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Turbulent boundary-layer studies at high Reynolds numbers at mach numbers between 0.2 and 2.8

31 Dec 1970-
TL;DR: In this paper, the authors measured the turbulent boundary layer on the sidewall of the RAE 8ft x 8ft wind tunnel and used a large strain-gauge balance, together with velocity and temperature profiles.
Abstract: Measurements of the turbulent boundary layer on the sidewall of the RAE 8ft x 8ft wind tunnel are described. The measurements consisted of surface shearing stress, using a large strain-gauge balance, together with velocity and temperature profiles. Maximum Reynolds numbers, based on an effective streamwise run, range from about 200 million at M = 0.2 to 60 million at M = 2.8. The analysis of the results shows that accepted descriptions of turbulent boundary layers in incompressible flow, derived from the concept of a universal velocity defect law, are preserved for compressible flows if the boundary-layer parameters are expressed in kinematic form. This leads to a simple method of calculating skin friction and velocity profiles for constant pressure flows without heat transfer.
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TL;DR: In this article, a reformulated version of the author's k-ω model of turbulence has been presented, which has been applied to both boundary layers and free shear flows and has little sensitivity to finite freestream boundary conditions on turbulence properties.
Abstract: This paper presents a reformulated version of the author'sk-ω model of turbulence. Revisions include the addition of just one new closure coefficient and an adjustment to the dependence of eddy viscosity on turbulence properties. The result is a significantly improved model that applies to both boundary layers and free shear flows and that has very little sensitivity to finite freestream boundary conditions on turbulence properties. The improvements to the k-ω model facilitate a significant expansion of its range of applicability. The new model, like preceding versions, provides accurate solutions for mildly separated flows and simple geometries such as that of a backward-facing step. The model's improvement over earlier versions lies in its accuracy for even more complicated separated flows. This paper demonstrates the enhanced capability for supersonic flow into compression corners and a hypersonic shock-wave/ boundary-layer interaction. The excellent agreement is achieved without introducing any compressibility modifications to the turbulence model.

882 citations


Cites background from "Turbulent boundary-layer studies at..."

  • ...Wieghardt and Tillman [33] (squares), and Winter and Gaudet [34]...

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Journal ArticleDOI
TL;DR: The available data describing the incompressible zero-pressure gradient boundary layer are reviewed in association with a range of studies which are either new or, to date, not very generally available as discussed by the authors.

403 citations

Journal ArticleDOI
TL;DR: It is generally accepted that the direct effects of density fluctuations on turbulence are small if the root-mean-square density fluctuation is small compared with the absolute density: this is Morkovin's hypothesis.
Abstract: It is generally accepted that the direct effects of density fluctuations on turbulence are small if the root-mean-square density fluctuation is small compared with the absolute density: this is Morkovin's hypothesis (Favre 1964, p. 367). This means that the turbulence structure of boundary layers and wakes at free-stream Mach numbers Me less than about 5, and of jets at Mach numbers less than about 1.5, is closely the same as in the corrcsponding constant-density flow. By "turbulence structure" we mean dimensionless properties like correlation coefficients and spectrum shapes: the skin-friction coefficient cf == Tw/tPeU; and other ratios of turbulence quantities to mean flow quantities are greatly affected by the influence of mean density changes on the mean motion. The effect of mean density variations in x or y on the turbulence structure is not covered by Morkovin's hypothesis, but is often negligible at the lower Mach numbers if stream wise pressure gradients are small. Therefore assumptions about turbulence structure that give good results in calculation methods for constant-density /low will, if properly scaled, give good results in compressible boundary layers or wakes for Me 5, say. Basic equations for compressible shear layers are given by Howarth (1953) and Lin (1959). More recent treatments (FavJe 1971, Cebeci & Smith 1974, Rubesin & Rose 1973, Bilger 1975) use "mass-weighted" variables, which remove density iluctuations from the time-averaged equations of motion but not from the turbulence or from the response of measuring instruments (although Laufer, in Birch et aI1972, p. 462, suggests that pitot tubes probably yield mass-averaged velocities). It seems probable that the difference between conventional and mass-weighted averages rises more slowly with Mach number than current errors in measuring either. Of problems 1 The author is grateful for a number of helpful comments or contributions, especialIy

363 citations

Journal ArticleDOI
TL;DR: In this article, the authors discuss force-measurement balances, the use of the velocity profile, pressure measurements by surface pitot tubes or about obstacles, and the analogies of heat transfer, mass transfer or surface oil flow.

337 citations

Journal ArticleDOI
TL;DR: In this article, the effects of spanwise distribution on the aircraft aerodynamic efficiency were studied through an inverse twist design approach, combining both a low fidelity panel method and a high-fidelity Reynolds-averaged Navier-Stokes solution method.

210 citations


Cites methods from "Turbulent boundary-layer studies at..."

  • ...00653 using the flat plate turbulent boundary layer correlation law [22,23]....

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