Last edited by Sar
Thursday, July 9, 2020 | History

2 edition of Wind-tunnel evaluation of an advanced main-rotor blade design for a utility-class helicopter found in the catalog.

Wind-tunnel evaluation of an advanced main-rotor blade design for a utility-class helicopter

Wind-tunnel evaluation of an advanced main-rotor blade design for a utility-class helicopter

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Published by National Aeronautics and Space Administration, Scientific and Technical Information Office, For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Rotors (Helicopters) -- Testing.,
  • Rotors (Helicopters) -- Aerodynamics.

  • Edition Notes

    Other titlesWind tunnel evaluation of an advanced main rotor blade design for a utility class helicopter.
    StatementWilliam T. Yaeger, Jr. ... [et al.].
    SeriesNASA technical memorandum -- 89129.
    ContributionsYaeger, William T., United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15286464M

    Rotor Blade Capabilities & Center of Excellence Submitted by kaman_admin on Fri, Backed by more than 70 years of solid aerospace experience and proven performance as an industry innovator, today's Kaman is delivering complete design, development, test and turnkey manufacturing solutions to the aircraft industry. Rotor blade modulation can be quite oppressive. Nulls in the radiation pattern of a helicopter-mounted antenna due to rbm can be 30 dB or more below the nominal signal level. In the worse cases, the warbling effect garbles voice communications and can render digital communications useless.

    Helicopter rotor blades require at a minimium some mechanism to control the pitch of the blade (AKA feathering) and most also allow the blade to flap up and downward, or to teeter in pairs. These mechanisms are mostly required to be duplicated for each blade, so adding cost, weight, and increasing the possibility of failure. Thus, a good design for a helicopter blade may not be a good design for a wind turbine. However, since composite helicopter blades are considered to offer unlimited life, the knowledge gained in their development should have some value to the wind turbine designer. Helicopter blades are made by semimechanized processes.

    Helicopter Track and Balance Theory. A vertical vibration is a result of unequal lift produced by the main rotor blades. This unequal lift can be a result of blade chord profile variances from.   Structural design of wind turbine blades DTU Wind Energy. This lecture will explain how to formulate the basic principles of structural design and explain the difference between loads.


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Wind-tunnel evaluation of an advanced main-rotor blade design for a utility-class helicopter Download PDF EPUB FB2

Wind-Tunnel Evaluation of an Advanced Main-Rotor Blade Design for a Utility-Class Helicopter William T. Yeager, Jr., Wayne R. Mantay, Matthew L. Wilbur, Robert G. Cramer, Jr., and Jeffrey D.

Singleton Aerostructures Directorate Langley Researcb Center Hampton, Virginia USAARTA-A VSCOM Na t i ona I Aeronautics and Space AdministrationFile Size: 3MB. An investigation was conducted in the Langley Transonic Dynamics Tunnel to evaluate differences between an existing utility-class main-rotor blade and an advanced-design main-rotor blade.

Thus, an experimental investigation was conducted in the Langley Transonic Dynamics Tunnel (TDT) to evaluate the effect of using slotted airfoils in the rotor blade tip region (85 to percent radius) on rotor aerodynamic performance and by: 6.

Wind Tunnel Evaluation of a Model Helicopter Main-Rotor Blade With Slotted Airfoils at the Tip Kevin W. Noonan Joint Research Program Office Aeroflightdynamics Directorate U.S.

Army Aviation and Missile Command Langley Research Center, Hampton, Virginia William T. Yeager, Jr., Jeffrey D. Singleton, Matthew L. Wilbur, and Paul H. Mirick. An investigation was conducted in the Langley Transonic Dynamics Tunnel to evaluate differences between an existing utility-class main-rotor blade and an advanced-design main-rotor blade.

The two rotor blade designs were compared with regard to rotor performance oscillatory pitch-link loads, and 4-per-rev vertical fixed-system loads.

Wind-tunnel evaluation of an advanced main-rotor blade design for a utility-class helicopter / By William T. Yeager and United States. Army. Aerostructures Directorate. Abstract. Wind-Tunnel Evaluation of an Advanced Main-Rotor Blade Design for a Utility-Class Helicopter DTI - '.

L LcTIE iSEP 17 *~l William T. Yeager, Jr., Wayne R. Mantay, Matthew L. Wilbur, Robert G. Cramer, Jr., and Jeffrey D. Singleton SEPTEMBER DLMWhBtffON sTATEMEII A Approved for public MOloWNOI n Distribution UnlUmted ~US ARMY AVIATION MA.

