Table of Contents

Wing-Body Junction Flow

Experiments by Ölçmen and Simpson


Description

A three dimensional, pressure driven turbulent boundary layer created by a wing-body junction flow was experimentally studied. The geometry is shown in figure 1.

 Flow geometryFig. 1: Flow geometry

The wing used was a 3:2, semi-elliptical nosed NACA 0020 tailed symmetric profile which has a chord length of 30.5 cm (12 in.), maximum thickness of 7.17 cm (2.824 in.), and height of 22.9 cm (9.016 in.). The wing was mounted on the centreline of the flat plate wind tunnel floor. The nominal reference velocity of the flow was 27.5 m/s and the Reynolds number based on the momentum thickness at 0.75 chord upstream of the wing on the centreline of the tunnel and wing was \(Re_{\theta} = 5936\).

The data available includes the mean velocity and all Reynolds stresses at several (\(x\), \(z\)) stations on a line determined by translating in the direction of the mean velocity vector component parallel to the wall in the layer where the \(\overline{u^2}\) normal stress is maximum. Time-mean static pressure at a number of locations on the base wall and wing surface was also measured.

Measurement Details

Data were obtained both with hot-wire (HW, at 24 stations) and laser Doppler-velocimeter (LDV, at 8 stations) techniques. The locations of these traverses are shown in figure 2. The incoming boundary layer was also measured at 15 different stations located at a distance of 0.75 chord upstream of the wing across half of the tunnel test section.

Measurement pointsFig. 2: Hot wire and LDV measurement points (circles and triangles: hot wire points; crosses: LDV points)

Measurement Errors

The LDV measurements were taken twice due to the differences observed between the HW and the LDV data. The uncertainties in the mean velocity and the stresses were examined extensively.

Available measurements

Data available include:

Sample plots of selected quantities are available.

The data can be downloaded as compressed archives from the links below, or as individual files.

The file readme.txt has information on the data file naming and contents.

Pressure coefficients:

cp-far.dat \(C_p\) in the farfield, along lines \(z/T=\pm 3.17\)
cp-wall.dat \(C_p\) on the test wall surrounding the wing
cp-nose.dat \(C_p\) around the nose
cp-on.dat \(C_p\) on the wing surface

LDV and hot-wire profiles:
Other than for the upstream locations, three files are given for each profile, corresponding to the velocities being expressed in three different coordinate systems. “tc” denotes Tunnel Coordinates, where the \(x\)-axis is along the symmetry line of the wing. “fs” denotes Free-Stream Coordinates, where the positive \(x\)-axis is in the direction of the mean velocity at the boundary layer edge. “ns” denotes Normal Stress Coordinates, where the positive \(x\)-axis is in the direction of the local mean velocity vector parallel to the tunnel floor at the \(y\) location where the normal stress \(\overline{u^2}\) is maximum.

