Example of Integrated CFD and Experimental Studies ... - CFD4Aircraft
Example of Integrated CFD and Experimental Studies ... - CFD4Aircraft
Example of Integrated CFD and Experimental Studies ... - CFD4Aircraft
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<strong>Example</strong> <strong>of</strong> <strong>Integrated</strong> <strong>CFD</strong><br />
<strong>and</strong> <strong>Experimental</strong> <strong>Studies</strong>:<br />
Design <strong>of</strong> Flow Control in the<br />
FOI-EIC-01 Inlet<br />
Adam Jirásek<br />
Swedish Defence Research<br />
Agency FOI<br />
3 rd International Symposium on Integrating <strong>CFD</strong> <strong>and</strong> Experiments in Aerodynamics<br />
the US Air Force Academy<br />
Colorado Springs, CO, USA<br />
June 21 st –22 nd , 2007
Propulsion Integration project<br />
Conceptual study <strong>of</strong> a UAV propulsion<br />
FOI<br />
Volvo Aeronautics Company<br />
SAAB Aerospace<br />
Financed by Swedish Defence Materiel<br />
Administration, FMV<br />
3 rd International Symposium on Integrating <strong>CFD</strong> <strong>and</strong> Experiments in Aerodynamics<br />
the US Air Force Academy<br />
Colorado Springs, CO, USA<br />
June 21 st –22 nd , 2007
Propulsion integration project<br />
Aerodynamics<br />
Aeroelasticity<br />
Structure <strong>and</strong> materials<br />
Signature studies<br />
3 rd International Symposium on Integrating <strong>CFD</strong> <strong>and</strong> Experiments in Aerodynamics<br />
the US Air Force Academy<br />
Colorado Springs, CO, USA<br />
June 21 st –22 nd , 2007
Design <strong>of</strong> flow control in inlet<br />
Problems with distortion<br />
<strong>and</strong> recovery<br />
VG restructure flow in<br />
inlet<br />
Sub-boundary layer VGs<br />
(50% δ)<br />
A number <strong>of</strong> geometrical<br />
parameters<br />
3 rd International Symposium on Integrating <strong>CFD</strong> <strong>and</strong> Experiments in Aerodynamics<br />
the US Air Force Academy<br />
Colorado Springs, CO, USA<br />
June 21 st –22 nd , 2007
Role <strong>of</strong> <strong>CFD</strong> <strong>and</strong> WT in AD<br />
<strong>CFD</strong>, WT advantages<br />
<strong>and</strong> difficulties<br />
<strong>CFD</strong><br />
Wind<br />
tunnel<br />
Advantages<br />
Geometrical modifications<br />
Reynolds number<br />
A large number <strong>of</strong> flow<br />
conditions<br />
Difficulties<br />
Time consuming to get<br />
solution<br />
Extensive or too many<br />
modifications <strong>of</strong> geometry<br />
Full scale Re<br />
Reproduced with permission,<br />
* Tinoco 1998<br />
*Tinoco, The Changing Role <strong>of</strong> Computational Fluid Dynamics in Aircraft Development, AIAA<br />
Paper 98-2512, 1998<br />
# Hamstra J. W. <strong>and</strong> Miller D. N. <strong>and</strong> Traux P. P. <strong>and</strong> Anderson B. H. <strong>and</strong> Wendt B. J., Active inlet<br />
flow control technology demonstration, Aeronautical Journal 2002(104), 2001<br />
Reproduced with permission,<br />
# Hamstra 2001<br />
3 rd International Symposium on Integrating <strong>CFD</strong> <strong>and</strong> Experiments in Aerodynamics<br />
the US Air Force Academy<br />
Colorado Springs, CO, USA<br />
June 21 st –22 nd , 2007
Flow control design within<br />
Propulsion Integration project<br />
<strong>CFD</strong>/DOE design WT testing T1500 Post-WT <strong>CFD</strong><br />
Design parameters,<br />
One design flow condition,<br />
<strong>CFD</strong>, DOE<br />
<br />
Response surface,<br />
Two VG installation<br />
3 rd International Symposium on Integrating <strong>CFD</strong> <strong>and</strong> Experiments in Aerodynamics<br />
the US Air Force Academy<br />
