Wind-tunnel acoustic results of two rotor models with several tip designs

Publisher: National Aeronautics and Space Administration, Scientific and Technical Information Branch, Publisher: For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va

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  • Rotors (Helicopters) -- Noise.

Edition Notes

Other titlesWind tunnel acoustic results of two rotor models with several tip designs
StatementR.M. Martin and Andrew B. Connor.
SeriesNASA technical memorandum -- 87698
ContributionsConnor, Andrew B., United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL17095844M

  New Rotor Ship Sails in Lightest Wind (Jul, ) For more than a year, Lesh has been experimenting with miniature rotor ships in the model boat basin in Jackson Park, besides conducting various wind-tunnel tests. His researches have shown that the spinning wings of his models will pull the boats directly into the teeth of the wind and that. A full-scale prediction method for wind turbine rotor noise by using wind tunnel test data Jaeha Ryia, Jong-Soo Choia,*, Seunghoon Leeb, Soogab Leec aDepartment of Aerospace Engineering, Chungnam National University, Daejeon , Republic of Korea b School of Mechanical and Aerospace Engineering, Seoul National University, Seoul , Republic of Korea. To investigate exterior aerodynamic noise produced by high speed trains, wind tunnel measurements are typically performed on scale models of train sections, or on components such as pantographs. A number of array systems are described to perform this kind of measurements together with some typical results.   A high tip speed turboprop is being considered as a future energy conservative airplane. When the turboprop airplane is at cruise, the combination of the airplane forward speed and the propeller rotational speed results in supersonic helical velocities over the other portions of the propeller blades. These supersonic blade sections could generate noise that is a cabin Cited by:

A wind tunnel experiment was conducted in order to perform an aerodynamic frequency domain identification on a NACA airfoil with a simple flap. The experimental results revealed the existence of two flow noise sources; mainly a wind tunnel resonance, also. of this parameters used to settle the rotor tip speed and the blade angle of attack in order to reduce the noise emission (Shaltout and al ). Leloudas and al () carried out a parametrical study to optimize the performance and noise emissions from a MW Wind Turbine by changing tip speed and pitch setting using the acoustic modelCited by: 2. The possibility of using the time-reversal technique to localize acoustic sources in a wind-tunnel flow is investigated. While the technique is widespread, it has scarcely been used in aeroacoustics up to now. The proposed method consists of two steps: in a first experimental step, the acoustic pressure fluctuations are recorded over a linear array of microphones; in a Cited by: The wind tunnel is made of several distinct sections, the settling chamber, the contraction cone, the test/working section, the diffuser and the fan. Several considerations have to be made in order to achieve a wind tunnel with the wanted properties [10]. The main design criteria are listed in the table below: Open circuit wind-tunnel.

  This paper discussed a noise reduction effect of airfoil and small-scale model rotor by using attached serration trailing edge in the wind tunnel test condition. In order to analyze the changes in the performance due to the inclusion of a serrated trailing edge designed to reduce noise, a 10 kW wind turbine rotor was equipped with a thin serrated trailing by: 3. WIND TUNNEL TECHNICAL. A wind tunnel is a research tool developed to assist with studying the effects of air moving over or around solid objects. Air is blown or sucked through a duct equipped with a viewing port and instrumentation where models or geometrical shapes are mounted for study. Various techniques are then used to study the actual airflow around the . It has been tested in the NASA Ames ft wind tunnel as well as the National Transonic Facility.9 The CRM was designed for a cruise Mach number of at a Reynolds number of 40 million. It has an aspect ratio of , a taper ratio of , and a washout of degrees from the side of body to wing tip.8 The CRM65 has a span of ft, aCited by:   The acoustic modeling is realized in two steps: (i) an integral method based on the Ffowcs Williams and Hawkings (FWH) equat16 gives the tonal noise radiated by the rotor from the steady loading yielded by the BEMT and (ii) analytical models based on the work of Roger and Moreau 17 estimate the broadband part of the acoustic spectrum Cited by: 1.

