Record Details

Record 1 of 1
Open Rotor Aeroacoustic Installation Effects for Conventional and Unconventional Airframes
NTRS Full-Text: Click to View  [PDF Size: 4.6 MB]
Author and Affiliation:
Czech, Michael J.(Boeing Co., Everett, WA, United States);
Thomas, Russell H.(NASA Langley Research Center, Hampton, VA, United States)
Abstract: As extensive experimental campaign was performed to study the aeroacoustic installation effects of an open rotor with respect to both a conventional tube and wing type airframe and an unconventional hybrid wing body airframe. The open rotor rig had two counter rotating rows of blades each with eight blades of a design originally flight tested in the 1980s. The aeroacoustic installation effects measured in an aeroacoustic wind tunnel included those from flow effects due to inflow distortion or wake interaction and acoustic propagation effects such as shielding and reflection. The objective of the test campaign was to quantify the installation effects for a wide range of parameters and configurations derived from the two airframe types. For the conventional airframe, the open rotor was positioned in increments in front of and then over the main wing and then in positions representative of tail mounted aircraft with a conventional tail, a T-tail and a U-tail. The interaction of the wake of the open rotor as well as acoustic scattering results in an increase of about 10 dB when the rotor is positioned in front of the main wing. When positioned over the main wing a substantial amount of noise reduction is obtained and this is also observed for tail-mounted installations with a large U-tail. For the hybrid wing body airframe, the open rotor was positioned over the airframe along the centerline as well as off-center representing a twin engine location. A primary result was the documentation of the noise reduction from shielding as a function of the location of the open rotor upstream of the trailing edge of the hybrid wing body. The effects from vertical surfaces and elevon deflection were also measured. Acoustic lining was specially designed and inserted flush with the elevon and airframe surface, the result was an additional reduction in open rotor noise propagating to the far field microphones. Even with the older blade design used, the experiment provided quantification of the aeroacoustic installation effects for a wide range of open rotor and airframe configurations and can be used with data processing methods to evaluate the aeroacoustic installation effects for open rotors with modern blade designs.
Publication Date: May 27, 2013
Document ID:
20130013993
(Acquired Jul 19, 2013)
Subject Category: ACOUSTICS
Report/Patent Number: NF1676L-15865, AIAA Paper 2013-2185
Document Type: Conference Paper
Meeting Information: 19th AIAA/CEAS Aeroacoustics Conference; 27-29 May 2013; Berlin; Germany
Meeting Sponsor: American Inst. of Aeronautics and Astronautics; Reston, VA, United States
Contract/Grant/Task Num: WBS 699959.02.10.07.05
Financial Sponsor: NASA Langley Research Center; Hampton, VA, United States
Organization Source: NASA Langley Research Center; Hampton, VA, United States
Description: 21p; In English; Original contains color and black and white illustrations
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Distribution as joint owner in the copyright
NASA Terms: ACOUSTIC PROPAGATION; AEROACOUSTICS; AERODYNAMIC NOISE; AIRFRAMES; NOISE PROPAGATION; NOISE REDUCTION; ROTOR AERODYNAMICS; SHIELDING; TRAILING EDGES; WAKES; WIND TUNNELS
› Back to Top
Facebook icon, External Link to NASA STI page on Facebook Twitter icon, External Link to NASA STI on Twitter YouTube icon, External Link to NASA STI Channel on YouTube RSS icon, External Link to New NASA STI RSS Feed
Find Similar Records
 
NASA Logo, External Link

NASA Official: Gerald Steeman
Sponsored By: NASA Scientific and Technical Information Program
Site Curator: STI Support Services
Last Modified: July 19, 2013

Privacy Policy & Important Notices Disclaimers, Copyright, Terms of Use Freedom of Information Act USA.gov NASA.gov NASA OCIO Free Adobe PDF Reader Free MS Word Viewer