Colorado Springs, CO, USA<br />
June 21 st –22 nd , 2007
Phase I - <strong>CFD</strong>-DOE study (1)<br />
SSS<br />
<strong>CFD</strong> – DOE<br />
Only geometrical<br />
parameters (5-7 params.)<br />
One flow conditions<br />
CCD matrix (27-46 runs)<br />
Response surfaces<br />
Significance <strong>of</strong> factors<br />
Locus <strong>of</strong> optimum<br />
(h=27.5%d, l/h=8.25, s/h=3.5,<br />
Δx/h=6.75, α p not significant)<br />
Graphical interpretation<br />
factor t-value<br />
DC 0<br />
84.35<br />
h 13.05<br />
Δx/h 12.92<br />
Δx 9.62<br />
Δx 2 6.93<br />
h 2 6.79<br />
Δx/h 4.90<br />
s/h 4.19<br />
3 rd International Symposium on Integrating <strong>CFD</strong> <strong>and</strong> Experiments in Aerodynamics<br />
the US Air Force Academy<br />
Colorado Springs, CO, USA<br />
June 21 st –22 nd , 2007
Phase I - <strong>CFD</strong>-DOE study (2)<br />
The most important<br />
Position <strong>of</strong> separation<br />
Boundary layer thickness<br />
configuration DC 60<br />
[%] Recov.[%]<br />
w/o VGs 57.13 96.45<br />
One row 2.97 98.42<br />
Two row 5.96 98.30<br />
3 rd International Symposium on Integrating <strong>CFD</strong> <strong>and</strong> Experiments in Aerodynamics<br />
the US Air Force Academy<br />
Colorado Springs, CO, USA<br />
June 21 st –22 nd , 2007
Phase II - WT test<br />
WT model, FOI 1500 WT<br />
3 rd International Symposium on Integrating <strong>CFD</strong> <strong>and</strong> Experiments in Aerodynamics<br />
the US Air Force Academy<br />
Colorado Springs, CO, USA<br />
June 21 st –22 nd , 2007
Phase II - WT test<br />
WT test results<br />
M=0.85, three Re numbers<br />
max. value <strong>of</strong> corrected mass flow<br />
w/o VGs<br />
Two row VGs<br />
Re w/o VGs with VGs<br />
x10 6 DC 60<br />
Recov DC 60<br />
Recov<br />
2.9 56.2 94.7 24.3 94.6<br />
5.9 53.5 95.1 11.5 95.4<br />
7.0 52.5 95.1 21.6 95.3<br />
Re 2.9 mil 5.9 mil 7.0 mil<br />
3 rd International Symposium on Integrating <strong>CFD</strong> <strong>and</strong> Experiments in Aerodynamics<br />
the US Air Force Academy<br />
Colorado Springs, CO, USA<br />
June 21 st –22 nd , 2007
Phase III – Post-WT <strong>CFD</strong> analysis<br />
Direct analysis <strong>of</strong> WT test<br />
Additional vortices in sector 5,7<br />
Analysis <strong>of</strong> effect <strong>of</strong> Re<br />
Test at different flight<br />
conditions<br />
Missing VGs<br />
All VGs<br />
Missing VG<br />
Test <strong>of</strong> different VGs<br />
3 rd International Symposium on Integrating <strong>CFD</strong> <strong>and</strong> Experiments in Aerodynamics<br />
the US Air Force Academy<br />
Colorado Springs, CO, USA<br />
June 21 st –22 nd , 2007
Conclusion<br />
Technical level<br />
Tools <strong>and</strong> procedures for design <strong>of</strong> VG flow<br />
control<br />
Project level<br />
Efficient use <strong>of</strong> <strong>CFD</strong> – WT interaction<br />
Planning<br />
<strong>CFD</strong> design with geometrical parameters<br />
Evaluation <strong>of</strong> Reynolds number effect<br />
Study <strong>of</strong> wind tunnel test<br />
Can help in planning WT campaign<br />
3 rd International Symposium on Integrating <strong>CFD</strong> <strong>and</strong> Experiments in Aerodynamics<br />
the US Air Force Academy<br />
Colorado Springs, CO, USA<br />
June 21 st –22 nd , 2007
Acknowledgment<br />
Swedish Defence Materiel Administration, FMV,<br />
is acknowledged for financing the project<br />
3 rd International Symposium on Integrating <strong>CFD</strong> <strong>and</strong> Experiments in Aerodynamics<br />
the US Air Force Academy<br />
Colorado Springs, CO, USA<br />
June 21 st –22 nd , 2007
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