NDLI: The investigation of a variable camber blade lift control for helicopter rotor systems

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The investigation of a variable camber blade lift control for helicopter rotor systems

Content Provider	NASA Technical Reports Server (NTRS)
Author	Awani, A. O.
Copyright Year	1982
Description	A new rotor configuration called the variable camber rotor was investigated numerically for its potential to reduce helicopter control loads and improve hover performance. This rotor differs from a conventional rotor in that it incorporates a deflectable 50% chord trailing edge flap to control rotor lift, and a non-feathering (fixed) forward portion. Lift control is achieved by linking the blade flap to a conventional swashplate mechanism; therefore, it is pilot action to the flap deflection that controls rotor lift and tip path plane tilt. This report presents the aerodynamic characteristics of the flapped and unflapped airfoils, evaluations of aerodynamics techniques to minimize flap hinge moment, comparative hover rotor performance and the physical concepts of the blade motion and rotor control. All the results presented herein are based on numerical analyses. The assessment of payoff for the total configuration in comparison with a conventional blade, having the same physical characteristics as an H-34 helicopter rotor blade was examined for hover only.
File Size	6688815
Page Count	131
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19840019627
Archival Resource Key	ark:/13960/t7np6wn1j
Language	English
Publisher Date	1982-01-01
Access Restriction	Open
Subject Keyword	Aerodynamics Pitching Moments Helicopter Tail Rotors Helicopters Pressure Distribution Airfoils Mathematical Models Trailing Edge Flaps Hovering Camber Computer Programs Loads Forces Lift Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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