NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Landing Gear Noise Prediction and Analysis for Tube-and-Wing and Hybrid-Wing-Body AircraftImprovements and extensions to landing gear noise prediction methods are developed. New features include installation effects such as reflection from the aircraft, gear truck angle effect, local flow calculation at the landing gear locations, gear size effect, and directivity for various gear designs. These new features have not only significantly improved the accuracy and robustness of the prediction tools, but also have enabled applications to unconventional aircraft designs and installations. Systematic validations of the improved prediction capability are then presented, including parametric validations in functional trends as well as validations in absolute amplitudes, covering a wide variety of landing gear designs, sizes, and testing conditions. The new method is then applied to selected concept aircraft configurations in the portfolio of the NASA Environmentally Responsible Aviation Project envisioned for the timeframe of 2025. The landing gear noise levels are on the order of 2 to 4 dB higher than previously reported predictions due to increased fidelity in accounting for installation effects and gear design details. With the new method, it is now possible to reveal and assess the unique noise characteristics of landing gear systems for each type of aircraft. To address the inevitable uncertainties in predictions of landing gear noise models for future aircraft, an uncertainty analysis is given, using the method of Monte Carlo simulation. The standard deviation of the uncertainty in predicting the absolute level of landing gear noise is quantified and determined to be 1.4 EPNL dB.
Document ID
20160007658
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Guo, Yueping (NEAT Consulting Seal Beach, CA, United States)
Burley, Casey L. (NASA Langley Research Center Hampton, VA, United States)
Thomas, Russell H. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
June 16, 2016
Publication Date
January 4, 2016
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NF1676L-21517
Meeting Information
Meeting: 2016 AIAA SciTech Forum and Exposition
Location: San Diego, CA
Country: United States
Start Date: January 4, 2016
End Date: January 8, 2016
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 338881.02.07.07.08
Distribution Limits
Public
Copyright
Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available