Pointed two-parameter power-law nose shapes of minimum wave drag

A direct method of constructing pointed contours which are close to optimum with respect to wave drag is developed for axisymmetric nose shapes using Euler's equations. A two-parameter power function is a good approximation of the contours constructed using this method. Calculations, carried out using the proposed approximation, demonstrate the reduction in the wave drag of the bodies constructed compared with existing optimum, blunt, one-parameter, power-law nose shapes.     

The construction of symmetric nose shapes of minimum wave drag

The problem of minimizing the wave drag of axisymmetric noses in the supersonic flow of an inviscid, non-heat-conducting perfect gas is considered. A procedure is proposed for constructing the extremal generatrix by step-by-step solution of single parameter problems using assumptions concerning the local relation between the geometric parameters and the gas-dynamic functions. A unique generatrix, from which parts are separated which form noses of arbitrary length, corresponds to the specified free-stream conditions. Comparison of the noses obtained and the noses which are optimal in the exact formulation of the problem shows that the aerodynamic characteristics are close when there is an appreciable difference between the geometric parameters.     

On the calculation of minimum variance estimators for unobservable dependent variables

The determination of minimum variance estimators in an unusual context is considered. The problem arises from an attempt to perform a regression with an unobservable dependent variable. The required minimum variance estimator is shown to satisfy a linear system of equations where the coefficient matrix has a simple structure. Uniqueness of the estimator is established by determining necessary and sufficient conditions on the data which guarantee positive definiteness of this coefficient matrix. Numerical aspects of the method of computation are also briefly explored.     

Axisymmetric bodies of minimum drag in hypersonic flow

The problem of determining the longitudinal contour of a slender, axisymmetric body in hypersonic flow which has minimum drag is considered. The pressure distribution is assumed to be Newtonian, while the skin-friction distribution is for laminar flow and depends on body geometry. This investigation is conducted with the method of steepest descent, whose feasiblity is demonstrated by solving minimum drag problems having known analytical solutions.     

On the calculation of wave fields propagating in multilayer media

A program for evaluating elastic waves in multilayer media is composed on the basis of the algorithm previously stated. The waves under consideration undergo all possible acts of reflection and refraction on the interfaces of the media. Exchanges on these interfaces are also taken into account. Two examples illustrating the calculation of theoretical seismograms of elastic waves are presented. Bibliography: 5 titles. Translated fromZapiski Nauchnykh Seminarov POMI, Vol. 203, 1992, pp. 156–165. Translated by N. S. Zabavnikova     

Towards the computation of minimum drag profiles in viscous laminar flow

A numerical method is given for the solution of certain optimum design problems of fluid mechanics. The profile of given area and smallest drag in a uniform laminar flow is computed. This profile is long and slim, its front end is shaped like a wedge of angle 90° and its rear end is shaped like a cusp. Owing to the numerical complexity of the problem the precision of the results is average (around 5%). However, this work is a good illustration of the theoretical method exposed previously and it shows how good precision can be obtained if one is prepared to pay for it. A numerical solution of the adjoint system of the stationary Navier-Stokes equation is also given; this equation will play an important role in optimum design in fluid mechanics.     

Variation of drag coefficient with wind wave development

Turbulent air flows over developing wind waves in the air-sea boundary layer are numerically simulated without considering wave breaking. Influences of wind waves on air flows are considered using a model of significant wave and surface roughness, with a formula proposed for calculating the surface roughness. κ-ε model is adopted to simulate turbulent flows. The results of the drag coefficient and turbulence characteristics agree well with the observations. Project supported by the National Natural Science Foundation of China (Grant No. 19332010).     

On the structure of supersonic flow

Zusammenfassung Die im Grossen invarianten Eigenschaften von Wellenfronten, Zweig- und Grenzlinien in der ebenen, stetigen, wirbelfreien und isentropischen Str?mung idealer Gase werden diskutiert.

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This work was sponsored by the Office of Scientific Research of the Air Research and Development Command of the United States Air Force under Contract AF 49(638)232.     

LES and analyses on the vortex structure behind supersonic MVG with turbulent inflow

In this paper, an implicitly implemented high order large eddy simulation by using the fifth order bandwidth-optimized WENO scheme is applied to make comprehensive studies on ramp flows with and without control at Mach 2.5 and Re_θ = 5760. Flow control in the form of microramp vortex generators (MVG) is applied. The mechanism of vortex ring generation behind MVG has been studied in detail and shear layer instability has been studied and found as the mechanism of K–H vortex ring generation. A series of new observations on the flow around supersonic MVG have been made including inflection points (surface in 3-D), vorticity conservation, interaction of the primary vortex and new generated K–H vortex rings, and the K–H vortex ring structure. The numerical observations have been confirmed by the experimental work.     

Global supersonic conic shock wave for the steady supersonic flow past a cone: Polytropic gas

In this paper, we establish the global existence and stability of a steady conic shock wave for the symmetrically perturbed supersonic flow past an infinitely long conic body as long as the vertex angle is less than a critical value. The flow is assumed to be polytropic, isentropic and described by a steady potential equation. Based on the delicate asymptotic expansion of the background solution, one can verify that the boundary conditions on the shock and the conic surface satisfy the “dissipative” property. From this property, by use of the reflected characteristics method and the special form of the shock equation, we show that the conic shock attached at the vertex of the cone exists globally in the whole space when the speed of the supersonic coming flow is appropriately large. On the other hand, we remove the smallness restriction on the sharp vertex angle in order to establish the global existence of a shock or a global weak solution, moreover, our proof approach is different from that in [Shuxing Chen, Zhouping Xin, Huicheng Yin, Global shock wave for the supersonic flow past a perturbed cone, Comm. Math. Phys. 228 (2002) 47-84] and [Zhouping Xin, Huicheng Yin, Global multidimensional shock wave for the steady supersonic flow past a three-dimensional curved cone, Anal. Appl. 4 (2) (2006) 101-132].     

On the minimum time map

Santo Si studiano alcune proprietà della funzione di tempo minimo per un'equazione differenziale multivoca su una varietà C. Si mette in relazione la funzione di tempo minimo per una famiglia di campi vettoriali con guella per l'equazione multivoca associata. Inoltre si prova che da una estensione alle varietà riemanniane complete della condizione classica F(t, x)(t)+v(t)x, si hanno le stesse conseguenze che in Rⁿ. Si prova, infine, sotto la stessa condizione, che la funzione che ad ogni t associa l'insieme raggiungibile al tempo t è localmente lipschitziana (rispetto alla metrica di Hausdorff).

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This work was performed under the auspices of the National Research Council of Italy (C.N.R.).     

On the minimum of harmonic functions

Letu be a function harmonic in the unit disc or in the plane, and letu(z)≤M(|z|) for a majorantM. We formulate conditions onM that guarantee thatu(z)≥−(1+o(1))M(|z|) for |z|→1 in the disc and for |z|→∞ in the plane.     

On the existence of global vortex rings

Sans résumé Supported in part by a grant from the National Science Foundation. The results of this paper were obtained while the author was partially supported by U. S. Army Research Office grant No. DAA-29-78-6-0127 at Courant Institute, New York University.