Aeroelastic Model Helicopter Rotor Testing in the Langley TDT PDF Download
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Author:
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ISBN:
Category :
Languages : en
Pages : 22
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Author:
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ISBN:
Category :
Languages : en
Pages : 22
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722942533
Category :
Languages : en
Pages : 38
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Book Description
A survey was conducted of the flow field produced by the Airstream Oscillator System (AOS) in the Langley Transonic Dynamics Tunnel (TDT). The magnitude of a simulated gust field was measured at 15 locations in the plane of a typical model helicopter rotor when tested in the TDT using the Aeroelastic Rotor Experimental System (ARES) model. These measurements were made over a range of tunnel dynamic pressures typical of those used for an ARES test. The data indicate that the gust field produced by the AOS is non-uniform across the tunnel test section, but should be sufficient to excite a model rotor. Mirick, Paul H. and Hamouda, M-Nabil H. and Yeager, William T., Jr. Langley Research Center DA PROJ. 1L1-62211-A-47-AB; RTOP 505-63-51-03...
Author: W. Keats Wilkie
Publisher:
ISBN:
Category : Modal analysis
Languages : en
Pages : 24
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Author:
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ISBN:
Category :
Languages : en
Pages : 24
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Author: Wayne R. Mantay
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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A research study was initiated to systematically determine the impact of selected blade tip geometric parameters on conformable rotor performance and loads characteristics. The model articulated rotors included baseline and torsionally soft blades with interchangeable tips. Seven blade tip designs were evaluated on the baseline rotor and six tip designs were tested on the torsionally soft blades. The designs incorporated a systemmatic variation in geometric parameters including sweep, taper, and anhedral. The rotors were evaluated in the NASA Langley Transonic Dynamics Tunnel at several advance ratios, lift and propulsive force values, and tip Mach numbers. A track sensitivity study was also conducted at several advance ratios for both rotors. Based on the test results, tip parameter variations generated significant rotor performance and loads differences for both baseline and torsionally soft blades. Azimuthal variation of elastic twist generated by variations in the tip parameters strongly correlated with rotor performance and loads, but the magnitude of advancing blade elastic twist did not. In addition, fixed system vibratory loads and rotor track for potential conformable rotor candidates appears very sensitive to parametric rotor changes. (Author).
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721101245
Category :
Languages : en
Pages : 116
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Book Description
A historical account of the contributions of the Aeroelasticity Branch (AB) and the Langley Transonic Dynamics Tunnel (TDT) to rotorcraft technology and development since the tunnel's inception in 1960 is presented. The paper begins with a summary of the major characteristics of the TDT and a description of the unique capability offered by the TDT for testing aeroelastic models by virtue of its heavy gas test medium. This is followed by some remarks on the role played by scale models in the design and development of rotorcraft vehicles and a review of the basic scaling relationships important for designing and building dynamic aeroelastic models of rotorcraft vehicles for testing in the TDT. Chronological accounts of helicopter and tiltrotor research conducted in AB/TDT are then described in separate sections. Both experimental and analytical studies are reported and include a description of the various physical and mathematical models employed, the specific objectives of the investigations, and illustrative experimental and analytical results. Yeager, William T., Jr. and Kvaternik, Raymond G. Langley Research Center RTOP 712-20-21-01
Author:
Publisher: DIANE Publishing
ISBN: 1428995803
Category :
Languages : en
Pages : 115
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Author: Charles Eugene Hammond
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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The use of aeroelastically scaled helicopter rotor wind-tunnel models in establishing or verifying the dynamic characteristics of new or existing rotor designs is discussed. A model, termed the generalized rotor aeroelastic model (GRAM), which has been developed for testing aeroelastically scaled rotor models is described, and the utility of the model in being able to test a variety of rotor systems to meet a broad range of test objectives is demonstrated though presentation of data from recent tests. Data are presented from tests of an AH-1G Cobra model to determine whether or not the two-blade teetering rotor can experience stall flutter, tests of two wide chord teetering rotors to evaluate the effect of the wide chord on blade loads and rotor performance, and tests of a new four-blade flex-hinge rotor configuration to provide information for the designer relative to its dynamic characteristics. Since the GRAM was developed for testing in a wind tunnel which has the capability of using Freon-12 as a test medium, some of the advantages of Freon-12 for testing of aeroelastically scaled models are also discussed. (Author).
Author:
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ISBN:
Category :
Languages : en
Pages : 134
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Data for rotors using unconventional airfoils are of interest to permit an evaluation of this technology's capability to meet the U.S. Army's need for increased helicopter mission effectiveness and improved safety and survivability. 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 100 percent radius) on rotor aerodynamic performance and loads. Four rotor configurations were tested in forward flight at advance ratios from 0.15 to 0.45 and in hover in-ground effect. The hover tip Mach number was 0.627, which is representative of a design point of 4000-ft geometric altitude and a temperature of 95 degrees F. The baseline rotor configuration had a conventional single element airfoil in the tip region. A second rotor configuration had a forward-slotted airfoil with a -6 degrees slat, a third configuration had a forward-slotted airfoil with a -10 degrees slat, and a fourth configuration had an aft-slotted airfoil with a 3 degrees flap (trailing edge down). The results of this investigation indicate that the -6 degrees slat configuration offers some performance and loads benefits over the other three configurations.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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