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

Flower, J. W.

doi:10.1017/s0368393100078597

Cited by 9 publications

(5 citation statements)

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“…Maikapar in Russia. 16 Small models of these were tested in supersonic free flight, fired from gas guns at the Jet Propulsion Laboratory in California, but failed to demonstrate the anticipated performance, due it is thought to friction effects. 17 Nonweiler believed that in 1962-63 at least one Waverider was tested at the Woomera Rocket Range, mounted on the nose of an air-launched Blue Steel stand-off bomb, but no trace of such a flight could be found, and at the 2001 Charterhouse conference of the British Rocketry Oral History Program, and in subsequent lectures and conversations in Scotland, Prof. John Allen and other lecturers described the Woomera Blue Steel tests in detail and confirmed that none of them had add-on Waveriders.…”

Section: Research 1960-1980mentioning

confidence: 99%

Waverider, A Revised Chronology

Lunan¹

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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The Waverider atmosphere entry vehicle was invented in the 1950s at Queen's College, Belfast, during studies of a man-carrying vehicle for a British space program to be based on Blue Streak, by the late Prof. Terence R.F. Nonweiler, later Professor of Aeronautics and Dean of Engineering at Glasgow University. The use of a Waverider nose-cone on the US Air Force X-51A prototype cruise missile, 2003-2012, has caused some press coverage to describe it as a recent invention. Research by the author, particularly in 2013-14, has clarified many issues regarding the definition, origins and history of Waverider vehicles to date, and may help to set the record straight in a number of respects.

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Section: Research 1960-1980mentioning

confidence: 99%

Waverider, A Revised Chronology

Lunan¹

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…As the simplest forms of conical bodies with star-shaped cross-section [22,23], waveriders [26,27] as well as other more complicated bodies [1][2][3]11,24,34,42,44], which were later constructed in gasdynamics, belonged to the new class of aerodynamic forms. Compared, for example, to such classical forms as triangular and other slender wings, slender bodies of revolution and so on, the flows around the above forms were not studied in a wide range of flow velocities.…”

Section: Brief Surveymentioning

confidence: 99%

“…However, the advantage of this form, in his opinion, makes itself evident only in calculations rather than in the aerodynamic characteristics. If a simple waverider is considered as the prototype of a hypersonic aircraft [1,11,15,18,27], its drawbacks are quite natural and evident. First, the presence of a bottom section.…”

Section: Brief Surveymentioning

confidence: 99%

“…It is emphasized in the survey work [42] that for the construction of the lower surface it is possible to use the flows near different bodies: a two-dimensional wedge, a multistage wedge, a cone, a conecylinder combination, a cone-ogive combination, as well as a vortex flow behind a curved shock. In order to construct a lifting upper surface two-dimensional and axisymmetric expanding flows are used [11,21,45].…”

Section: Brief Surveymentioning

confidence: 99%

“…These tools are quite sufficient to construct the test forms [11,20,23] for the computational algorithms for three-dimensional problems and find some regularities [6,27,30,44] in hypersonic aerodynamics. In order to construct complicated forms of an air inlet type or the whole aircraft, which are intended for the numerical experiment, we introduce some additional procedures, in particular, we consider a nonuniform flow.…”

Section: Additional Proceduresmentioning

confidence: 99%

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Information technology of mathematical modelling of a three-dimensional supersonic flow on the basis of particular solutions of hydrodynamic problems

Shchepanovskii¹

1997

Russian Journal of Numerical Analysis and Mathematical Modelling

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We propose the formalized methods of mathematical modelling of a three-dimensional supersonic flow on the basis of solutions of smaller dimensionality. We separate a base algorithm for constructing the solution and derive an equation for the streamlined space surface. We introduce concrete techniques, viz. the procedures of superposition, completion, and convergence. We construct test forms for debugging the multidimensional computational algorithms and study various parts of hypersonic aircraft.The methods of mathematical modelling and numerical experiment, which are used in research, find expanding application in engineering fields, where the mathematical models of processes and phenomena have not been adequately developed and tested. When passing to multidimensional complex problems we encounter the difficulties associated with the statement of the problems and the adequacy of the model to a real object. In particular, we mean the problems of high-speed aerodynamics. There are the most complicated aspects of the problem here, viz. on the one hand, the problem is multidimensional and on the other hand it is basically nonlinear for supersonic flows. At the same time the problem of a hypersonic three-dimensional flow has become most urgent because of the evolution of aerospace technology.When studying the hypersonic flow problems it is necessary to consider threedimensional forms. Motion with supersonic speeds in gaseous atmosphere inevitably gives rise to shock waves. When the supersonic speeds are high, these shocks are strong. Then the lifting properties of a body are mainly defined by the asymmetry of the shock configuration since the excessive pressure behind a bow shock is a substantial component when producing a lift force. Therefore three-dimensional problems are urgent and characteristic of a hypersonic velocity range. In 1969 Maikapar and Keldysh [24] introduced a special concept of gasdynamic design to construct a supersonic three-dimensional flow on the basis of particular solutions of smaller dimension. In this paper we try to formalize the technology of obtaining a three-dimensional solution, determine the main operations of the technology, and demonstrate a concrete application.In the procedure of superposition in which the base algorithm is combined with the same technique but this technique is applied to an extended undisturbed supersonic flow we obtain lifting systems whose lift force is produced by the pressure differential in the shock wave. That is why the gasdynamic design takes the features of the technology in hypersonic aerodynamics. The procedure of completion is introduced for constructing bodies with complicated, in particular, star-shaped cross-section.

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