Hybrid Wing Body Aircraft Acoustic Test Preparations and Facility Upgrades

A hybrid wing body transport aircraft model was tested in NASA Langley's 14 by 22Foot Subsonic Tunnel to evaluate proposed "low noise" technology. The experiment was set up to evaluate the community noise impact of the hybrid wing body design, as well as study the noise components of propulsion-airframe noise and shielding. A high fidelity 5.8-percent scale model, including landing gear, cruise and drooped wing leading edges, trailing edge elevons, vertical tail options, and engine noise simulators, was built to test both aerodynamic and acoustic configurations. The aerodynamic test data were used to establish appropriate flight conditions for the acoustic test. To accomplish the acoustic portion of this test, two major upgrades were required of NASA Langley's 14 by 22 Foot Subsonic Tunnel; first, a fuel delivery system to provide realistic gas temperatures to the jet engine simulators; and second, a traversing microphone array and side towers to measure full spectral and directivity noise characteristics. The results of this test provide benchmark hybrid wing body aircraft and noise shielding data to assist in achieving NASA's 2020 noise emission goals.

[1]  Dorian Frederic Marie Colas A diffraction integral based turbomachinery noise shielding method , 2011 .

[2]  Gregory M. Gatlin,et al.  The Langley 14- by 22-Foot Subsonic Tunnel: Description, Flow Characteristics, and Guide for Users , 1990 .

[3]  Ronald T. Kawai Acoustic Prediction Methodology and Test Validation for an Efficient Low-Noise Hybrid Wing Body Subsonic Transport , 2011 .

[4]  Karl A. Geiselhart,et al.  Integration of Propulsion-Airframe-Aeroacoustic Technologies and Design Concepts for a Quiet Blended-Wing-Body Transport , 2004 .

[5]  Michael J. Doty,et al.  Investigation of Flow Conditioners for Compact Jet Engine Simulator Rig Noise Reduction , 2011 .

[6]  Jr William M. Humphreys,et al.  Effect of Directional Array Size on the Measurement of Airframe Noise Components , 1999 .

[7]  W. E. Zorumski Aircraft noise prediction program theoretical manual, part 1 , 1982 .

[8]  Dennis Huff Technologies for Turbofan Noise Reduction , 2013 .

[9]  Russell H. Thomas,et al.  Hybrid Wing Body Aircraft System Noise Assessment with Propulsion Airframe Aeroacoustic Experiments , 2010 .

[10]  Thomas F. Brooks,et al.  A Deconvolution Approach for the Mapping of Acoustic Sources (DAMAS) Determined from Phased Microphone Arrays , 2004 .

[11]  Thomas F. Brooks,et al.  Noise Spectra and Directivity for a Scale-Model Landing Gear , 2007 .

[12]  Michael J. Doty,et al.  Acoustic Characterization of Compact Jet Engine Simulator Units , 2013 .

[13]  Edmane Envia,et al.  An Analytical Assessment of NASA's N+1 Subsonic Fixed Wing Project Noise Goal , 2009 .

[14]  Russell H. Thomas,et al.  Propulsion Airframe Aeroacoustic Integration Effects for a Hybrid Wing Body Aircraft Configuration , 2010 .

[15]  Michael J. Doty Investigation of Twin Jet Aeroacoustic Properties in the Presence of a Hybrid Wing Body Shield , 2012 .

[16]  Ana F. Tinetti,et al.  Fast Scattering Code (Fsc) User's Manual: Version 2 , 2013 .

[17]  Geoffrey A. Hill,et al.  Challenges and Opportunities for Noise Reduction Through Advanced Aircraft Propulsion Airframe Integration and Configurations , 2005 .

[18]  Thomas F. Brooks,et al.  A Deconvolution Approach for the Mapping of Acoustic Sources (DAMAS) Determined from Phased Microphone Arrays , 2006 .

[19]  Craig A. Reimann,et al.  Noise Scattering by the Blended Wing Body Airplane: Measurements and Prediction , 2006 .

[20]  Thomas F. Brooks,et al.  DAMAS Processing for a Phased Array Study in the NASA Langley Jet Noise Laboratory , 2010 .

[21]  Leonard V. Lopes,et al.  Design of the Next Generation Aircraft Noise Prediction Program: ANOPP2 , 2011 .

[22]  Thomas F. Brooks,et al.  Extension of DAMAS Phased Array Processing for Spatial Coherence Determination (DAMAS-C) , 2006 .

[23]  Edmane Envia Emerging Community Noise Reduction Approaches , 2011 .

[24]  Dan D. Vicroy,et al.  Experimental Investigation of the Low-Speed Aerodynamic Characteristics of a 5.8-Percent Scale Hybrid Wing Body Configuration , 2012 .

[25]  Daniel L. Sutliff,et al.  Hybrid Wing Body Shielding Studies Using an Ultrasonic Configurable Fan Artificial Noise Source Generating Simple Modes , 2012 .

[26]  Carl H. Gerhold,et al.  Inlet Noise Reduction by Shielding for the Blended-Wing-Body Airplane , 1999 .

[27]  Jr William M. Humphreys,et al.  Design and Use of Microphone Directional Arrays for Aeroacoustic Measurements , 1998 .

[28]  Russell H. Thomas,et al.  High Bypass Ratio Jet Noise Reduction and Installation Effects Including Shielding Effectiveness , 2013 .