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Wednesday, July 29, 2020 | History

3 edition of Tip aerodynamics and acoustics test found in the catalog.

Tip aerodynamics and acoustics test

Jeffrey L. Cross

Tip aerodynamics and acoustics test

a report and data survey

by Jeffrey L. Cross

  • 307 Want to read
  • 21 Currently reading

Published by National Aeronautics and Space Administration, Scientific and Technical Information Division in [Washington, D.C.] .
Written in English

    Subjects:
  • Rotors (Helicopters) -- Aerodynamics

  • Edition Notes

    StatementJeffrey L. Cross and Michael E. Watts.
    SeriesNASA reference publication ;, 1179
    ContributionsWatts, Michael E.
    Classifications
    LC ClassificationsTL716 .C73 1988
    The Physical Object
    Paginationvi, 458 p. :
    Number of Pages458
    ID Numbers
    Open LibraryOL1811837M
    LC Control Number89601353

    A computational framework used to evaluate the aerodynamics and aeroacoustics is developed and validated against the experimental data in the previous work. In the present work, the different operating parameters of inlet flow velocity, tip speed ratio and turbulence Cited by: 1.   Here you can download the free lecture Notes of Aerodynamics II Notes Pdf (AE II Notes Pdf) materials with multiple file links to download. This Aerodynamics II Pdf Notes – AE II Pdf Notes book starts with the topics covering Compressibility of fluid and flow, Perfect gas, Thermodynamics Concepts, System, Surroundings, Types of systems, isolated systems, closed systems, open systems 5/5(19).

    Aircraft Technologies INTERDISCIPLINARY DESIGN Analysis of APIAN High Speed Isolated Test Results - Acoustics and Aerodynamics J, FROTA, Eric MAURY The APIAN programme (Advanced Propulsion Integration Aerodynamics and Noise) 'aunched in under the coordination of AM Airbus follows GEMINI (), and GEMINI II and SNAAP () and the huge advances Cited by: 4.   Quiz: Basic Aircraft Aerodynamics. Quiz: Basic Aircraft Aerodynamics. By. Chris Clarke - June 5, 0. Take this quiz to test your aerodynamics knowledge. 1. Select the four flight fundamentals involved in maneuvering an aircraft. Sign up for our free email newsletter, packed with tips, tricks and news for pilots. Email.

    Ground effect is caused by a reduction in induced drag when your plane is within approximately 1 wingspan or less of the runway. The closer you get to the runway, the more pronounced ground effect is. > Aerodynamics, Acoustics, and Dynamics - San Francisco, California Aeromechanics Specialists' Conference January , , San Francisco, California


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Tip aerodynamics and acoustics test by Jeffrey L. Cross Download PDF EPUB FB2

In a continuing effort to understand helicopter rotor tip aerodynamics and acoustics, a flight test was conducted by NASA Ames Research Center. The test was performed using the NASA White Cobra. Tip aerodynamics and acoustics test. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Division, (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors / Contributors: J L Cross; Michael E Watts.

Get this from a library. Tip aerodynamics and acoustics test: a report and data survey. [Jeffrey L Cross; Michael E Watts; United States. National Aeronautics and Space Administration.

Scientific and Technical Information Division.]. In a continuing effort to understand helicopter rotor tip aerodynamics and acoustics, a flight test was conducted by NASA Ames Research Center.

The test was performed using the NASA White Cobra and a set of highly instrumented blades. All aspects of the flight test instrumentation and test procedures.

This test was called the Tip Aerodynamics and Acoustics Test As the transducers added TEST SETUP AND METHOD The environmental Chamber located at NASA ARC was found to meet the test cali- bration requirements. usually used for studies involving altitude, atmospheric composition, and tempera- ture variations on the human body (fig.

A calibration test is described that was performed to supplement the normal calibration of the pressure transducers used in the Tip Aerodynamics and Acoustics Test.

This calibration led to the identification of 15 transducers which had a slope change of greater than 7% from the initial calibration. The calibration procedure is described and the results presented.

It solves the URANS equations with LEA (Linear Explicit Algebraic stress) k-ω model using the chimera overlapping grids technique.

