Hypersonic Flow on Yawed Wedges with Leading-Edge Bluntness and Viscous Interaction

1971 ◽  
Vol 8 (7) ◽  
pp. 729-735 ◽  
Author(s):  
R. C. BOGER ◽  
G. F. AIELLO
Keyword(s):  
Hypersonic Flow ◽  
Leading Edge ◽  
Viscous Interaction

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

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

Axisymmetric hypersonic flow with strong viscous interaction

1968 ◽  
Vol 34 (4) ◽  
pp. 687-703 ◽  
Author(s):  
John Webster Ellinwood ◽  
Harold Mirels
Keyword(s):  
Shock Wave ◽  
Hypersonic Flow ◽  
Power Law ◽  
Axisymmetric Flow ◽  
Strong Shock ◽  
The Body ◽  
Strong Shock Wave ◽  
Viscous Interaction ◽  
Slender Bodies ◽  
Prandtl Numbers

Stewartson's theory for axisymmetric hypersonic flow of a model gas over slender bodies with strong viscous interaction and strong shock wave is extended to power-law viscosity variation and Prandtl numbers other than one. Flow properties at the body surface and shock are obtained without recourse to numerical integration. Numerical computations are presented for axisymmetric flow over a three-quarter power-law body with strong shock wave and viscous interactions that range from weak to strong.

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.

Sign in / Sign up

Export Citation Format

Share Document