Large-Amplitude Long-Wave Instability of a Supersonic Shear Layer

For sufficiently high Mach numbers, small disturbances on a supersonic vortex sheet are known to grow in amplitude because of slow nonlinear wave steepening. Under the same external conditions, linear theory predicts slow growth of long-wave disturbances to a thin supersonic shear layer. An asymptotic formulation is given here which adds nonzero shear-layer thickness to the weakly nonlinear formulation for a vortex sheet. Spatial evolution is considered, for a spatially periodic disturbance having amplitude of the same order, in Reynolds number, as the shear-layer thickness. A quasi-equilibrium inviscid nonlinear critical layer is found, with effects of diffusion and slow growth appearing through nonsecularity condition. Other limiting cases are also considered, in an attempt to determine a relationship between the vortex-sheet limit and the long-wave limit for a thin shear layer; there appear to be three special limits, corresponding to disturbances of different amplitudes at different locations along the shear layer

A study of the interaction of a normal shock wave with a turbulent boundary layer at transonic speeds

An asymptotic description is derived for the interaction of a weak normal shock wave and a turbulent boundary layer along a plane wall. In the case studied the nondimensional friction velocity is small in comparison with the nondimensional shock strength, and the shock wave extends well into the boundary layer. Analytical results are described for the local pressure distribution and wall shear, and a criterion for incipient separation is proposed. A comparison of predicted pressures with available experimental data includes the effect of longitudinal wall curvature

Asymptotic methods for internal transonic flows

For many internal transonic flows of practical interest, some of the relevant nondimensional parameters typically are small enough that a perturbation scheme can be expected to give a useful level of numerical accuracy. A variety of steady and unsteady transonic channel and cascade flows is studied with the help of systematic perturbation methods which take advantage of this fact. Asymptotic representations are constructed for small changes in channel cross-section area, small flow deflection angles, small differences between the flow velocity and the sound speed, small amplitudes of imposed oscillations, and small reduced frequencies. Inside a channel the flow is nearly one-dimensional except in thin regions immediately downstream of a shock wave, at the channel entrance and exit, and near the channel throat. A study of two-dimensional cascade flow is extended to include a description of three-dimensional compressor-rotor flow which leads to analytical results except in thin edge regions which require numerical solution. For unsteady flow the qualitative nature of the shock-wave motion in a channel depends strongly on the orders of magnitude of the frequency and amplitude of impressed wall oscillations or fluctuations in back pressure. One example of supersonic flow is considered, for a channel with length large compared to its width, including the effect of separation bubbles and the possibility of self-sustained oscillations. The effect of viscosity on a weak shock wave in a channel is discussed

Interaction between a normal shock wave and a turbulent boundary layer at high transonic speeds. Part 1: Pressure distribution

Analytical solutions are derived which incorporate additional physical effects as higher order terms for the case when the sonic line is very close to the wall. The functional form used for the undisturbed velocity profile is described to indicate how various parameters will be calculated for later comparison with experiment. The basic solutions for the pressure distribution are derived. Corrections are added for flow along a wall having longitudinal curvature and for flow in a circular pipe, and comparisons with available experimental data are shown

Interaction between a normal shock wave and a turbulent boundary layer at high transonic speeds. Part 1: Pressure distribution. Part 2: Wall shear stress. Part 3: Simplified formulas for the prediction of surface pressures and skin friction

An asymptotic description is derived for the interaction between a shock wave and a turbulent boundary layer in transonic flow, for a particular limiting case. The dimensionless difference between the external flow velocity and critical sound speed is taken to be much smaller than one, but large in comparison with the dimensionless friction velocity. The basic results are derived for a flat plate, and corrections for longitudinal wall curvature and for flow in a circular pipe are also shown. Solutions are given for the wall pressure distribution and the shape of the shock wave. Solutions for the wall shear stress are obtained, and a criterion for incipient separation is derived. Simplified solutions for both the wall pressure and skin friction distributions in the interaction region are given. These results are presented in a form suitable for use in computer programs

Expansion Procedures and Similarity Laws for Transonic Flow Part I. Slender Bodies at Zero Incidence

