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Friday, April 17, 2020 | History

3 edition of Inflow measurements made with a laser velocimeter on a helicopter model in forward flight. found in the catalog.

Inflow measurements made with a laser velocimeter on a helicopter model in forward flight.

Inflow measurements made with a laser velocimeter on a helicopter model in forward flight.

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  • 7 Currently reading

Published by National Aeronautics and Space Administration, Langley Research Center, US Army Aviation Systems Command, Aviation R&T Activity in Hampton, Va, [St. Louis, Mo.] .
Written in English

    Subjects:
  • Helicopters.,
  • Laser Doppler velocimeter.

  • Edition Notes

    StatementDanny R. Hoad ... [et al.].
    SeriesAVSCOM technical memorandum -- 89-B-002., NASA technical memorandum -- 101599., AVSCOM technical memorandum -- 89-B-002., NASA technical memorandum -- 101599.
    ContributionsHoad, Danny R., United States. Army Aviation Research and Technology Activity., Langley Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL14690822M

    Laser Doppler Velocimeter Measurements in the Ground Interaction Region of an Impinging Scale Model Jet Scott Hromisin, Nicholas Rudenko, Leighton Myers, Dennis McLaughlin, Pennsylvania State University May 5, Your Path: Home > Laser Doppler Velocimeter Measurements in the Ground Interaction Region of an Impinging Scale Model JetCited by: 2. The paper describes a methodology to extract linearized state- space dynamic inflow model from a generic and high fidelity aerodynamic analysis for single and coaxial helicopter rotor systems. Both hover and forward flight are studied includ- ing maneuvering and the results are demonstrated by a free- Cited by: 1.


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Inflow measurements made with a laser velocimeter on a helicopter model in forward flight. Download PDF EPUB FB2

Inflow measurement made with a laser velocimeter on a helicopter model in forward flight (SuDoc NAS ) Unknown Binding by Joe W. Elliott (Author)Author: Joe W.

Elliott. An experimental investigation was conducted in the by Foot Supersonic Tunnel at the NASA Langley Research Center to measure the inflow into a scale model helicopter rotor in forward flight (mu = ).

The measurements were made with a two-component Laser Velocimeter (LV) chord above the plane formed by the path of the rotor tips (tip-path-plane).

An experimental investigation was conducted in the by Foot Subsonic Tunnel at the NASA Langley Research Center to measure the inflow into a scale model helicopter rotor in forward flight (mu = ). The measurements were made with a two-component Laser Velocimeter (LV) chord above the plane formed by the path of the rotor tips (tip-path-plane).

An experimental investigation was conducted in the by Foot Subsonic Tunnel at NASA Langley Research Center to measure the inflow into a scale model helicopter rotor in forward flight. The measurements were made with a two component Laser Velocimeter (LV) one chord above the plane formed by the path of the rotor tips (tips path plane).

Inflow measurements made with a laser velocimeter on a helicopter model in forward flight. Volume 4: Tapered planform blades at an advance ratio of By Richard H.

Sailey, Joe W. Elliott and Susan L. Abstract. These data files contain the inflow measurements made with a laser velocimeter on a Inflow measurements made with a laser velocimeter on a helicopter model in forward flight.

book model in forward flight, volume X, rectangular planform blades at an advance ratio of, chord above the tip path plane. A combined Doppler Global Velocimetry (DGV) and Projection Moire Interferometry (PMI) investigation of a helicopter rotor wake flow field and rotor blade deformation is presented.

The three-component Dbv system uses a single-frequency, frequency-doubled Nd:Y AG laser to obtain instantaneous velocity measurements in the by: 8. Elliot, J. W., Althoff, S. L and Sailey, R. () Inflow Measurements made with a Laser Velocimeter on a Helicopter Model in Forward Flight, NASA TM Google Scholar Cited by: 2.

Numerical solution of forward flight rotor flow using an upwind method Inflow Measurement made with a Laser Velocimeter on a Helicopter Model Forward Flight. Inflow measurement made with a laser velocimeter on a helicopter model in forward flight. Vol. III, Rectangular planform blades at an advance ratio of Velocity measurements were taken using a laser velocimeter with components in the vertical and down- stream directions.

Measurements were taken at 13 sta- tions downstream from the rotor hub. At each station, measurements were taken in both a horizontal and verti- cal row of locations.

