Shock Control Bump design optimization on Natural Laminar Aerofoil

D. S. Lee; J. Periaux; K. Srinivas; L. F. Gonzalez; N. Qin; E. Onate

doi:10.1007/978-3-642-17884-9_31

Shock Control Bump design optimization on Natural Laminar Aerofoil

D. S. Lee^*, J. Periaux, K. Srinivas, L. F. Gonzalez, N. Qin, E. Onate

^*Corresponding author for this work

Research output: Chapter in Book/Report/Conference proceeding › Conference proceeding contribution › peer-review

4 Citations (Scopus)

Abstract

The chapter investigates Shock Control Bumps (SCB) on a Natural Laminar Flow (NLF) aerofoil; RAE 5243 for Active Flow Control (AFC). A SCB approach is used to decelerate supersonic flow on the suction/pressure sides of transonic aerofoil that leads delaying shock occurrence or weakening of shock strength. Such an AFC technique reduces significantly the total drag at transonic speeds. This chapter considers the SCB shape design optimisation at two boundary layer transition positions (0 and 45%) using an Euler software coupled with viscous boundary layer effects and robust Evolutionary Algorithms (EAs). The optimisation method is based on a canonical Evolution Strategy (ES) algorithm and incorporates the concepts of hierarchical topology and parallel asynchronous evaluation of candidate solution. Two test cases are considered with numerical experiments; the first test deals with a transition point occurring at the leading edge and the transition point is fixed at 45% of wing chord in the second test. Numerical results are presented and it is demonstrated that an optimal SCB design can be found to significantly reduce transonic wave drag and improves lift on drag (L/D) value when compared to the baseline aerofoil design.

Original language	English
Title of host publication	Computational fluid dynamics 2010
Subtitle of host publication	Proceedings of the Sixth International Conference on Computational Fluid Dynamics, ICCFD6, St Petersburg, Russia, on July 12-16, 2010
Editors	Alexander Kuzmin
Place of Publication	Berlin; Heidelberg
Publisher	Springer, Springer Nature
Pages	253-259
Number of pages	7
ISBN (Electronic)	9783642178849
ISBN (Print)	9783642178832
DOIs	https://doi.org/10.1007/978-3-642-17884-9_31
Publication status	Published - 2011
Externally published	Yes
Event	6th International Conference on Computational Fluid Dynamics, ICCFD 2010 - St. Petersburg, Russian Federation Duration: 12 Jul 2010 → 16 Jul 2010

Other

Other	6th International Conference on Computational Fluid Dynamics, ICCFD 2010
Country/Territory	Russian Federation
City	St. Petersburg
Period	12/07/10 → 16/07/10

Access to Document

10.1007/978-3-642-17884-9_31

Cite this

Lee, D. S., Periaux, J., Srinivas, K., Gonzalez, L. F., Qin, N., & Onate, E. (2011). Shock Control Bump design optimization on Natural Laminar Aerofoil. In A. Kuzmin (Ed.), Computational fluid dynamics 2010: Proceedings of the Sixth International Conference on Computational Fluid Dynamics, ICCFD6, St Petersburg, Russia, on July 12-16, 2010 (pp. 253-259). Springer, Springer Nature. https://doi.org/10.1007/978-3-642-17884-9_31

Lee, D. S. ; Periaux, J. ; Srinivas, K. et al. / Shock Control Bump design optimization on Natural Laminar Aerofoil. Computational fluid dynamics 2010: Proceedings of the Sixth International Conference on Computational Fluid Dynamics, ICCFD6, St Petersburg, Russia, on July 12-16, 2010. editor / Alexander Kuzmin. Berlin; Heidelberg : Springer, Springer Nature, 2011. pp. 253-259

@inproceedings{2457dd8c7bd14977a7ce8b0ca547612f,

title = "Shock Control Bump design optimization on Natural Laminar Aerofoil",

abstract = "The chapter investigates Shock Control Bumps (SCB) on a Natural Laminar Flow (NLF) aerofoil; RAE 5243 for Active Flow Control (AFC). A SCB approach is used to decelerate supersonic flow on the suction/pressure sides of transonic aerofoil that leads delaying shock occurrence or weakening of shock strength. Such an AFC technique reduces significantly the total drag at transonic speeds. This chapter considers the SCB shape design optimisation at two boundary layer transition positions (0 and 45%) using an Euler software coupled with viscous boundary layer effects and robust Evolutionary Algorithms (EAs). The optimisation method is based on a canonical Evolution Strategy (ES) algorithm and incorporates the concepts of hierarchical topology and parallel asynchronous evaluation of candidate solution. Two test cases are considered with numerical experiments; the first test deals with a transition point occurring at the leading edge and the transition point is fixed at 45% of wing chord in the second test. Numerical results are presented and it is demonstrated that an optimal SCB design can be found to significantly reduce transonic wave drag and improves lift on drag (L/D) value when compared to the baseline aerofoil design.",

author = "Lee, {D. S.} and J. Periaux and K. Srinivas and Gonzalez, {L. F.} and N. Qin and E. Onate",

year = "2011",

doi = "10.1007/978-3-642-17884-9_31",

language = "English",

isbn = "9783642178832",

pages = "253--259",

editor = "Alexander Kuzmin",

booktitle = "Computational fluid dynamics 2010",

publisher = "Springer, Springer Nature",

address = "United States",

note = "6th International Conference on Computational Fluid Dynamics, ICCFD 2010 ; Conference date: 12-07-2010 Through 16-07-2010",