Matthew Wilbur An investigation was conducted in the NASA Langley Transonic Dynamics Tunnel to evaluate an advanced main rotor designed for use on a utility class helicopter, specifically the U.S. “HELICOPTER’S MAIN ROTOR BLADE” and compare them for different materials such as “ALUMINIUM and STEEL” using the.

finite element method. Keywords: Catia, Hyper mesh, Ansys 1. Introduction. helicopter. is a type of rotorcraft in which lift and thrust are supplied by rotors. This allows the. Yeager, W. Mantay, M. Wilbur, R.

Cramer and J. Singleton, Wind tunnel evaluation of an advanced main rotor blade design for a utility class helicopter, NASA TM. rotor blades are attached to the centre. The motion of blade is controlled by the helicopter rotor system. The main rotor blade mainly affected by the air flow for rotation of the blade and the influence of aerodynamic force and a centrifugal force applying to blade has been considered.

The dynamic characteristics analysis of rotor blade is. Get this from a library. Wind-tunnel evaluation of an advanced main-rotor blade design for a utility-class helicopter.

[William T Yaeger; United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.;]. An enhanced integrated aerodynamic load/dynamic optimization procedure is developed for minimizing vibratory root shears and moments of a helicopter rotor blade. The optimization problem is formulated with 4/rev inplane shears at the blade root as objective functions.

Constraints are imposed on 3/rev radial shear, 3/rev flapping and torsional moments, 4/rev lagging moment, blade natural. An investigation was conducted in the NASA Langley Transonic Dynamics Tunnel to evaluate an advanced main rotor designed for use on a utility class helicopter, specifically the U.S.

Army UHA Blackhawk. This rotor design incorporated advanced twist. DESIGN AND TESTING OF A HELICOPTER ROTOR BLADE CHORD EXTENSION SYSTEM A Thesis in Aerospace Engineering by Eric William Hayden and high speed operations, the helicopter main rotor is susceptible to stall.

The onset of stall both limits the envelope as well as significantly increases morphing of sections of the main rotor blade.

Sikorsky bearingless rotor mounted in by Foot Wind Tunnel. The primary objective of the wind tunnel test was to evaluate the SBMR in the following five areas: dynamics and stability, rotor structures and loads, handling qualities, aeroperformance and acoustics. The DARPA Helicopter Quieting Phase 1B effort funded the test preparation, the majority of the wind tunnel test occupancy time, and data reduction and analysis.

The data was used to validate the next generation of helicopter aeroacoustic analysis codes developed by Georgia Tech, Stanford University, the University of Maryland, and Penn State.

Mach-scaled rotor was tested in December in ONERA S1 Modane wind-tunnel. The main objective of this test was to validate the concept of using active flaps located on the trailing edge of the blades of the main rotor of a helicopter to decrease the vibration level generated by this rotor.

A model of a helicopter rotor has four blades, each of length m from the central shaft to the blade tip. The model is rotated in a wind tunnel at a rotational speed of rev/min. a) What is the linear speed of the blade tip. _____ m/s b) What is the radial acceleration of the blade tip expressed as a multiple of the acceleration of gravity, g.

INSPECTION OF HELICOPTER ROTOR BLADES BY NEUTRON- AND X-RAY RADIOGRAPHY 22 - 4 RTO-AG-AVT INVESTIGATED OBJECTS Metal Composite Structure The majority of the helicopters, Mi-8, Mi and Mi types, in the Hungarian Army’s inventory are several decades old and yet they are required to provide continued service.

A wind-tunnel based study of helicopter tail rotor blade vortex interaction - Volume Issue - F. N. Coton, R. A. McD. Galbraith, T. Wang, S. J. Newman.From Summary: "A portion of a PV-2 helicopter rotor blade has been tested in the 6- by 6-foot test section of the Langley stability tunnel to determine if the aerodynamic characteristics were seriously affected by cross flow or fabric distortion.

The outer portion of the blade was tested as a reflection plane model pivoted about the tunnel wall to obtain various angles of cross flow over the.S Main Rotor & Tail Rotor Blade Development.

ATI designed, analyzed, and tested composite main-rotor blades to replace the metal blades on Carson Helicopter's S (H-3). ATI fabricated the first flight-certified sets of the rotor-blades as well as the static and fatigue test also developed the S composite tail rotor blades which have been successfully flight tested.