Inn ow Measurements Made with a Laser Velocimeter on a Helicopter Model in Forward Flight-Volume VII: Rectangular Planform Blades at an Advance Ratio of" NASA TM Helicopter. Inflow measurements made with a laser velocimeter on a helicopter model in forward flight.

Volume VIII, Rectangular planform blades at an advance ratio ofchord above the tip path plane. [Susan L Althoff; United States. Inflow measurements made with a laser velocimeter on a helicopter model in forward flight.

Volume X, Rectangular planform blades at an advance ratio ofchord above the tip path plane. [Susan L Althoff; United States.

Inflow measurement made with a laser velocimeter on a helicopter model in forward flight. Volume 2: Rectangular planform blades at an advance ratio of By Joe W.

Elliott, Susan L. Althoff and Richard H. Sailey. Tunnel at NASA Langley Research Center to measure the inflow into a scale model helicopter rotor in forward flight (_m = ). The measurements were made with a two component Laser Velocimeter (LV) one chord above the plane formed hv the path of the rotor tips (tip path plane).

A conditional samplinq technique was employed to. An experimental investigation was conducted in the by Foot Subsonic tunnel at NASA Langley Research Center to measure the inflow into a scale model helicopter rotor in forward flight (mu sub inf = ). The measurements were made with a two component Laser Velocimeter (LV) one chord above the plane formed by the path of the blade tips.

RAD (Comprehensive Analytical Model of Rotor-craft Aerodynamics and Dynamics) and rotor inflow measurements using a laser velocimeter have been presented. This information is presented for a rectan-gular four-bladed rotor system operating at a thrust coefficient of The inflow measurements were made at azimuthal increments of from an az.

An experimental investigation was conducted in the by Foot Subsonic Tunnel at NASA Langley to measure the inflow into a scale model helicopter rotor in forward flight (microinf = ).

The measurements were made with a two component Laser Velocimeter (LV) one chord above the plane formed by the path of the rotor tips (tip path plane).

at the NASA Langley Research Center to measure the inflow into a scale model helicopter rotor in forward flight (I = ). The measurements were made with a two-component Laser Velocimeter (LV) one chord above the plane formed by the path of the rotor tips (tip-path-plane).

Novel Actuator Surface Method for Helicopter Rotor Analysis. the hovering and forward flight cases that are extensively used in validation studies of the rotor analysis code are analyzed using the suggested method. L., Sailey, R. H., "Inflow Measurement Made with a Laser Velocimeter on a Helicopter Model in Forward Flight-μ= Author: Taewoo Kim, Sejong Oh, Kwanjung Yee.

J.W. Elliott, S.L. Althoff, R.H. Sailey, Inflow measurement made with a laser velocimeter on a helicopter model in forward flight. Volume 1: Rectangular planform Cited by: 4. Therefore, the induced inflow of a scale-model rotor is firstly predicted and compared with well-known experimental measurements.

The experiment was conducted in a 2-m rotor test system (2MRTS) at the NASA Langley Research Center (LaRC) facility for a scaled model rotor in forward flight condition. The model rotor has four articulated blades Cited by: An experimental investigation was conducted in the by Foot Subsonic tunnel at NASA Langley Research Center to measure the inflow into a scale model helicopter rotor in forward flight (mu.

Helicopter rotor in forward flight acc ompany periodic. “Inflow Measurements Made with a Laser. Velocimeter on a Helicopter Model in Forward. An experimental investigation was conducted in the by foot subsonic tunnel at NASA-Langley Research Center to measure the inflow into a scale model helicopter rotor in forward flight.

helicopter aerodynamic investigations, an experiment was conducted using a laser velocimeter to measure velocities in the wake of a model helicopter hub operat-ing at Mach-scaled conditions in forward flight. Velocity measurements were taken using a laser velocimeter with components in the vertical and down-stream directions.

