Some design aspects of space shuttle orbiters

Townend, L. H.

doi:10.1016/0376-0421(72)90015-2

Cited by 4 publications

(3 citation statements)

References 58 publications

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“…Townend (Ref. 22,1970) presents data showing that such aerodynamic advantages are realized in practice. He concludes that the Nonweiler wing may providb lift coefficients greater than those of the convex or flat-bottomed delta shapes which have received most of the attention in the U. S. Roe (Ref.…”

Section: Aedctr-72-181mentioning

confidence: 99%

An Investigation of an Upper Stage Rocket Plane with External-Burning Thrust Augmentation

Callens¹,

Miller²,

Potter³

1973

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Section: Aedctr-72-181mentioning

confidence: 99%

An Investigation of an Upper Stage Rocket Plane with External-Burning Thrust Augmentation

Callens¹,

Miller²,

Potter³

1973

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“…Townend 6 suggests that the heating problems (both the rate and the peak) may be less severe on waveriders than on flat delta wings with the same lower surface deflection angle.…”

Section: Introductionmentioning

confidence: 97%

Off-design performance of hypersonic waveriders

Long

1990

Journal of Aircraft

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Waveriders are being considered more and more as potential aerospace vehicles. There are several questions, however, regarding these configurations that must be answered before they can be considered viable designs. The most significant problems are related to aerothermal heating, propulsion integration, and off-design performance. This paper presents off-design performance predictions for two generic waveriders. The results are from a numerical method based on the nonlinear, inviscid Euler equations. Comparisons to experimental data are also shown.

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“…The role of dynamic stability at high incidence during re-entry or manoeuvre has been pointed out by Orlik-Ruckemann (1975). The shock-attached relatively high aspect ratio delta is often preferred (Townend 1970) for its high lift-drag ratio. Hui and Hemdan (1976) have studied the unsteady shock-detached case in the context of thin shock layer theory.…”

Section: Introductionmentioning

confidence: 99%

Hypersonic large-deflection similitude for oscillating delta wings

Ghosh

1984

Aeronaut. j.

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A similitude has been obtained for delta wings with attached leading edge shock at large incidence in hypersonic flow. A strip theory in which flow at a spanwise location is two-dimensional has been developed. This combines with the similitude to lead to a piston theory which gives closed form solutions for unsteady derivatives in pitch and roll. The derivatives in pitch are independent of and the roll damping derivative varies linearly with the aspect ratio. Substantially the same results as the theory of Liu and Hui are obtained with remarkable computational ease.

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Some design aspects of space shuttle orbiters

Cited by 4 publications

References 58 publications

An Investigation of an Upper Stage Rocket Plane with External-Burning Thrust Augmentation

An Investigation of an Upper Stage Rocket Plane with External-Burning Thrust Augmentation

Off-design performance of hypersonic waveriders

Hypersonic large-deflection similitude for oscillating delta wings

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