Errata: Unsteady Hypersonic Flow over Delta Wings with Detached Shock Waves

AIAA Journal ◽  
1976 ◽  
Vol 14 (11) ◽  
pp. 1663b-1663b
Author(s):  
W. H. Hui ◽  
H. T. Hemdan
Keyword(s):  
Shock Waves ◽  
Hypersonic Flow ◽  
Delta Wings

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 with attached shock waves over plane delta wings

1977 ◽  
Vol 79 (2) ◽  
pp. 361-377 ◽  
Author(s):  
B. A. Woods ◽  
C. B. G. Mcintosh
Keyword(s):  
General Solution ◽  
Shock Waves ◽  
Hypersonic Flow ◽  
Shock Layer ◽  
Delta Wing ◽  
Numerical Calculations ◽  
Delta Wings ◽  
Thin Shock Layer ◽  
New Form

A new form is given for the general solution to the thin-shock-layer equations for the flow over a nearly plane delta wing. Using this, the solution described conjecturally by Hayes & Probstein for symmetrical flow with attached shock waves over a plane delta wing is realized numerically. The flow construction devised for this purpose is applied also to yawed flows. The solutions obtained are found to agree moderately well with the results of numerical calculations from the full equations, but contain a number of anomalous features characteristic of the thin-shock-layer approximation.

Delta Wings of Shapes Amenable to Exact Shock-wave Theory

1963 ◽  
Vol 67 (625) ◽  
pp. 39-40 ◽  
Author(s):  
T. Nonweiler
Keyword(s):  
Shock Wave ◽  
Mach Number ◽  
Shock Waves ◽  
Hypersonic Flow ◽  
Cross Section ◽  
Wave Theory ◽  
Wave System ◽  
Delta Wings ◽  
Shock Wave Theory

SummaryA class of delta wings is considered, whose under-surface has an inverted-V, or inverted-W, cross section of such a form that, at the “design” Mach number and incidence, the shock waves formed are plane. The geometry of the shock-wave system and surface is described briefly, and comments made about the utility of the concept in relation to hypersonic flow studies.

Unsteady hypersonic flow over delta wings with detached shock waves

AIAA Journal ◽  
1976 ◽  
Vol 14 (4) ◽  
pp. 505-511 ◽  
Author(s):  
W. H. Hui ◽  
H. T. Hemdan
Keyword(s):  
Shock Waves ◽  
Hypersonic Flow ◽  
Delta Wings

Entropy effects in hypersonic flow over blunt delta wings

1991 ◽  
Vol 26 (2) ◽  
pp. 304-307
Author(s):  
S. A. Gorokhov ◽  
V. V. Eremin ◽  
A. M. Polyakov
Keyword(s):  
Hypersonic Flow ◽  
Delta Wings ◽  
Entropy Effects

Configurations for High Supersonic Speeds Derived from Simple Shock-waves and Expansions

1963 ◽  
Vol 67 (629) ◽  
pp. 287-290 ◽  
Author(s):  
J. W. Flower
Keyword(s):  
Shock Waves ◽  
Lower Surface ◽  
Delta Wings ◽  
Free Surfaces

SummaryThe Nonweiler method of designing delta wings (caret wings) to have plane shocks on the lower surface is extended to the design of upper surfaces. Cambered and shock-free surfaces are also deduced, and methods of design for complete configurations suggested.An important point is that all surfaces are of single curvature.

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