Comparison of Detached Eddy Simulations with Turbulence Modeling
Flow field around hypersonic vehicles is very
complex and difficult to simulate. The boundary layers are squeezed
between shock layer and body surface. Resolution of boundary layer,
shock wave and turbulent regions where the flow field has high
values is difficult of capture. Detached eddy simulation (DES) is a
modification of a RANS model in which the model switches to a
subgrid scale formulation in regions fine enough for LES
calculations. Regions near solid body boundaries and where the
turbulent length scale is less than the maximum grid dimension are
assigned the RANS mode of solution. As the turbulent length scale
exceeds the grid dimension, the regions are solved using the LES
mode. Therefore the grid resolution is not as demanding as pure LES,
thereby considerably cutting down the cost of the computation. In
this research study hypersonic flow is simulated at Mach 8 and
different angle of attacks to resolve the proper boundary layers and
discontinuities. The flow is also simulated in the long wake regions.
Mesh is little different than RANS simulations and it is made dense
near the boundary layers and in the wake regions to resolve it
properly. Hypersonic blunt cone cylinder body with frustrum at angle
5o and 10 o are simulated and there aerodynamics study is performed
to calculate aerodynamics characteristics of different geometries. The
results and then compared with experimental as well as with some
turbulence model (SA Model). The results achieved with DES
simulation have very good resolution as well as have excellent
agreement with experimental and available data. Unsteady
simulations are performed for DES calculations by using duel time
stepping method or implicit time stepping. The simulations are
performed at Mach number 8 and angle of attack from 0o to 10o for
all these cases. The results and resolutions for DES model found
much better than SA turbulence model.
[1] Spalart, P.R., Jou, W.-H., Strelets, M. and Allmaras, S.R., Comments on
the feasibility of LES for wings, and on a hybrid RANS/LES
approach. In: Liu, C. and Liu, Z. (eds), Advances in DNS/LES,
Proceedings of 1st AFOSR International Conference on DNS/LES,
Ruston, LA,August 4-8. Greyden Press, Columbus, OH (1997) pp. 137-
147.
[2] Spalart, P.R., Strategies for turbulence modelling and simulations.
Internat. J. Heat Fluid Flow,to appear.
[3] Shur, M., Spalart, P.R., Strelets, M. and Travin, A., Detached-eddy
simulation of an airfoil at high angle of attack. In: Rodi, W. and
Laurence, D. (eds), 4th International Symposium on Engineering
TurbulenceModelling and Measurements, Corsica, May 24-26. Elsevier,
Amsterdam (1999) pp. 669-678.
[4] Muhammad Amjad Sohail , Muhammad yamin Younis "applications of
High order low dessipitive shcme on hypersonic flow field by using min
mode limiter"CFP1070K-PRT, ISBN=11-4244-8101-9 Singapore 2010.
[5] Muhammad Amjad Sohail et al" Effect of Turbulence Modeling on
Aerodynamics characteristics of a conventional tailed finned missile
configurations" CFP1070K-PRT, ISBN=11-4244-8101-9 Singapore
2010.
[6] Muhammad Yamin Younis., Muhammad Amjad Sohail, Tawfiqur
Rahman, Zaka Muhammad, Saifur Rahman Bakaul" Applications of
AUSM+ Scheme on Subsonic, Supersonic and Hypersonic Flows
Fields" World Academy Of Science, Engineering and Technology Issue
73 January 2011
[7] J PRoos, F.W. and Kegelman, J.T., "Aerodynamic Characteristics of
Three Generic Forebodies at High Angles of Attack," AIAA Paper 91-
0275, January, 1991.).
[8] Jason M. Merret* and Michael B. Bragg" X-38 AERODYNAMICS
DURING RAPID PITCH UP" University of Illinois at Urbana-
Champaign Urbana, IL 61801AIAA 2003-3526.
[9] S. Saravanan ÔÇó G. Jagadeesh ÔÇó K. P. J. Reddy" Aerodynamic force
measurement using 3-componentaccelerometer force balance system in a
hypersonic shock tunnel" Shock Waves (2009) 18:425-435 DOI
10.1007/s00193-008-0172-8.
[10] Philipe R. Spalart "Young-s persons guide for detached eddy
simulations Grid generations" NASA/CR-2001-211032
[11] M. Shur, P. R. Spalart, M. Strelets, and A. Travin. Detached-Eddy
Simulation of an Airfoil at High Angle of Attack. In 4th Int. Symposium
on Eng. Turb. Modeling and Experiments, Corsica, France, May 1999.
[12] Scott A. Morton" High Reynolds Number Detached-Eddy Simulations
of Vortex Breakdown Over A 70 Degree Delta Wing"
[13] B. CARUELLEa, and F. DUCROSb" Detached-Eddy Simulations of
Attached and Detached Boundary Layers" International Journal of
Computational Fluid Dynamics, December 2003 Vol. 17 (6), pp. 433-
451
[14] ANDREI TRAVIN, MICHAEL SHUR, MICHAEL STRELETS and
PHILIPPE SPALART" Detached-Eddy Simulations Past a Circular
Cylinder" Flow, Turbulence and Combustion 63: 293-313, 1999
[1] Spalart, P.R., Jou, W.-H., Strelets, M. and Allmaras, S.R., Comments on
the feasibility of LES for wings, and on a hybrid RANS/LES
approach. In: Liu, C. and Liu, Z. (eds), Advances in DNS/LES,
Proceedings of 1st AFOSR International Conference on DNS/LES,
Ruston, LA,August 4-8. Greyden Press, Columbus, OH (1997) pp. 137-
147.