Elliott, S. Althoff, R. Sailey, Inflow measurements made with a laser velocimeter on a helicopter model in forward flight—Volume II: Rectangular planform blades at an advance ratio ofTech. Rep. TM, NASA, Cited by: A long-range laser velocimeter for the national full-scale aerodynamics complex [microform]: new develo Stereo imaging based particle velocimeter [microform] / submitted by Celal Batur Inflow measurements made with a laser velocimeter on a helicopter model in forward flight.

at the NASA Langley Research Center to measure the inflow into a scale model helicopter rotor in forward flight (jt = ). The measurements were made with a two-component Laser Velocimeter (LV) one chord above the plane formed by the path of the rotor tips (tip-path-plane). Comparison of the inflow calculations between an analytical rotor wake method and rotor inflow measurements using a laser velocimeter was presented.

The inflow measurements were made near a 4-bladed rotor system using rectangular planform blades operating in forward flight at a thrust coefficient ofand at 3 rotor advance ratios: longitudinal inflow distribution Lateral inflow distribution hub hub e s Field s ° x/l c p 0 1 0 Experiment ASM ADM ADM ADM ASM ADM: Actuator disk model Elliot, J., Althoff, S.

L., Sailey, R., “Inflow Measurement Made with a Laser Velocimeter on a Helicopter Model in Forward Flight, Vol. Tilt-rotor aircraft flight regimes include the helicopter flight regime, transition flight regime and the forward flight regime.

Therefore, the inflow angle (α T), which is the angle between the propeller axis and the airstream, may vary within the range of 0° and 90°. The aerodynamic derivatives at these high inflow angle regimes differ. In the prediction of ground noise from an in-flight helicopter, flight trajectory is discretized first.

In this paper, the trajectory is discretized according to the distance traveled by helicopter over one rotor revolution, namely, 2 π μ R (μ is advance ratio, and R is rotor radius). The comparison between second-level acoustic radiation model and direct ground noise prediction method is Author: Fei Wang, Guohua Xu, Yongjie Shi.

undertaken to provide detailed measurements of ro- tor inflow (refs. These data have been used to evaluate the rotor-inflow models used by rotor perfor- mance codes (refs. 18 and 24). These flow field mea- surements were made with a two-component laser Doppler velocimeter over a helicopter model File Size: 6MB.

A remarkable in-flight experiment to measure the time-averaged-induced velocity over the rotor disk in forward flight was made by Brotherhood & Stewart ().

Based on measurements of the angular displacements of smoke streamers introduced upstream of the rotor, the longitudinal inflow variation was determined to be approximately linear.

Introduction Doppler velocimeter over a helicopter model with a realistic, although simplified, fuselage.

particularly in forward flight, tor to assess the magnitude of the isolated fuselage were made during a helicopter inflow-measurement The source-panel method has been in use for over program. The rotor-inflow data are reported in ref. In most cases, an investigator proposed a technique of laser velocimetry and/or reported a successful atmospheric wind-speed measurement at a convenient range without discussing the time required for such a measurement or the dependence of the measurement rate on laser Cited by: 1.

Simple Simulink simulation for a helicopter control design. The package includes a paper, matlab file, and a simulink model. Read the paper for detailed description of the simulink model.

The design is based on the book by Gareth D. Padfield: (Helicopter Flight Dynamics: The Theory and Application of Flying Qualities and Simulation Modeling).Reviews: forward flight wake geometry effects of wake geometry on harmonic airloads hovering wake geometry references page no, 1 1 5 8 10 section ii development of laser doppler velocimeter for use in helicopter rotor wakes 11 introduction 11 basic principles of laser doppler velocimetry 11File Size: 4MB.

DEVELOPMENT OF A SIMPLIFIED INFLOW MODEL FOR A HELICOPTER ROTOR IN DESCENT FLIGHT A Dissertation Presented to The Academic Faculty by Chang Chen In Partial Fulfillment of invited Dr.

Prasad to come to DSO for a 5-day course on Helicopter Stability and Control. I also went to Georgia Tech for a rotorcraft specialists’ meeting in model was tested in the ONERA S2Ch wind tunnel (figure 1). From this model steady and unsteady pressure data on the fuselage were acquired.

Also, 3D laser velocimeter (LV) data were acquired in two vertical planes. The first plane was taken at a downstream location through the hub and the second plane was taken at radius downstream from File Size: 1MB.In forward flight, air flows opposite the aircraft’s flightpath.

The velocity of this air flow equals the helicopter’s forward speed. Because the rotor blades turn in a circular pattern, the velocity of airflow across a blade depends on the position of the blade in the plane of rotation at a given instant, its rotational velocity, and.