The purpose of this report is to provide a detailed and comprehensive account of a transonic approximation as applied to flows past wings and bodies. It is mainly concerned with the derivation of approximate equations, boundary conditions, etc., rather than with the more difficult problem of the solution of transonic flow problems. Thus the report contains for the most part a re-examination of the basic ideas, as presented for example, in Ref. 1. The essential new point of view introduced here is to regard the approximate transonic equations as part of a systematic expansion procedure. Thus, it becomes possible, in principle, to compute the higher terms of this approximation or at least to estimate errors. In the next section the form of the expansion and the reasons for it are explained. In the succeeding sections the equations of motion, shock relations, and boundary conditions for the flow problem are presented and then the expansion procedure is applied systematically. The resulting system of equations for the first, second, and higher approximations i s presented in Section 5. The main results of interest for practical applications concern similarity laws and the pressure coefficient on the surface of slender bodies and these appear in Section 6. The remaining section treats bodies of non-circular cross-section

Strip blowing from a wedge at hypersonic speeds

Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/76052/1/AIAA-12372-854.pd

Transonic small-disturbance theory for lightly loaded cascades

Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/76863/1/AIAA-7841-736.pd

The vertical plate in laminar free convection: Effects of leading and trailing edges and discontinuous temperature

For laminar free-convection flow past a heated vertical plate of finite length, the local asymptotic flow structure is studied in regions where the boundary-layer equations do not provide a correct approximation at large Grashof numbers. The leading-edge region is shown to contribute a secondorder term to the integrated heat transfer. An integral form of the energy equation permits calculation of this correction in terms of the second-order boundary-layer solution away from the edge, without knowledge of the flow details near the edge, which can be obtained only by solution of the full Navier-Stokes equations. Near the trailing edge and near a jump in the prescribed plate temperature the longitudinal pressure gradient is found to be important in a thin sublayer adjacent to the plate, and the transverse pressure gradient is important in the remainder of the boundary layer, each for a distance along the plate which is slightly larger in order of magnitude than the boundary-layer thickness. At the trailing edge the sublayer problem is nonlinear and cannot be solved analytically, but it can be shown that the local correction to the total heat transfer is of slightly larger order of magnitude than the leading-edge correction. It is pointed out that the trailing-edge flow is identical in form to the flow near the edge of a rotating disc in a stationary fluid. The temperature-jump problem is linear and a solution is given which shows how the singularity in streamline slope predicted by the boundary-layer solution is removed. Bei laminarer natürlicher Strömung längs einer senkrecht stehenden endlichen geheizten Platte bei sehr grossen Grashof'schen Zahlen gibt es kleine Bereiche, bei denen die Grenzschichtgleichungen keine echte asymptotische Darstellung liefern. Im Vorderkantenbereich findet man ein Zusatzglied zweiter Ordnung für die gesamte Wärmeübertragung. Die Berechnung dieser Korrektur erfolgt durch eine Integralform der Energiegleichung, wobei nur die Lösung der Grenzschichtgleichung zweiter Ordnung fern von der Kante benützt wird, während die Kenntnis der Strömung in der Nähe der Kante nur durch eine Lösung der exakten Navier-Stokes'schen Gleichungen gefunden werden könnte. In der Nähe der Hinterkante und in der Nähe einer Diskontinuität der gegebenen Plattentemperatur wird das Längsdruckgefälle in einer dünnen Unterschicht wichtig; das Querdruckgefälle wird in dem restlichen Teil der Grenzschicht berücksichtigt, für eine Länge, deren Grössenordnung etwas grösser ist, als die der Grenzschichtdicke. Bei der Hinterkante ist das Unterschichtsproblem nicht linear, und es gibt keine analytische Lösung, aber man kann zeigen, dass die Grössenordnung der Korrektur der gesamten Wärmeübertragung etwas grösser ist als die Korrektur bei der Vorderkante. Die Strömung bei der Hinterkante ist dieselbe wie die Strömung bei der Kante einer rotierenden Scheibe in einer sonst ruhenden Flüssigkeit. Das Temperatur-Diskontinuitätsproblem ist linear, und eine Lösung ist hier gefunden worden, wodurch die von der Grenzschichttheorie gegebene Singularität (unendliche Quergeschwindigkeit) entfernt wird.Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/43360/1/33_2005_Article_BF01591175.pd

Unsteady transonic cascade fow with in-passage shock wave

Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/76409/1/AIAA-25179-720.pd