MHD Control of the Hypersonic Flow in the Shock Layer Around a Body

The separation points which occur in the Newtonian theory of hypersonic flow are treated by locally modifying the shock-layer equations. This approach leads to direct verification of the free-layer theory for separation on certain bodies with discontinuous curvature. Separation points on bodies with continuous curvature have already been treated by matching the upstream shock-layer solution to the downstream free-layer solution. The agreement that is found between these results and those of the present approach provides further confirmation of the free-layer theory.

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Three-dimensional wings in hypersonic flow

Journal of Fluid Mechanics ◽

10.1017/s0022112072000709 ◽

1972 ◽

Vol 54 (2) ◽

pp. 305-337 ◽

Cited By ~ 5

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.

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Asymptotic solution to the problem of hypersonic flow over bodies in the neighborhood of the separation point of a thin shock layer

Fluid Dynamics ◽

10.1007/bf01090703 ◽

1982 ◽

Vol 17 (1) ◽

pp. 81-86

Author(s):

E. R. Abramovskii ◽

N. N. Lychagin

Keyword(s):

Asymptotic Solution ◽

Hypersonic Flow ◽

Shock Layer ◽

Separation Point ◽

Thin Shock Layer

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Aerodynamic drag reduction by heat addition into the shock layer for a large angle blunt cone in hypersonic flow

Physics of Fluids ◽

10.1063/1.2944982 ◽

2008 ◽

Vol 20 (8) ◽

pp. 081703 ◽

Cited By ~ 23

Author(s):

Vinayak Kulkarni ◽

G. M. Hegde ◽

G. Jagadeesh ◽

E. Arunan ◽

K. P. J. Reddy

Keyword(s):

Drag Reduction ◽

Hypersonic Flow ◽

Shock Layer ◽

Aerodynamic Drag ◽

Large Angle ◽

Blunt Cone ◽

Heat Addition ◽

Aerodynamic Drag Reduction

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Viscous shock layer on a plate in hypersonic flow

European Journal of Mechanics - B/Fluids ◽

10.1016/s0997-7546(99)80023-5 ◽

1999 ◽

Vol 18 (2) ◽

pp. 213-226 ◽

Cited By ~ 7

Author(s):

A.A. Maslov ◽

S.G. Mironov ◽

T.V. Poplavskaya ◽

A.N. Shiplyuk ◽

V.N. Vetlutsky

Keyword(s):

Hypersonic Flow ◽

Shock Layer ◽

Viscous Shock Layer

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Hypersonic Flow with Attached Shock Waves over Delta Wings

Aeronautical Quarterly ◽

10.1017/s0001925900005539 ◽

1970 ◽

Vol 21 (4) ◽

pp. 379-399 ◽

Cited By ~ 10

Author(s):

B. A. Woods

Keyword(s):

Shock Waves ◽

Hypersonic Flow ◽

Shock Layer ◽

Numerical Solutions ◽

Delta Wing ◽

Simple Wave ◽

Delta Wings ◽

Conical Flows ◽

Thin Shock Layer ◽

Flow Variables

SummaryHypersonic conical flows over delta wings are treated in the thin-shock-layer approximation due to Messiter. The equations are hyperbolic throughout, even in regions where the full equations are elliptic, and have not hitherto been solved for flows with attached shock waves. The concept of the simple wave has been used to construct a class of solutions for such flows; they contain discontinuities in flow variables and shock slope but, for the case of flow over a delta wing with lateral symmetry, agreement with results of numerical solutions of the full equations is good. The method is applied to plane delta wings at yaw, and to wings with anhedral and dihedral. For the flow at the tip of a rectangular wing, it is shown that two distinct solutions may be constructed.

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