Validation of the numerical model uses comparison with the detailed flight test data gathered by Cross J. and Watts M. during the Tip Aerodynamics and Acoustics Test (TAAT) conducted at NASA in Cited by: 2. Validation of the numerical model uses comparison with the detailed flight test data gathered by Cross J.

and Watts M. during the Tip Aerodynamics and Acoustics Test (TAAT) conducted at NASA. A calibration test is described that was performed to supplement the normal calibration of the pressure transducers used in the Tip Aerodynamics and Acoustics Test.

This calibration led to the identification of 15 transducers which had a slope change of greater than 7% from the initial calibration. An Introduction to Acoustics S.W.

Rienstra & A. Hirschberg Eindhoven University of Technology 28 Nov This is an extended and revised edition of IWDE Comments and corrections are gratefully accepted. This file may be used and printed, but for personal or educational purposes only. c S.W. Rienstra & A. Hirschberg Tabulation of data from the tip aerodynamics and acoustics test.

Moffett Field, California: National Aeronautics and Space Administration, Ames Research Center, November (OCoLC) Material Type: Document, Government publication, National government publication, Internet resource: Document Type: Internet Resource, Computer File.

Tabulation of data from the tip aerodynamics and acoustics test. Moffett Field, California: Ames Research Center, November (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors / Contributors: J L Cross; Wilson Tu; Ames Research Center.

Get this from a library. Supplementary calibration test of the tip-aerodynamics- and acoustics-test pressure transducers.

[Michael E Watts; Ames Research Center.]. A calibration test is described that was performed to supplement the normal calibration of the pressure transducers used in the Tip Aerodynamics and Acoustics Test. This calibration led to the identification of 15 transducers which had a slope change of greater than 7 from the initial calibration.

Helicopter Aerodynamics by D. Bazov. How to design build and test small liquid fuel rocket engines by Leroy J. Krzycki. Introduction to the Aerodynamics of Flight by Theodore A. Talay.

Lecture notes gas dynamics by Joseph M. Powers. Modeling Flight by Joseph R. Chambers. Nasa at 50 by Rebecca Wright, Sandra Johnson, Steven J. Dick. A review of helicopter rotor blade tip design technology has been carried out with a view to undertaking subsequent computations to evaluate the performance of new tip designs.

Rotor blade and flow field aerodynamics are calculated by CFD, and wake motions are simulated by Time-Marching-Free-Wake (TMFW) method. This tightly coupled CFD/Free-wake method can describe wake characteristics as well as rotor aerodynamic properties. Using this coupling analysis, hovering is analyzed for accurate by: 1.

A highly efficient unsteady panel time-marching free wake is established to achieve fast and accurate prediction of the unsteady aerodynamics of a helicopter.

The unsteady panel method is used to calculate the airload of rotor blades, and the free-wake method is applied to simulate the dynamics of rotor wake. The two methods are tightly coupled by convecting panels to vortex filaments, and the Cited by: 2.

The present research focused on the analysis of the leakage flows developing from advanced blade tip geometries. The aerodynamic field of a contoured blade tip and of a high-performance rimmed blade were investigated against a baseline squealer rotor.

Time-resolved numerical predictions were combined with high-frequency pressure measurements to characterize the tip leakage flow of each tip : Bogdan Cezar Cernat, Sergio Lavagnoli. In that test, a 1/7th scale model of a UH-1H rotor blade was run over a range of hover-tip Mach numbers, Mt~p, from to These rotor speeds produce strong aerodynamic shocks at the blade tips and an annoying pattern of high-speed impulsive noise.

Microphones were placed at four radial locations to record the acoustic by:. This paper investigates by means of computational fluid dynamics (CFD) and acoustic analogy the influence of blade deformations on open-rotor aerodynamics and aeroacoustics for three key operating points: cruise, takeoff, and approach conditions.

For each operating point, simulation results obtained with unrunning blade shapes and running blade shapes are compared with wind tunnel test Author: F. Falissard, R. Boisard, R. Gaveriaux, G.

Delattre, P. Gardarein, A. Chelius, S. Canard-Caruana, Y.Effects of golf ball dimple configuration on aerodynamics, trajectory, and acoustics Article (PDF Available) in Journal of Flow Visualization and Image Processing 14(2) January RUAG Aerodynamics Site Acoustics Acoustics Noise generated by transport vehicles, such as aircraft and cars, is a concern for the health, safety and comfort of passengers and crew member as well as inhabitants of noise affected areas.