Effect of Airfoil Shape on Flow Control by Small-Amplitude Oscillations

Cleaver, David; Wang, Zhijin; Gursul, Ismet

doi:10.2514/6.2012-756

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 2012

DOI: 10.2514/6.2012-756

|View full text |Cite

Effect of Airfoil Shape on Flow Control by Small-Amplitude Oscillations

David Cleaver

Zhijin Wang

Ismet Gursul

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...

Citation Types

Supporting

Mentioning

Contrasting

Year Published

2021

Publication Types

Select...

Article1

Relationship

Self Cite0

Independent1

Authors

Journals

Cited by 1 publication

References 22 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

Numerical analysis of high-lift configurations with oscillating flaps

Ruhland

Breitsamter

2021

CEAS Aeronaut J

View full text Add to dashboard Cite

This study presents two-dimensional aerodynamic investigations of various high-lift configuration settings concerning the deflection angles of droop nose, spoiler and flap in the context of enhancing the high-lift performance by dynamic flap movement. The investigations highlight the impact of a periodically oscillating trailing edge flap on lift, drag and flow separation of the high-lift configuration by numerical simulations. The computations are conducted with regard to the variation of the parameters reduced frequency and the position of the rotational axis. The numerical flow simulations are conducted on a block-structured grid using Reynolds Averaged Navier Stokes simulations employing the shear stress transport $$k-\omega $$ k - ω turbulence model. The feature Dynamic Mesh Motion implements the motion of the oscillating flap. Regarding low-speed wind tunnel testing for a Reynolds number of $$0.5 \times 10^{6}$$ 0.5 × 10 6 the flap movement around a dropped hinge point, which is located outside the flap, offers benefits with regard to additional lift and delayed flow separation at the flap compared to a flap movement around a hinge point, which is located at 15 % of the flap chord length. Flow separation can be suppressed beyond the maximum static flap deflection angle. By means of an oscillating flap around the dropped hinge point, it is possible to reattach a separated flow at the flap and to keep it attached further on. For a Reynolds number of $$20 \times 10^6$$ 20 × 10 6 , reflecting full scale flight conditions, additional lift is generated for both rotational axis positions.

show abstract

Numerical analysis of high-lift configurations with oscillating flaps

Ruhland

Breitsamter

2021

CEAS Aeronaut J

View full text Add to dashboard Cite

show abstract

scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.

Contact Info

customersupport@researchsolutions.com

10624 S. Eastern Ave., Ste. A-614

Henderson, NV 89052, USA

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.

Blog Terms and Conditions API Terms Privacy Policy Contact Cookie Preferences Do Not Sell or Share My Personal Information

Made with 💙 for researchers

Part of the Research Solutions Family.

Effect of Airfoil Shape on Flow Control by Small-Amplitude Oscillations

Cited by 1 publication

References 22 publications

Numerical analysis of high-lift configurations with oscillating flaps

Numerical analysis of high-lift configurations with oscillating flaps

Contact Info

Product

Resources

About