich Gubernatenko ◽  
Vladimir Evguenyevich Mosharov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Hypersonic Flow ◽  
Leading Edge ◽  
Turbulent Transition ◽  
Laminar Turbulent Transition

Linear stability of hypersonic flow in thermochemical nonequilibrium

AIAA Journal ◽  
1997 ◽  
Vol 35 ◽  
pp. 958-964
Author(s):  
Mary L. Hudson ◽  
Ndaona Chokani ◽  
Graham V. Candler
Keyword(s):  
Hypersonic Flow ◽  
Linear Stability

scholarly journals Smooth leading edge transition in hypersonic flow

1999 ◽  
Vol 26 (1-2) ◽  
pp. 169-176 ◽  
Author(s):  
L. Gaillard ◽  
E. Benard ◽  
T. Alziary de Roquefort
Keyword(s):  
Hypersonic Flow ◽  
Leading Edge

scholarly journals Towards the Understanding of Humpback Whale Tubercles: Linear Stability Analysis of a Wavy Flat Plate

Fluids ◽  
2020 ◽  
Vol 5 (4) ◽  
pp. 212
Author(s):  
Miles Owen ◽  
Abdelkader Frendi
Keyword(s):  
Reynolds Number ◽  
Stability Analysis ◽  
Flat Plate ◽  
Linear Stability ◽  
Linear Stability Analysis ◽  
Critical Reynolds Number ◽  
Global Analysis ◽  
Leading Edge ◽  
Local Analysis ◽  
Mean Flow

The results from a temporal linear stability analysis of a subsonic boundary layer over a flat plate with a straight and wavy leading edge are presented in this paper for a swept and un-swept plate. For the wavy leading-edge case, an extensive study on the effects of the amplitude and wavelength of the waviness was performed. Our results show that the wavy leading edge increases the critical Reynolds number for both swept and un-swept plates. For the un-swept plate, increasing the leading-edge amplitude increased the critical Reynolds number, while changing the leading-edge wavelength had no effect on the mean flow and hence the flow stability. For the swept plate, a local analysis at the leading-edge peak showed that increasing the leading-edge amplitude increased the critical Reynolds number asymptotically, while the leading-edge wavelength required optimization. A global analysis was subsequently performed across the span of the swept plate, where smaller leading-edge wavelengths produced relatively constant critical Reynolds number profiles that were larger than those of the straight leading edge, while larger leading-edge wavelengths produced oscillating critical Reynolds number profiles. It was also found that the most amplified wavenumber was not affected by the wavy leading-edge geometry and hence independent of the waviness.

THE BLUNT-LEADING-EDGE PROBLEM IN HYPERSONIC FLOW

AIAA Journal ◽  
1963 ◽  
Vol 1 (2) ◽  
pp. 361-368 ◽  
Author(s):  
HAKURO OGUCHI
Keyword(s):  
Hypersonic Flow ◽  
Leading Edge ◽  
Edge Problem ◽  
Blunt Leading Edge

Hypersonic Flow Near the Leading Edge of a Flat Plate

1960 ◽  
Vol 3 (1) ◽  
pp. 140 ◽  
Author(s):  
H. T. Nagamatsu ◽  
T. Y. Li
Keyword(s):  
Flat Plate ◽  
Hypersonic Flow ◽  
Leading Edge

Numerical Investigation of the Linear Stability of a Free Convection Boundary Layer Flow Using a Thermal Disturbance With a Slowly Increasing Frequency

2008 ◽  
Vol 130 (12) ◽  
Author(s):  
Manosh C. Paul ◽  
D. Andrew S. Rees
Keyword(s):  
Boundary Layer ◽  
Free Convection ◽  
Linear Stability ◽  
Leading Edge ◽  
Critical Distance ◽  
Working Fluid ◽  
Convection Flow ◽  
Convection Boundary Layer ◽  
Current Frequency ◽  
Layer Flow

Numerical simulations are performed to investigate the linear stability of a two-dimensional incompressible free convection flow induced by a vertical semi-infinite heated flat plate. A small-amplitude local temperature disturbance with a slowly increasing frequency is introduced on the surface near to the leading edge in order to generate disturbance waves within the boundary layer. The aim is to compare the response of the thermal boundary layer with that obtained by selecting discrete disturbance frequencies. In the present study, air is considered to be the working fluid for which the value of the Prandtl number is taken to be Pr=0.7. The computational results show that the disturbance decays initially until it reaches a critical distance, which depends on the current frequency of the disturbance. Thereafter the disturbance grows, but the growth rate also depends on the effective frequency of the disturbance. Comparisons with previous work using constant disturbance frequencies are given, and it is shown that the sine-sweep technique is an effective method for analyzing the instability of convectively unstable boundary layers.

Hypersonic flow over concave surfaces with leading-edge bluntness

AIAA Journal ◽  
1975 ◽  
Vol 13 (9) ◽  
pp. 1230-1233 ◽  
Author(s):  
A. V. Murthy
Keyword(s):  
Hypersonic Flow ◽  
Leading Edge

scholarly journals About the features of hypersonic flow past a yawed plate

2019 ◽  
Vol 487 (1) ◽  
pp. 24-27
Author(s):  
G. N. Dudin ◽  
V. Ya. Neyland
Keyword(s):  
Hypersonic Flow ◽  
Strong Interaction ◽  
Leading Edge ◽  
Transverse Coordinate ◽  
Trailing Edge ◽  
The Third ◽  
Flow Past ◽  
Flow Functions

The flow around the yawed plate in the regime of strong interaction is considered in the case when the pressure at its trailing edge is not constant, but changes along the transverse coordinate. It is shown that in the case of large transverse gradients of the induced pressure, the type of expansions of flow functions in the vicinity of the leading edge changes significantly and the third term of the expansions should be taken into account.

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