Research and design for lifting reentry

Townend, L. H.

doi:10.1016/0376-0421(79)90001-0

Cited by 36 publications

(4 citation statements)

References 41 publications

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“…Work on waveriders in the 1980s took some account of Nonweiler's conductive leading edges (Bowcutt 1986) and recent results in Germany, published by the AIAA (Strohmeyer et al . 1998) reach conclusions that are consistent with those of Capey and Nonweiler (see Townend 1978). The analysis presented here allows Nonweiler to indicate the potential, especially at higher Mach numbers, which is offered by conductive cooling, and gives the theoretical foundation for further work, both for re-entry and launch.…”

Section: Philsupporting

confidence: 82%

Topic I. Serving the International Space Station

Townend¹

1999

Philosophical Transactions of the Royal Society of London. Seri

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Section: Philsupporting

confidence: 82%

Topic I. Serving the International Space Station

Townend¹

1999

Philosophical Transactions of the Royal Society of London. Seri

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“…The first extension of Nonweiler's concept to the use of a conical flow as a generating flowfield was by Jones [237] in 1963, and further extensions to other axisymmetic generating flows are discussed by Jones et al in [238]. An excellent and authoritative survey of waverider research up to 1979 is given by Townend in [239]. In the early 1980s Rasmussen and his colleagues at the University of Oklahoma (for example, see [240 -242]) utilized hypersonic small-disturbance theory to design waveriders from flowfields over right-circular cones as well as elliptic cones.…”

Section: Design Example 52: Hypersonic Waveriders-partmentioning

confidence: 95%

Hypersonic and High-Temperature Gas Dynamics, Second Edition

Anderson¹

2006

973

603

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Data and information appearing in this book are for information purposes only. AIAA is not responsible for any injury or damage resulting from use or reliance, nor does AIAA warrant that use or reliance will be free from privately owned rights. Downloaded by Stanford University on September 30, 2012 | http://arc.aiaa.org | , for all their love and understanding Downloaded by Stanford University on September 30, 2012 | http://arc.aiaa.org |

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“…The possibility of improving the lifting properties of a wing with a delta-like planform by deforming its transverse contour was demonstrated experimentally in [33].…”

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confidence: 99%

Aerodynamic characteristics of V-shaped wings with shock waves detached from leading edges at hypersonic speeds

Ostapenko¹

1993

Fluid Dyn

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The direct problem of hypersonic flow past a V-shaped wing with a shock wave detached from the leading edges is solved. The reduced normal force coefficient and the lift-drag (L/D) ratio are calculated for a configuration with a lower part in the shape of a V-wing and a streamwise upper part.1. Consider a symmetrical flow past a V-wing with aperture angle "y and apex angle/3 (Fig. 1) 1 (:x -,f) (1.1) b=tg[3cosq',, h=tg~sinT,, T,= Let the function y=y~ z) represent the shape of the shock wave. Using the conservation laws, we can obtain the following expressions for the velocity components u ~ v ~ w ~ along the x, y and z axes, the pressure p~ and the density p~ behind the shock from divided by the free-stream velocity, double ram pressure and density, respectively:Here, • is the specific heat ratio and M is the flee-stream Mach number. The small parameter e, which is that of thin shock layer theory and equal to the ratio of the densities before and behind the shock wave, is defined by the following relation:We shall assume that (x-1)M 2 sin 2 c~_>O(l) and cos e~=O(1). Then, in accordance with (1.2), u~ v~ Yx = O(e tan o0. We also have an estimate for the scale length of the conical vorticity flow in the compressed layer for uniform flow behind the plane shock attached to the leading edge: z/x=O(.4e tan o0. As follows from this estimate, the transition from the flow regime with a shock attached to the wing leading edges to that with a detached shock takes place when (see Fig. 1) b = o ( ~ tg ~) (1.3)Moreover, the thin shock layer theory determines the limits within which h may vary ( Fig. 1)Then, in accordance with (1.1), (1.3), and (1.4), we can obtain the following estimate: T1 -< O(x/e). Let us assume that the shock is attached to the leading edges, this corresponding to the relation ~ oYx-h-byz.Then, using the impermeability condition on the wing surface v~ ~ =h/b and taking (1.2) into account, we get Yz + b ctg ayz~ + e -h ctg a = 0 (1.5)where only the main terms of the expansion have been kept. It follows from (1.5) that flow with a detached shock wave will occur when the following inequality holds:Moscow.

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Research and design for lifting reentry

Cited by 36 publications

References 41 publications

Topic I. Serving the International Space Station

Topic I. Serving the International Space Station

Hypersonic and High-Temperature Gas Dynamics, Second Edition

Aerodynamic characteristics of V-shaped wings with shock waves detached from leading edges at hypersonic speeds

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