Parametric Study of an Air-Jet Vortex Generator Configuration to Control Rotorcraft Retreating Blade Stall

This paper presents an experimental and computational study of a novel passive version of the air jet vortex generator flow control system for the delay or suppression of trailing edge boundary layer separation and subsequent stall. The results show that a passive vortex generating jet flow control system can effectively delaying trailing edge separation and subsequent stall to higher angles of attack, without the need for any active energy input and without significant drag penalty. Nomenclature α Angle of attack (deg) c Chord length (m) C A Axial force coefficient C D Drag force coefficient C L Lift force coefficient C M 1 / 4 chord pitching moment coefficient C µ Blowing momentum coefficient Cp Pressure coefficient m & Mass flow rate through AJVG duct (kg/s) p Static Pressure (N/m 2 ) p 0 Total Pressure (N/m 2 ) ρ Density (kg/m 3 ) U Velocity (m/s) S Reference (model planform) area (m 2 ) x Chordwise distance from leading-edge (m) y Spanwise distance from model centre (m) z Distance normal to the chordline (m) Subscripts: 1 Local conditions ∞ Freestream conditions j

show abstract

Low-Speed Static Stall Suppression Using Steady and Pulsed Air-Jet Vortex Generators

Prince

Khodagolian

2011

AIAA Journal

View full text Add to dashboard Cite

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.

Parametric Study of an Air-Jet Vortex Generator Configuration to Control Rotorcraft Retreating Blade Stall

Cited by 3 publications

References 13 publications

Control of dynamic stall of helicopter rotor blades

Control of dynamic stall of helicopter rotor blades

Aerodynamic Stall Suppression on Aerofoil Sections Using Passive Air-Jet Vortex Generators

Low-Speed Static Stall Suppression Using Steady and Pulsed Air-Jet Vortex Generators

Contact Info

Product

Resources

About