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Research Papers: Flows in Complex Systems

The Effects of Splitter Plates on Turbulent Boundary Layer on a Long Flat Plate Near the Trailing Edge

[+] Author and Article Information
Yoshifumi Jodai

Department of Mechanical Engineering, Takamatsu College of Technology, 761-8058 Takamatsu, Japanjodai@takamatsu-nct.ac.jp

Yoshikazu Takahashi

Department of Mechanical Engineering, Takamatsu College of Technology, 761-8058 Takamatsu, Japantakahasi@takamatsu-nct.ac.jp

Masashi Ichimiya

Department of Mechanical Engineering, University of Tokushima, Japanichimiya@me.tokushima-u.ac.jp

Hideo Osaka

Department of Mechanical Engineering, Yamaguchi University, Japanohsaka@po.cc.yamaguchi-u.ac.jp

J. Fluids Eng 130(5), 051103 (May 01, 2008) (7 pages) doi:10.1115/1.2911683 History: Received August 29, 2007; Revised January 23, 2008; Published May 01, 2008

Abstract

An experimental investigation has been made on a turbulent boundary layer near the trailing edge on a long flat plate. The flow was controlled by an additional splitter plate fitted to the trailing edge along the wake centerline. The length of the splitter plate, $l$, was varied from a half, to five times the trailing edge thickness, $h$. Measurements of base pressure behind the trailing edge and of mean velocity and pressure distribution in the turbulent boundary layer on the flat plate were made under the freestream zero-pressure gradient. The absolute value of the base pressure coefficient of the long flat plate was considerably smaller than that of the short flat plate without the splitter plate. A significant increase in the base pressure coefficient was achieved with the splitter plate $(l∕h≧1)$, fitted to the long flat plate. Within an inner layer in the turbulent boundary layer near the trailing edge, the mean velocity increased more than that in the upstream position in the case without the splitter plate. With the splitter plate, however, the base pressure rise made the mean velocity distribution more closely approach that of a fully developed turbulent boundary layer.

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Figures

Figure 6

Static pressure coefficient. Uncertainty: around 1% and 4% for boundary-layer pressure −8Pa(Cp∼−0.060) and −2Pa(Cp∼−0.015), respectively.

Figure 7

Momentum thickness and Clauser’s shape parameter

Figure 8

Local skin friction coefficient. (a) cf for x∕h; (b) cf for Rθ.

Figure 9

Wake parameter

Figure 5

Mean velocity excess

Figure 4

Mean velocity profiles. Uncertainty: less than 2% for velocities ranging from 4m∕sto16m∕s(U∕Ue≒0.25–1) and around 5% for lower velocities.

Figure 3

Normalized base pressure coefficient

Figure 2

Base pressure coefficient. Uncertainty: less than 1% for base pressure ranging from about −40Pa(Cpb∼−0.3) to −15Pa(Cpb∼−0.1).

Figure 1

Configuration of flow field and coordinate system

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