The intermediate wake of a body of revolution at high Reynolds numbers

Abstract

Results are presented on the flow field downstream of a body of revolution for Reynolds numbers based on a model length ranging from 1.1 × 106 to 67 × 106. The maximum Reynolds number is more than an order of magnitude larger than that obtained in previous laboratory wake studies. Measurements are taken in the intermediate wake at locations 3, 6, 9, 12 and 15 diameters downstream from the stern in the midline plane. The model is based on an idealized submarine shape (DARPA SUBOFF), and it is mounted in a wind tunnel on a support shaped like a semi-infinite sail. The mean velocity distributions on the side opposite the support demonstrate self-similarity at all locations and Reynolds numbers, whereas the mean velocity distribution on the side of the support displays significant effects of the support wake. None of the Reynolds stress distributions of the flow attain self-similarity, and for all except the lowest Reynolds number, the support introduces a significant asymmetry into the wake which results in a decrease in the radial and streamwise turbulence intensities on the support side. The distributions continue to evolve with downstream position and Reynolds number, although a slow approach to the expected asymptotic behaviour is observed with increasing distance downstream.

A numerical investigation of the wake of an axisymmetric body with appendages

“…Similar results were reported by Bhushan et al (2013), who simulated the appended DSub at Re L = 12 × 10 6 by URANS, DES and hybrid RANS/implicit LES: the C p distribution was predicted equally well by all methods, while C f was best captured by the hybrid RANS/LES methodology. In our computations the overall evolution of C p agrees with the results by Jiménez et al (2010a), although there is an offset. Jiménez et al (2010a) suggested that this offset is likely caused by a different value of the reference pressure.…”

“…The variation along the plane a, for both negative (location 1) and positive (location 2) y coordinates, and the average along planes c1 and c2 (location 3) are shown (see figure 4 for the definition of the different planes). The experimental results by Huang et al (1994) and Jiménez et al (2010a) as well as the computations by Gorski et al (1990) are included. In both experiments the geometry has no stern appendages, while the Reynolds numbers are 12 × 10 6 and 1.1 × 10 6 , respectively.…”

Spatial resolution correction for wall-bounded turbulence measurements

“…Accordingly, a number of new facilities that provide detailed access to high Reynolds number flows have been commissioned, including the Princeton/ONR Superpipe (Zagarola & Smits 1998) and High Reynolds Number Test Facility (Jiménez, Hultmark & Smits 2010), the Stanford pressurized wind tunnel (DeGraaff & Eaton 2000), the MTL wind tunnel at KTH (Österlund et al 2000), the National Diagnostic Facility at IIT (Nagib, Chauhan & Monkewitz 2007) and the High Reynolds Number Boundary Layer Wind Tunnel at the University of Melbourne (Nickels et al 2007). In addition, the Surface Layer Turbulence and Environmental Science Test (SLTEST) facility in Utah (Metzger & Klewicki 2001) has provided high quality data in the atmospheric boundary layer, which has been invaluable for studying the behaviour at Reynolds numbers one or two orders of magnitude larger than what is possible in the laboratory.…”

Development of Turbulent Wakes Evolving from Asymmetric Shear Layers

“…Furthermore, for the ATT cases, the traditional scaling adopted in the ST case failed to collapse the profiles of ū ′ 2 and u ′ v ′ particularly at high θ/θ 0 . As seen in the scaled mean flow profiles (Figures 2 and 5a to 5c), the lack of collapse in the perturbed side was clearly highlighted in the profiles of u ′ v ′ /U d 2 , indicating that the similarity of the asymmetric cases was incomplete and that their wakes were still evolving slowly in the streamwise direction towards a well-established asymptotic state [19].…”