}

Lee, DS, Periaux, J, Srinivas, K, Gonzalez, LF, Qin, N & Onate, E 2011, Shock Control Bump design optimization on Natural Laminar Aerofoil. in A Kuzmin (ed.), Computational fluid dynamics 2010: Proceedings of the Sixth International Conference on Computational Fluid Dynamics, ICCFD6, St Petersburg, Russia, on July 12-16, 2010. Springer, Springer Nature, Berlin; Heidelberg, pp. 253-259, 6th International Conference on Computational Fluid Dynamics, ICCFD 2010, St. Petersburg, Russian Federation, 12/07/10. https://doi.org/10.1007/978-3-642-17884-9_31

Shock Control Bump design optimization on Natural Laminar Aerofoil. / Lee, D. S.; Periaux, J.; Srinivas, K. et al.
Computational fluid dynamics 2010: Proceedings of the Sixth International Conference on Computational Fluid Dynamics, ICCFD6, St Petersburg, Russia, on July 12-16, 2010. ed. / Alexander Kuzmin. Berlin; Heidelberg: Springer, Springer Nature, 2011. p. 253-259.

Research output: Chapter in Book/Report/Conference proceeding › Conference proceeding contribution › peer-review

TY - GEN

T1 - Shock Control Bump design optimization on Natural Laminar Aerofoil

AU - Lee, D. S.

AU - Periaux, J.

AU - Srinivas, K.

AU - Gonzalez, L. F.

AU - Qin, N.

AU - Onate, E.

PY - 2011

Y1 - 2011

N2 - The chapter investigates Shock Control Bumps (SCB) on a Natural Laminar Flow (NLF) aerofoil; RAE 5243 for Active Flow Control (AFC). A SCB approach is used to decelerate supersonic flow on the suction/pressure sides of transonic aerofoil that leads delaying shock occurrence or weakening of shock strength. Such an AFC technique reduces significantly the total drag at transonic speeds. This chapter considers the SCB shape design optimisation at two boundary layer transition positions (0 and 45%) using an Euler software coupled with viscous boundary layer effects and robust Evolutionary Algorithms (EAs). The optimisation method is based on a canonical Evolution Strategy (ES) algorithm and incorporates the concepts of hierarchical topology and parallel asynchronous evaluation of candidate solution. Two test cases are considered with numerical experiments; the first test deals with a transition point occurring at the leading edge and the transition point is fixed at 45% of wing chord in the second test. Numerical results are presented and it is demonstrated that an optimal SCB design can be found to significantly reduce transonic wave drag and improves lift on drag (L/D) value when compared to the baseline aerofoil design.

AB - The chapter investigates Shock Control Bumps (SCB) on a Natural Laminar Flow (NLF) aerofoil; RAE 5243 for Active Flow Control (AFC). A SCB approach is used to decelerate supersonic flow on the suction/pressure sides of transonic aerofoil that leads delaying shock occurrence or weakening of shock strength. Such an AFC technique reduces significantly the total drag at transonic speeds. This chapter considers the SCB shape design optimisation at two boundary layer transition positions (0 and 45%) using an Euler software coupled with viscous boundary layer effects and robust Evolutionary Algorithms (EAs). The optimisation method is based on a canonical Evolution Strategy (ES) algorithm and incorporates the concepts of hierarchical topology and parallel asynchronous evaluation of candidate solution. Two test cases are considered with numerical experiments; the first test deals with a transition point occurring at the leading edge and the transition point is fixed at 45% of wing chord in the second test. Numerical results are presented and it is demonstrated that an optimal SCB design can be found to significantly reduce transonic wave drag and improves lift on drag (L/D) value when compared to the baseline aerofoil design.

UR - http://www.scopus.com/inward/record.url?scp=84890295328&partnerID=8YFLogxK

U2 - 10.1007/978-3-642-17884-9_31

DO - 10.1007/978-3-642-17884-9_31

M3 - Conference proceeding contribution

AN - SCOPUS:84890295328

SN - 9783642178832

SP - 253

EP - 259

BT - Computational fluid dynamics 2010

A2 - Kuzmin, Alexander

PB - Springer, Springer Nature

CY - Berlin; Heidelberg

T2 - 6th International Conference on Computational Fluid Dynamics, ICCFD 2010

Y2 - 12 July 2010 through 16 July 2010

ER -

Lee DS, Periaux J, Srinivas K, Gonzalez LF, Qin N, Onate E. Shock Control Bump design optimization on Natural Laminar Aerofoil. In Kuzmin A, editor, Computational fluid dynamics 2010: Proceedings of the Sixth International Conference on Computational Fluid Dynamics, ICCFD6, St Petersburg, Russia, on July 12-16, 2010. Berlin; Heidelberg: Springer, Springer Nature. 2011. p. 253-259 doi: 10.1007/978-3-642-17884-9_31

Shock Control Bump design optimization on Natural Laminar Aerofoil

Abstract

Other

Access to Document

Other files and links

Fingerprint

Cite this