Publications
Thesis
M.S. Thesis
University of California, Irvine
Methodology for Analyzing Multi Propeller Aircraft Community Noise and Procedural Applications
This work presents, outlines, and demonstrates a methodology used to analyze the community noise of multi propeller aircraft as well noise of procedural applications. This methodology is capable of propeller performance analysis and design, aircraft source noise modeling, and source noise propagation over a community. Aircraft source noise modeling captures the noise generated from propeller and aircraft geometry at local operating conditions such as onset velocity and propeller RPM. Noise propagation captures changes in altitude, attitude, and propeller performance over distance or time as specified by a flight profile.
Conference Papers
AIAA Aviation 2022
Paper Presenter
Chicago, Illinois
Component Noise Modeling for Distributed Propulsion Blown-Flap STOL Vehicle Flight Procedures
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This paper describes the development of a component-based noise modeling methodology to examine flight procedures and resulting community noise levels for distributed propulsion (DP), blown-flap Short Takeoff and Landing (STOL) aircraft for Advanced Air Mobility applications. Distributed propulsion and blown-flaps present unique sources of noise that must be modeled to assess the overall procedural noise levels. The present methodology assesses the impact of propeller wake velocity, thrust, and flap configuration, which govern the flight performance characteristics of these aircraft, on noise. These performance states, airframe geometries, and flight procedure parameters such as flight path angle and speed, are inputted into a noise modeling framework that incorporates methods from the NASA Aircraft NOise Prediction Program 2.
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AIAA Aviation 2023
Paper Presenter
San Diego, CA
Flight Procedure and Community Noise Modeling of Advanced Air Mobility Flight Vehicles
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This paper describes the development of a component-based noise modeling methodology to examine flight procedures and resulting community noise levels for distributed propulsion (DP), blown-flap Short Takeoff and Landing (STOL) aircraft for Advanced Air Mobility applications. DP blown-flap STOL aircraft are able to achieve short takeoff and landing field lengths and steep climb and descent profiles, which are shown in a demonstration flight test to have potentially lower overflight noise levels in comparison to conventional flight procedures. However, distributed propulsion and blown-flaps present unique sources of noise that must be modeled to assess the overall procedural noise levels. The present methodology assesses the impact of propeller wake velocity, thrust, and flap configuration, which govern the flight performance characteristics of these aircraft, on noise. These performance states, airframe geometries, and flight procedure parameters such as flight path angle and speed, are inputted into a noise modeling framework that incorporates methods from the NASA Aircraft NOise Prediction Program 2. Such a framework predicts engine and airframe component noise, emphasizing propeller noise and propeller wake influence on flaps. The modeling results when demonstrated on a sub-scale STOL aircraft indicate that propeller noise is dominant during departure and cruise, but propeller wake-flap interaction noise can be significant on approach procedures. Modeling results also indicate that DP STOL aircraft equipped with high-lift devices have wide operating conditions, leading to the potential to optimize flight procedures for noise attenuation.
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