Difference between revisions of "UFR 2-12 Test Case"
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Revision as of 09:59, 27 October 2012
Turbulent Flow Past Two-Body Configurations
Contents
Flows Around Bodies
Underlying Flow Regime 2-12
Test Case Study
Brief Description of the Study Test Case
A detailed description of the chosen test case (TC with L = 3.7D) is available at this link. So here we present only its brief overview.
A schematic of the airflow past the TC configuration is shown in Figure 1.
The model is comprised of two cylinders of equal diameter aligned with the streamwise flow direction.
The polar angle, , is measured from the upstream stagnation point and is positive
in the clockwise direction.
Figure 1: Schematic of TC configuration [3] |
Geometric and regime parameters defining the test case are summarized in
Table 1.
Parameter | Notation | Value |
---|---|---|
Reynolds number | Re= | 1.66×10^{5} |
Mach number | M | 0.128 |
Separation distance | 3.7 | |
TC aspect ratio | 12.4 | |
Cylinder diameter | 0.05715 m | |
Free stream velocity | 44 m/s | |
Free stream turbulence intensity | 0.1% |
The principal measured quantities by which the success or failure of CFD calculations are to be judged are as follows:
- Mean Flow
- Distributions of time-averaged pressure coefficient, , over the surface of both cylinders;
- Distribution of time-averaged mean streamwise velocity along a line connecting the centres of the cylinders;
- Unsteady Characteristics
- Distributions of the root-mean-square (rms) of the pressure coefficient over the surface of both cylinders;
- Power spectral density of the pressure coefficient (dB/Hz versus Hz) on the upstream cylinder at = 135°;
- Power spectral density of the pressure coefficient (dB/Hz versus Hz) on the downstream cylinder at = 45°;
- Turbulence kinetic energy
- x – y cut of the field of time-averaged two-dimensional turbulent kinetic energy ;
- 2D TKE distribution along* y = 0;
- 2D TKE distribution along* x = 1.5 D (in the gap between the cylinders);
- 2D TKE distribution along* x = 4.45 D (0.75 D downstream of the centre of the rear cylinder).
All these and some other data are available on the web site of the BANC-I Workshop.
Test Case Experiments
A detailed description of the experimental facility and measurement techniques is given in the original publications [2-4] and available on the web site of the BANC-I Workshop. So here we present only concise information about these aspects of the test case.
Figure 2: TC configuration in the BART facility [3] |
Experiments have been conducted in the Basic Aerodynamic Research Tunnel (BART) at NASA Langley Research Center
(see Figure 2).
This is a subsonic, atmospheric wind-tunnel for investigation of the fundamental characteristics of complex flow-fields.
The tunnel has a closed test section with a height of 0.711 m, a width of 1.016 m, and a length of 3.048 m.
The span size of the cylinders was equal to the entire BART tunnel height, thus resulting in the aspect ratio
L_{z} / D = 12.4.
The free stream velocity was set to 44 m/s giving a Reynolds number based on cylinder diameter equal to
1.66 × 10^{5} and Mach number equal to 0.128 (flow temperature T = 292 K).
The free stream turbulence level was less than 0.10%.
In the first series of the experiments [2, 3],
in order to ensure a turbulent separation from the upstream cylinder
at the considered Reynolds number, the boundary layers on this cylinder were tripped between azimuthal locations of
50 and 60 degrees from the leading stagnation point using a transition strip.
For the downstream cylinder, it was assumed that trip-like effect of turbulent wake impingement from the upstream cylinder
would automatically ensure turbulent separation.
However, later on [4]
it was found that the effect of tripping of the downstream cylinder at L/D = 3.7
is also rather tangible (resulted in reduced peaks in mean C_{p} distribution along the rear cylinder,
accompanied by an earlier separation from the cylinder surface, a reduced pressure recovery, lower levels of mean TKE
in the wake and reduced levels of peak surface pressure fluctuations).
For this reason, exactly these (with tripping of both cylinders) experimental data
[4] were used for the comparison
with fully turbulent CFD.
In the course of experiments, steady and unsteady pressure measurements were carried out along with 2-D Particle Image
Velocimetry (PIV) and hot-wire anemometry used for documenting the flow interaction around the two cylinders
(mean streamlines and instantaneous vorticity fields, shedding frequencies and spectra).
Information on the data accuracy available in the original publications
[2-4] is summarized in Table 2.
Most absolute values are given based on nominal tunnel conditions or on an average data value.
Percentage values are quoted for parameters where the uncertainty equations were posed in terms of the uncertainty relative
to the nominal value of the parameter.
Quantity | Uncertainty |
---|---|
Steady C_{p} | 0.02 |
Drag Coefficient | 0.0005 |
PIV: U_{mean}, V_{mean} | 0.03 (normalized) |
PIV: Spanwise velocity | 1.8 (normalized) |
PIV: TKE | 4% |
Power Spectral Density (PSD) | 10 – 20% |
C_{p}' rms | 5 – 11% |
Diameter, D; Sensor spacing Δz | 0.005 inch |
CFD Methods
The key physical features of the UFR (Section 1) present significant difficulties for all the existing approaches to turbulence representation, whether from the standpoint of solution fidelity (for the conventional (U)RANS models) or in terms of computational expense for full LES (especially if the turbulent boundary layers are to be resolved). For this reason, most of the computational studies of multi-body flows, in general, and the TC configuration, in particular, are currently relying upon hybrid RANS-LES approaches. This is true also with regard to simulations carried out in the course of the BANC-I and II Workshops and in the framework of the ATAAC project, where different hybrid RANS-LES models of the DES type were used (see Table 3) ^{[1]}.
Partner | Turbulence Modelling approach | Compressible/Incompressible | L_{z} | Grid | Side Walls |
---|---|---|---|---|---|
Beijing Tsinghua University BTU | SST DDES | Compressible | 3D | Mandatory | Slip |
German Aerospace Center, Göttingen DLR | SA DDES | Compressible | 3D | Mandatory | Slip |
New Technologies and Services, St.-Petersburg, Russia NTS | SA DDES
SA IDDES |
Incompressible and Compressible | 3D, 16D | Mandatory | Slip |
Technische Universität Berlin TUB | SA DDES
SA IDDES |
Incompressible | 3D | Mandatory | Slip |
Contributed by: A. Garbaruk, M. Shur and M. Strelets — New Technologies and Services LLC (NTS) and St.-Petersburg State Polytechnic University
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