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Author : Anonim
Publisher : Unknown
Page : 78 pages
File Size : 51,9 Mb
Release : 1976
Category : Electronic
ISBN : NASA:31769000536485
Author : Harvey H. Hubbard
Publisher : Unknown
Page : 616 pages
File Size : 49,6 Mb
Release : 1991
Category : Aerodynamic noise
ISBN : UCAL:B5262564
Author : Anonim
Publisher : Unknown
Page : 628 pages
File Size : 47,8 Mb
Release : 1977
Category : Astronautics
ISBN : MINN:31951P001419031
Author : Anonim
Publisher : Unknown
Page : 980 pages
File Size : 43,5 Mb
Release : 1990
Category : Aeronautics
ISBN : UIUC:30112075701679
Author : Henry C. Pusey,Rudolph H. Volin,J. Gordan Showalter,Shock and Vibration Information Center
Publisher : Unknown
Page : 476 pages
File Size : 54,5 Mb
Release : 1979
Category : Shock (Mechanics)
ISBN : UIUC:30112007788067
Author : M. Lesieur,Akiva M. Yaglom,F. David
Publisher : Springer Science & Business Media
Page : 566 pages
File Size : 54,8 Mb
Release : 2003-07-01
Category : Science
ISBN : 9783540456742
Following a longstanding tradition of the Les Houches Summer Schools, this book uses a pedagogically presented and accessible style to treat 2D and 3D turbulence from the experimental, theoretical and computational points of view.
Author : Thomas F. Brooks
Publisher : Unknown
Page : 52 pages
File Size : 43,7 Mb
Release : 1977
Category : Acoustic radiation pressure
ISBN : NASA:31769000425309
The Kirchhoff integral formulation is evaluated for its effectiveness in quantitatively predicting the sound radiated from an oscillating airfoil whose chord length is comparable with the acoustic wavelength.
Author : Anonim
Publisher : Unknown
Page : 724 pages
File Size : 46,8 Mb
Release : 1982
Category : Astronautics
ISBN : MINN:31951000586486K
Author : Louis G. Kaufman,Algirdas Maciulaitis,Rodney L. Clark
Publisher : Unknown
Page : 288 pages
File Size : 48,9 Mb
Release : 1983
Category : Aeroacoustics
ISBN : UOM:39015095307644
Internal weapons carriage in high performance aircraft is often adversely affected by the severe aeroacoustic environment produced with the weapons bay doors open. To obtain a better understanding of this fluid dynamic problem, basic static and oscillatory pressure data were obtained for Mach 0.6 to 3.0 flows over shallow rectangular cavities in a generic flat plate model. Cavity length to depth ratios were varied from approximately 5 to 10. Static pressure data characteristic of both open and closed cavity flows were obtained. An improved Rossiter method is presented that satisfactorily predicts the possible frequency modes within the cavity. Highest fluctuating pressure occurs on the aft bulkhead, peaking near Mach 1.5 for the conditions tested. Aeroacoustic levels are substantially reduced by installing suppression fences (spoilers) at subsonic and low supersonic conditions. Acoustic levels generally drop rapidly above Mach 1.5. (Author).
Author : Anonim
Publisher : Unknown
Page : 30 pages
File Size : 52,6 Mb
Release : 1977
Category : Electronic
ISBN : NASA:31769000537590
Author : American Institute of Aeronautics and Astronautics
Publisher : Unknown
Page : 1112 pages
File Size : 52,7 Mb
Release : 2008
Category : Aeronautics
ISBN : UCSD:31822036051662
Author : Anonim
Publisher : Unknown
Page : 576 pages
File Size : 42,5 Mb
Release : 1998
Category : Shock (Mechanics)
ISBN : STANFORD:36105022060086
Author : Interagency Aircraft Noise Research Panel
Publisher : Unknown
Page : 236 pages
File Size : 54,8 Mb
Release : 1975
Category : Airplanes
ISBN : UCR:31210012665111
Author : Anonim
Publisher : Unknown
Page : 616 pages
File Size : 44,5 Mb
Release : 1991
Category : Electronic
ISBN : NASA:31769000527179
The field of aeroacoustics has matured dramatically in the past two decades. Researchers have gained significant theoretical and experimental understanding of the noise generated by aircraft power plants and their components. In addition, airframe noise and interior noise have been investigated extensively. The physical understanding obtained from these efforts has resulted in the development of hardware capable of reducing community noise and of meeting strict noise certification requirements. Reductions in overall sound pressure level of 20 to 30 dB have been obtained for some types of power plants, while in the same period their installed power has increased significantly. Current quiet flight vehicle designs are based on information reported in a multitude of journals, conference proceeding, research reports, and specialized books. Each of these scientific publications represents only incremental steps in the evolution of our present understanding of the various aeroacoustic noise generation and propagation mechanisms and procedures for noise control.
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 142 pages
File Size : 48,5 Mb
Release : 2018-06-15
Category : Electronic
ISBN : 1721148086
This report contains the following information: 1) a review of airframe noise research performed under NASA's Advanced Subsonic Transport (AST) program up to the year 2000, 2) a comparison of the year 1992 airframe noise predictions with those using a year 2000 baseline, 3) an assessment of various airframe noise reduction concepts as applied to the year 2000 baseline predictions, and 4) prioritized recommendations for future airframe noise reduction work. NASA's Aircraft Noise Prediction Program was the software used for all noise predictions and assessments. For future work, the recommendations for the immediate future focus on the development of design tools sensitive to airframe noise treatment effects and on improving the basic understanding of noise generation by the landing gear as well as on its reduction. Rackl, Robert G. and Miller, Gregory and Guo, Yueping and Yamamoto, Kingo Langley Research Center NAS1-97040; 23-781-20-12