Asymptotic structure of inviscid disturbances in a thin shock layer

1989 ◽  
Vol 23 (6) ◽  
pp. 861-867
Author(s):  
V. R. Gushchin ◽  
A. V. Fedorov
Keyword(s):  
Shock Layer ◽  
Asymptotic Structure ◽  
Thin Shock Layer

A Note on the Thin-Shock-Layer Approximation

1977 ◽  
Vol 28 (2) ◽  
pp. 85-89 ◽  
Author(s):  
R Hillier ◽  
B A Woods
Keyword(s):  
Shock Layer ◽  
Thin Shock Layer

SummaryThis Note proposes a restriction on possible solution procedures for thin-shock-layer theory. This restriction has been widely violated in solutions presented hitherto, although with negligible error apparently. Those cases are indicated where failure to apply the restriction leads to definite errors.

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.

Hypersonic Flow with Attached Shock Waves over Delta Wings

1970 ◽  
Vol 21 (4) ◽  
pp. 379-399 ◽  
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.

Hypersonic Flow Over Conical Wing-Body Combinations

1978 ◽  
Vol 29 (4) ◽  
pp. 285-304 ◽  
Author(s):  
R. Hillier
Keyword(s):  
Hypersonic Flow ◽  
Shock Layer ◽  
The Body ◽  
Practical Computation ◽  
Comparison With Experiment ◽  
Thin Shock Layer ◽  
Slope Discontinuity ◽  
The Common ◽  
Good For ◽  
Conical Wing

SummaryThis paper shows how thin shock layer theory may be applied to wing-body combinations and also to yawed wings of caret and diamond section. The common feature of these cases is the interaction of the crossflow with the body slope discontinuity and the manner in which the resulting disturbances propagate through the shock layer. Practical computation of surface pressures is straightforward and comparison with experiment appears to be fairly good for the limited results available.

Flow Regimes over Delta Wings at Supersonic and Hypersonic Speeds

1976 ◽  
Vol 27 (1) ◽  
pp. 1-14 ◽  
Author(s):  
L C Squire
Keyword(s):  
Shock Layer ◽  
Delta Wing ◽  
Leading Edge ◽  
Flow Regimes ◽  
Lower Surface ◽  
Delta Wings ◽  
Thin Shock Layer ◽  
Wide Range ◽  
Wing Sweep ◽  
Edge Separation

SummaryThis paper concerns the boundaries between flow regimes for sharp-edged delta wings in supersonic flow and the relation of some predictions of thin-shock-layer theory to these boundaries. In particular, it is shown that the theory predicts that the attachment lines on the lower surface of a thin delta wing at supersonic speeds suddenly jump from just inboard of the leading edges to the centre line in certain flight conditions. In general there is close agreement between the conditions for this jump and the flight conditions corresponding to the change-over from attached flow to the leading-edge separation on the upper surface. Since the movement of the attachment lines on the lower surface must change the position of the sonic line and the nature of the expansion around the edge, it is suggested that the two phenomena are directly related. Thus thin-shock-layer theory can be used to establish the boundaries of the various flow regimes for a wide range of Mach number, incidence and wing sweep. The theory can also be used to predict the effects of wing thickness on leading-edge separation, but here the experimental data is very sparse and somewhat contradictory, so the value of the prediction in the case of thickness requires further investigation.

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