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

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

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

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.

Three-dimensional wings in hypersonic flow

1972 ◽  
Vol 54 (2) ◽  
pp. 305-337 ◽  
Author(s):  
R. Hillier
Keyword(s):  
Exact Solution ◽  
Hypersonic Flow ◽  
Shock Layer ◽  
Three Dimensional ◽  
Leading Edge ◽  
The Other ◽  
Calculation Methods ◽  
Conical Flow ◽  
Thin Shock Layer ◽  
Good For

Messiter's thin shock layer approximation for hypersonic wings is applied to several non-conical shapes. Two calculation methods are considered. One gives the exact solution for a particular three-dimensional geometry which possesses a conical planform and also a conical distribution of thickness superimposed upon a surface cambered in the chordwise direction. Agreement with experiment is good for all cases, including that where the wing is yawed. The other method is a more general approach whereby the solution is expressed as a correction to an already known conical flow. Such a technique is applicable to conical planforms with either attached or detached shocks but only to the non-conical planform for the region in the vicinity of the leading edge when the shock is attached.

Leading-edge receptivity to free-stream disturbance waves for hypersonic flow over a parabola

2001 ◽  
Vol 441 ◽  
pp. 315-367 ◽  
Author(s):  
XIAOLIN ZHONG
Keyword(s):  
Boundary Layer ◽  
Hypersonic Flow ◽  
Boundary Layers ◽  
Free Stream ◽  
Stokes Equations ◽  
Leading Edge ◽  
Bow Shock ◽  
Navier Stokes ◽  
Hypersonic Boundary Layer ◽  
Disturbance Waves

The receptivity of hypersonic boundary layers to free-stream disturbances, which is the process of environmental disturbances initially entering the boundary layers and generating disturbance waves, is altered considerably by the presence of bow shocks in hypersonic flow fields. This paper presents a numerical simulation study of the generation of boundary layer disturbance waves due to free-stream waves, for a two-dimensional Mach 15 viscous flow over a parabola. Both steady and unsteady flow solutions of the receptivity problem are obtained by computing the full Navier–Stokes equations using a high-order-accurate shock-fitting finite difference scheme. The effects of bow-shock/free-stream-sound interactions on the receptivity process are accurately taken into account by treating the shock as a discontinuity surface, governed by the Rankine-Hugoniot relations. The results show that the disturbance waves generated and developed in the hypersonic boundary layer contain both first-, second-, and third-mode waves. A parametric study is carried out on the receptivity characteristics for different free-stream waves, frequencies, nose bluntness characterized by Strouhal numbers, Reynolds numbers, Mach numbers, and wall cooling. In this paper, the hypersonic boundary-layer receptivity is characterized by a receptivity parameter defined as the ratio of the maximum induced wave amplitude in the first-mode-dominated region to the amplitude of the free-stream forcing wave. It is found that the receptivity parameter decreases when the forcing frequency or nose bluntness increase. The results also show that the generation of boundary layer waves is mainly due to the interaction of the boundary layer with the acoustic wave field behind the bow shock, rather than interactions with the entropy and vorticity wave fields.

Leading edge effect on rarefied hypersonic flow over a flat plate

1991 ◽  
Author(s):  
K. HEFFNER ◽  
L. GOTTESDIENER ◽  
A. CHPOUN ◽  
J. LENGRAND
Keyword(s):  
Flat Plate ◽  
Hypersonic Flow ◽  
Edge Effect ◽  
Leading Edge
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