Upstream hot-wire velocity and Reynolds stress profiles (at \(x/C=-0.75\))
Location Station ID File
\(z/T=0\) hw-up01 hw-up01-tc.dat
\(z/T=0.25\) hw-up02 hw-up02-tc.dat
\(z/T=0.5\) hw-up03 hw-up03-tc.dat
\(z/T=0.75\) hw-up04 hw-up04-tc.dat
\(z/T=1\) hw-up05 hw-up05-tc.dat
\(z/T=1.25\) hw-up06 hw-up06-tc.dat
\(z/T=1.5\) hw-up07 hw-up07-tc.dat
\(z/T=1.75\) hw-up08 hw-up08-tc.dat
\(z/T=2\) hw-up09 hw-up09-tc.dat
\(z/T=2.25\) hw-up10 hw-up10-tc.dat
\(z/T=2.5\) hw-up11 hw-up11-tc.dat
\(z/T=2.75\) hw-up12 hw-up12-tc.dat
\(z/T=3.25\) hw-up14 hw-up14-tc.dat
\(z/T=3.75\) hw-up16 hw-up16-tc.dat
\(z/T=4.25\) hw-up18 hw-up17-tc.dat
Right Hand Side of Wing
Hot-wire data LDV data
Location Station ID Files Station ID Files
\(x/C=-0.374\); \(z/T=-0.466\) ldv00 ldv00-tc.dat
ldv00-fs.dat
ldv00-ns.dat
\(x/C=-0.291\); \(z/T=-0.513\) hw-rhs01 hw-rhs01-tc.dat
hw-rhs01-fs.dat
hw-rhs01-ns.dat
ldv01 ldv01-tc.dat
ldv01-fs.dat
ldv01-ns.dat
\(x/C=-0.190\); \(z/T=-0.621\) hw-rhs02 hw-rhs02-tc.dat
hw-rhs02-fs.dat
hw-rhs02-ns.dat
ldv02 ldv02-tc.dat
ldv02-fs.dat
ldv02-ns.dat
\(x/C=-0.110\); \(z/T=-0.721\) hw-rhs03 hw-rhs03-tc.dat
hw-rhs03-fs.dat
hw-rhs03-ns.dat
ldv03 ldv03-tc.dat
ldv03-fs.dat
ldv03-ns.dat
\(x/C=-0.039\); \(z/T=-0.914\) hw-rhs04 hw-rhs04-tc.dat
hw-rhs04-fs.dat
hw-rhs04-ns.dat
ldv04 ldv04-tc.dat
ldv04-fs.dat
ldv04-ns.dat
\(x/C=0.022\); \(z/T=-1.042\) ldv05 ldv05-tc.dat
ldv05-fs.dat
ldv05-ns.dat
\(x/C=0.099\); \(z/T=-1.167\) hw-rhs06 hw-rhs06-tc.dat
hw-rhs06-fs.dat
hw-rhs06-ns.dat
ldv06 ldv06-tc.dat
ldv06-fs.dat
ldv06-ns.dat
\(x/C=0.180\); \(z/T=-1.250\) hw-rhs07 hw-rhs07-tc.dat
hw-rhs07-fs.dat
hw-rhs07-ns.dat
ldv07 ldv07-tc.dat
ldv07-fs.dat
ldv07-ns.dat
Left Hand Side of Wing (Hot-wire data)
Location Station ID Files
\(x/C=0.305\); \(z/T=1.302\) hw-lhs01 hw-lhs01-tc.dat
hw-lhs01-fs.dat
hw-lhs01-ns.dat
\(x/C=0.222\); \(z/T=1.275\) hw-lhs02 hw-lhs02-tc.dat
hw-lhs02-fs.dat
hw-lhs02-ns.dat
\(x/C=0.180\); \(z/T=1.249\) hw-lhs03 hw-lhs03-tc.dat
hw-lhs03-fs.dat
hw-lhs03-ns.dat
\(x/C=0.140\); \(z/T=1.122\) hw-lhs04 hw-lhs04-tc.dat
hw-lhs04-fs.dat
hw-lhs04-ns.dat
\(x/C=0.099\); \(z/T=1.167\) hw-lhs05 hw-lhs05-tc.dat
hw-lhs05-fs.dat
hw-lhs05-ns.dat
\(x/C=0.061\); \(z/T=1.104\) hw-lhs06 hw-lhs06-tc.dat
hw-lhs06-fs.dat
hw-lhs06-ns.dat
\(x/C=0.022\); \(z/T=1.041\) hw-lhs07 hw-lhs07-tc.dat
hw-lhs07-fs.dat
hw-lhs07-ns.dat
\(x/C=0.016\); \(z/T=0.965\) hw-lhs08 hw-lhs08-tc.dat
hw-lhs08-fs.dat
hw-lhs08-ns.dat
\(x/C=-0.039\); \(z/T=0.913\) hw-lhs09 hw-lhs09-tc.dat
hw-lhs09-fs.dat
hw-lhs09-ns.dat
\(x/C=-0.075\); \(z/T=0.824\) hw-lhs10 hw-lhs10-tc.dat
hw-lhs10-fs.dat
hw-lhs11-ns.dat
\(x/C=-0.111\); \(z/T=0.721\) hw-lhs11 hw-lhs11-tc.dat
hw-lhs11-fs.dat
hw-lhs11-ns.dat
\(x/C=-0.150\); \(z/T=0.666\) hw-lhs12 hw-lhs12-tc.dat
hw-lhs12-fs.dat
hw-lhs12-ns.dat
\(x/C=-0.191\); \(z/T=0.620\) hw-lhs13 hw-lhs13-tc.dat
hw-lhs13-fs.dat
hw-lhs13-ns.dat
\(x/C=-0.230\); \(z/T=0.562\) hw-lhs14 hw-lhs14-tc.dat
hw-lhs14-fs.dat
hw-lhs14-ns.dat
\(x/C=-0.291\); \(z/T=0.513\) hw-lhs15 hw-lhs15-tc.dat
hw-lhs15-fs.dat
hw-lhs15-ns.dat
\(x/C=-0.374\); \(z/T=0.466\) hw-lhs16 hw-lhs16-tc.dat
hw-lhs16-fs.dat
hw-lhs16-ns.dat
\(x/C=-0.540\); \(z/T=0.398\) hw-lhs17 hw-lhs17-tc.dat
hw-lhs17-fs.dat
hw-lhs17-ns.dat
\(x/C=-0.790\); \(z/T=0.382\) hw-lhs18 hw-lhs18-tc.dat
hw-lhs18-fs.dat
hw-lhs18-ns.dat

References

  1. Ölçmen, M.S., Simpson, R.L. (1992). Perspective: On the near wall similarity of three-dimensional turbulent boundary layers. Journal of Fluids Engineering, Vol. 114, pp. 487-495.
  2. Ölçmen, S.M., Simpson, R.L. (1995). An experimental study of a three-dimensional pressure-driven turbulent boundary layer. J. Fluid Mech., Vol. 290, pp. 225-262.

Indexed data:

case063 (dbcase, flow_around_body, semi_confined_flow)
case063
titleWing-body junction flow
authorOlcmen, Simpson
year1990
typeEXP
flow_tag3d, surface_mounted_body