Wind-tunnel acoustic results of two rotor models with several tip designs Download PDF EPUB FB2

Wind-Tunnel Acoustic Results of Two Rotor Models With Several Tip Designs R. Martin and Andrew B. Connor Langley Research Center Hampton, Virginia NI\S/\ National Aeronautics and Space Administration Scientific and Technical Information Branch File Size: 3MB.

Get this from a library. Wind-tunnel acoustic results of two rotor models with several tip designs. [R M Martin; Andrew B Connor; United States. National Aeronautics and Space Administration.

Scientific and Technical Information Branch.]. Wind-tunnel acoustic results of two rotor models with several tip designs v. (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors / Contributors: R M Martin; Andrew B Connor; United States.

National Aeronautics and Space Administration. Scientific and Technical. A wind-tunnel investigation has been conducted using an articulated heli- copter model rotor systen to determine the effects of several blade tip designs on both the perforaance ma acoustic ~h~ta~ttristi~s of the totor.

Cnly the porfoasurco characteetsfics are presented in this paper. (Low Speed Wind Tunnel) in Melbourne. The new test capability utilises a custom 64 microphone acoustic array whose design was optimised for large models.

Measurements were carried out on an aeroacoustic model for two flow speeds and for a wide range of pitch and yaw angles. The data were processed using a frequency.

The wind tunnel test model used within WENEMOR was designed and built by Teknosud. This section outlines the model characteristics, model con gurations, and the technical information related to the model construction. The manufactured model is a 1 7 th scale model of airplane equipped with two counter rotating open-rotor engines.

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.

Abstract The results of wind tunnel tests of a model scale, closely spaced, rigid, counter-rotating coaxial rotor system are presented. The system, tested in the Glenn L. Martin wind tunnel, features-two bladed upper and lower rotors, m in Author: Christopher Cameron, Jayant Sirohi.

between CAMRAD/JA results and measured wind tunnel data. The analytical results are also compared with flight test data. Test Hardware Wind Tunnel BO The BO helicopter rotor system is a four-bladed, soft inplane (ω ζ File Size: 2MB.

The results of wind tunnel tests performed on a full scale horizontal axis wind turbine with a rotor diameter of m are presented, analyzed and compared with those predicted by WT_Perf and. This paper describes the beamforming approaches used for characterizing acoustic sources on an counter rotating open rotor (CROR) installed on a 1/7th scale model of an advanced regional air-craft design.

The tests were conducted in a large Low Speed Wind Tunnel (WT) at The Pininfarina Aerodynamic and. Full text of "NASA Technical Reports Server (NTRS) Aeronautical engineering: A cumulative index to a continuing bibliography" See other formats.

Low Turbulence Wind Tunnel Design and Wind Turbine Wake Characterization Andrew Welsh experimental results. This work validates and opens the door to the use of the wind tunnel for simulated, data using a RANS approach, show the blade tip vortices still separated from the rest of the turbulence in the near wake by: 2.

The purpose of this research work is to investigate experimentally and computationally the feasibility of improving the performance of the vertical-axis Savonius wind turbine. The authors first performed a series of wind tunnel investigations on semi-cylindrical three-bladed Savonius rotor scale models with different overlap ratios and without by: The static tests covered two flap designs, conical and ejector nozzles, third-flap noise-reduction treatments, internal blowing, and flap/nozzle geometry variations.

of speed and exhaust nozzle area on the scale models noise characteristics were investigated with both the nominal rotor and serrated rotor. Acoustic results indicate the. Wind Tunnel Testing for Final Year BE Thesis Titled "Optimisation of NS14 Sail Design" at the University of New South Wales, Australia WIND TUNNEL PERFORMANCE DATA FOR TWO- AND THREE -BUCKET SAVONIUS ROTORS Ben F.

Blackwell Robert E. Sheldahl Aerothermodynamics Division, Louis V. Feltz Mechanical Design Division, Sandia Laboratories Albuquerque, NM ABSTRACT Fifteen configurations of a Savonius rotor wind turbine were tested in the Vought Corporation.

The Tilt Rotor Aeroacoustic Model (TRAM) is a general-purpose test bed for moderate-scale tiltrotor models. TRAM consists of two hardware-interchangeable test rigs: an isolated rotor test stand, and a full-span, dual-rotor model.