[2] Spalart, P.R., Strategies for turbulence modelling and simulations.
Internat. J. Heat Fluid Flow,to appear.
[3] Shur, M., Spalart, P.R., Strelets, M. and Travin, A., Detached-eddy
simulation of an airfoil at high angle of attack. In: Rodi, W. and
Laurence, D. (eds), 4th International Symposium on Engineering
TurbulenceModelling and Measurements, Corsica, May 24-26. Elsevier,
Amsterdam (1999) pp. 669-678.
[4] Muhammad Amjad Sohail , Muhammad yamin Younis "applications of
High order low dessipitive shcme on hypersonic flow field by using min
mode limiter"CFP1070K-PRT, ISBN=11-4244-8101-9 Singapore 2010.
[5] Muhammad Amjad Sohail et al" Effect of Turbulence Modeling on
Aerodynamics characteristics of a conventional tailed finned missile
configurations" CFP1070K-PRT, ISBN=11-4244-8101-9 Singapore
2010.
[6] Muhammad Yamin Younis., Muhammad Amjad Sohail, Tawfiqur
Rahman, Zaka Muhammad, Saifur Rahman Bakaul" Applications of
AUSM+ Scheme on Subsonic, Supersonic and Hypersonic Flows
Fields" World Academy Of Science, Engineering and Technology Issue
73 January 2011
[7] J PRoos, F.W. and Kegelman, J.T., "Aerodynamic Characteristics of
Three Generic Forebodies at High Angles of Attack," AIAA Paper 91-
0275, January, 1991.).
[8] Jason M. Merret* and Michael B. Bragg" X-38 AERODYNAMICS
DURING RAPID PITCH UP" University of Illinois at Urbana-
Champaign Urbana, IL 61801AIAA 2003-3526.
[9] S. Saravanan ÔÇó G. Jagadeesh ÔÇó K. P. J. Reddy" Aerodynamic force
measurement using 3-componentaccelerometer force balance system in a
hypersonic shock tunnel" Shock Waves (2009) 18:425-435 DOI
10.1007/s00193-008-0172-8.
[10] Philipe R. Spalart "Young-s persons guide for detached eddy
simulations Grid generations" NASA/CR-2001-211032
[11] M. Shur, P. R. Spalart, M. Strelets, and A. Travin. Detached-Eddy
Simulation of an Airfoil at High Angle of Attack. In 4th Int. Symposium
on Eng. Turb. Modeling and Experiments, Corsica, France, May 1999.
[12] Scott A. Morton" High Reynolds Number Detached-Eddy Simulations
of Vortex Breakdown Over A 70 Degree Delta Wing"
[13] B. CARUELLEa, and F. DUCROSb" Detached-Eddy Simulations of
Attached and Detached Boundary Layers" International Journal of
Computational Fluid Dynamics, December 2003 Vol. 17 (6), pp. 433-
451
[14] ANDREI TRAVIN, MICHAEL SHUR, MICHAEL STRELETS and
PHILIPPE SPALART" Detached-Eddy Simulations Past a Circular
Cylinder" Flow, Turbulence and Combustion 63: 293-313, 1999
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:64326", author = "Muhammad Amjad Sohail and Prof. Yan Chao and Mukkarum Husain", title = "Comparison of Detached Eddy Simulations with Turbulence Modeling", abstract = "Flow field around hypersonic vehicles is very
complex and difficult to simulate. The boundary layers are squeezed
between shock layer and body surface. Resolution of boundary layer,
shock wave and turbulent regions where the flow field has high
values is difficult of capture. Detached eddy simulation (DES) is a
modification of a RANS model in which the model switches to a
subgrid scale formulation in regions fine enough for LES
calculations. Regions near solid body boundaries and where the
turbulent length scale is less than the maximum grid dimension are
assigned the RANS mode of solution. As the turbulent length scale
exceeds the grid dimension, the regions are solved using the LES
mode. Therefore the grid resolution is not as demanding as pure LES,
thereby considerably cutting down the cost of the computation. In
this research study hypersonic flow is simulated at Mach 8 and
different angle of attacks to resolve the proper boundary layers and
discontinuities. The flow is also simulated in the long wake regions.
Mesh is little different than RANS simulations and it is made dense
near the boundary layers and in the wake regions to resolve it
properly. Hypersonic blunt cone cylinder body with frustrum at angle
5o and 10 o are simulated and there aerodynamics study is performed
to calculate aerodynamics characteristics of different geometries. The
results and then compared with experimental as well as with some
turbulence model (SA Model). The results achieved with DES
simulation have very good resolution as well as have excellent
agreement with experimental and available data. Unsteady
simulations are performed for DES calculations by using duel time
stepping method or implicit time stepping. The simulations are
performed at Mach number 8 and angle of attack from 0o to 10o for
all these cases. The results and resolutions for DES model found
much better than SA turbulence model.", keywords = "Detached eddy simulation, dual time stepping,hypersonic flow, turbulence modeling", volume = "5", number = "2", pages = "500-7", }