Parametric Study for the Low BVI Noise Rotor Blade Design

Hwang, Chang-Jeon; Joo, Gene

doi:10.5139/ijass.2003.4.1.088

International Journal of Aeronautical and Space Sciences

2003

DOI: 10.5139/ijass.2003.4.1.088

|View full text |Cite

Parametric Study for the Low BVI Noise Rotor Blade Design

Chang-Jeon Hwang¹,

Gene Joo²

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...

Citation Types

Supporting

Mentioning

Contrasting

Year Published

2003

2023

Publication Types

Select...

Article5

Relationship

Self Cite0

Independent5

Authors

Journals

Cited by 9 publications

(2 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…There is another type of blade generating twin tip vortices that was proposed and numerically tested by Hwang et al [4]. It was entitled the Korean BERP (British Experimental Rotor Program) blade (KBERP) and was designed by combining the twin-vortexgeneration concept and the BERP blade concept.…”

mentioning

confidence: 99%

See 1 more Smart Citation

Effect of the Blade Inner-Tip Position on the Generation of Twin Vortices

Jung

Choi

Lee

2008

Journal of Aircraft

View full text Add to dashboard Cite

Engineering Notes ENGINEERING NOTES are short manuscripts describing new developments or important results of a preliminary nature. These Notes should not exceed 2500 words (where a figure or table counts as 200 words). Following informal review by the Editors, they may be published within a few months of the date of receipt. Style requirements are the same as for regular contributions (see inside back cover).

show abstract

mentioning

confidence: 99%

“…Until relatively recently, few studies were done on the effect of tipshape parameters on the generation of twin tip vortices. The concept of twin tip vortices could be combined with established blades, as shown in [4]. The blade tip region is closely related to the aerodynamic performance.…”

mentioning

confidence: 99%

Effect of the Blade Inner-Tip Position on the Generation of Twin Vortices

Jung

Choi

Lee

2008

Journal of Aircraft

View full text Add to dashboard Cite

show abstract

Effect of Blade Tip Configurations on the Performance and Vibration of a Lift-Offset Coaxial Rotor

Lee¹,

Park

2023

Aerospace

View full text Add to dashboard Cite

This present study investigates the effect of blade tip configurations, such as the sweepback angle and anhedral angle, on the performance and hub vibratory loads for the lift-offset coaxial rotor of a 30,000-pound-class high-speed long-range utility helicopter. The rotorcraft comprehensive analysis code, CAMRAD II, is utilized to conduct the performance and hub vibratory load analyses for the present lift-offset coaxial rotor. The total rotor thrust, torque, and individual rotor’s hub pitch moment and hub roll moment are considered the trim targets. The general properties for the lift-offset coaxial rotor are designed from the X2TD, S-97 Raider, and SB > 1 Defiant, which are lift-offset compound helicopters. The rotor performance and hub vibratory loads are studied with the various blade tip configurations including the sweepback angle and anhedral angle. The rotor power when the rotor blade tip considers only the sweepback angle (20°) is lower than the baseline rotor model by 41.25% at 170 knots. The maximum rotor effective lift-to-drag ratio (L/De) for the lift-offset coaxial rotor using only the sweepback angle and the rotor with both sweepback (20°) and anhedral angles (10°) at 170 knots increase by 10.82% and 5.02%, respectively, compared with the baseline rotor model without both sweepback and anhedral angles. The vibration index (VI) for the rotor with only the sweepback angle is higher than that for the baseline rotor model without both sweepback and anhedral angles by 37.14%. Furthermore, when the rotor blade tip has the anhedral angle, the magnitude of the Blade Vortex Interaction (BVI) decreases compared with the rotor without the sweepback and anhedral angles.

show abstract

Reconfigurable Flight Control System Design Using Sliding Mode Based Model Following Control Scheme

Cho¹,

Kim²,

Kim³

2003

International Journal of Aeronautical and Space Sciences

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

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 for the Low BVI Noise Rotor Blade Design

Cited by 9 publications

References 1 publication

Effect of the Blade Inner-Tip Position on the Generation of Twin Vortices

Effect of the Blade Inner-Tip Position on the Generation of Twin Vortices

Effect of Blade Tip Configurations on the Performance and Vibration of a Lift-Offset Coaxial Rotor

Reconfigurable Flight Control System Design Using Sliding Mode Based Model Following Control Scheme

Contact Info

Product

Resources

About