The contractor team of Micro Craft and McDonnell Douglas Helicopter (now Boeing) had overallFile Size: 1MB. Introduced for full-scale rotor noise estimation by using wind tunnel test results. • Performed the noise test on the 2D airfoil and a small-scale rotor.

• Adjustment of the simulation distance and noise level from small-scale to full-scale. • Comparison between the wind tunnel scaling result and the full-scale rotor by: 2. Scaling the reference design. The first step of model design was the comparison between the turbine specifications and the Polimi Wind Tunnel (GVPM) (Zasso et al., ) test section dimensions and flow GVPM is a closed circuit facility with two test rooms: a 4 × 4m high speed low turbulence and a 14 × 4m low speed boundary layer test by: Rotor, drivetrain, and tower designs at 80 m/s maximum tip velocity and m/s maximum tip velocity are created to quantify these effects.

Component costs, annualized energy production, and cost of energy are computed for each design to quantify the change in overall cost of energy resulting from the increase in turbine tip velocity.

For the acoustic tests described in this paper, the two-dimensional airfoil models were mounted between two acoustically treated endplates and tested with and with-out boundary layer trips and a turbulence grid, at three angles of attack and five wind tunnel speeds corre-sponding to Reynolds numbers from to million.

A counter-rotating open rotor scale model was tested in the NASA Glenn Research Center 9- by Foot Low-Speed Wind Tunnel (LSWT). This model used a historical baseline blade set with which modern blade designs will be compared against on an acoustic and aerodynamic performance by: optimization of two contradictory metrics from the array response pattern, i.e., dynamic range & angular resolution.

The results of the optimization tool were verified by two wind tunnel experimental campaigns using a scaled aircraft model. The wind tunnel experimental results show that the a priori selection of the optimal. Several static circular guide vanes were tried by Ogawa (8).

In this study, a new type of Savonius rotor is proposed and it has been tested with the wind tunnel. The new type rotor was named by the authors to “Three-stage Out-phase Savonius Rotor” because it has three stages with degree bucket phase shift between the adjacent Size: KB.

Abstract— A new low-speed open-jet wind tunnel has been designed and constructed at the University of Leeds. A series of Computational Fluid Dynamics (CFD) and experimental evaluations were conducted to determine the flow quality and to verify the wind tunnel suitability for aerodynamic studies.

Two sets of resultsFile Size: KB. The present book focus on uses and developments of wind tunnels. It consists on nine chapters presenting different studies on the design, uses and developments of the wind tunnel in different applications like wind turbines, building and aircraft models.

Wind Tunnels have played and are continuing to play a significant role in providing controlled test facilities in the aerodynamic research and development [, ].The present chapter describes in detail, the design features of a subsonic return circuit wind tunnel that is currently in operation at the Aerodynamics Laboratory of the University of New South by: 1.

@article{osti_, title = {Wind turbine engineering design}, author = {Eggleston, D.M. and Stoddard, F.}, abstractNote = {The authors explain the fundamental theory behind wind turbines as well as the basic mathematical models needed for their design.

They give engineers a solid physical understanding of the dynamics of machines from both theory and field experience. This chapter describes design and optimization of low‐noise airfoil and wind turbines.

The airfoils and wind turbine blades are designed with the objective of high‐power performance. The aerodynamic noise is one of the important constraints for the optimization. The power coefficient of an airfoil is computed with the blade element momentum by: 1. store hitting the carrier.

A Mach 2 wind tunnel was designed using the method of characteristics with a viscous approximation to conduct research is the area of cavity flow acoustics. Unique features of the supersonic wind tunnel include a modular design for quick changes in cavity.Issue 7 - June - Overview of rotorcraft acoustic research at Onera AL The tools have been used to design and optimize new blades, which were first tested at model scale in a wind tunnel, before being pro-vided to industrialists for the Author: Y.

Delrieux.We examine aerodynamic properties and experiment with different solutions for actively controlling the loads on our blades. with advanced technology, we generate aeromechanic designs through a process of numerical simulations which are validated in our very own wind tunnel.

The tunnel dimensions are m width, m height and m length.