scholarly journals Guidelines for the LTO Noise Assessment of Future Civil Supersonic Aircraft in Conceptual Design

Aerospace ◽  
2022 ◽  
Vol 9 (1) ◽  
pp. 27
Author(s):  
Grazia Piccirillo ◽  
Nicole Viola ◽  
Roberta Fusaro ◽  
Luigi Federico
Keyword(s):  
Conceptual Design ◽  
Aircraft Design ◽  
Low Noise ◽  
Aircraft Noise ◽  
Noise Model ◽  
Noise Power ◽  
Community Noise ◽  
Prediction Program ◽  
Supersonic Aircraft ◽  
Noise Assessment

One of the most critical regulatory issues related to supersonic flight arises from limitations imposed by community noise acceptability. The most efficient way to ensure that future supersonic aircraft will meet low-noise requirements is the verification of noise emissions from the early stages of the design process. Therefore, this paper suggests guidelines for the Landing and Take-Off (LTO) noise assessment of future civil supersonic aircraft in conceptual design. The supersonic aircraft noise model is based on the semi-empirical equations employed in the early versions of the Aircraft NOise Prediction Program (ANOPP) developed by NASA, whereas sound attenuation due to atmospheric absorption has been considered in accordance with SAE ARP 866 B. The simulation of the trajectory leads to the prediction of the aircraft noise level on ground in terms of several acoustic metrics (LAmax, SEL, PNLTM and EPNL). Therefore, a dedicated validation has been performed, selecting the only available supersonic aircraft of the Aircraft Noise and Performance database (ANP), that is, the Concorde, through the matching with Noise Power Distance (NPD) curves for LAmax and SEL, obtaining a maximum prediction error of ±2.19%. At least, an application to departure and approach procedures is reported to verify the first noise estimations with current noise requirements defined by ICAO at the three certification measurement points (sideline, flyover, approach) and to draw preliminary considerations for future low-noise supersonic aircraft design.

EPISTLE: High lift system design for low-noise applied to a supersonic aircraft

2006 ◽  
Vol 110 (1107) ◽  
pp. 327-331 ◽  
Author(s):  
U. Herrmann
Keyword(s):  
System Design ◽  
Aircraft Design ◽  
Reynolds Numbers ◽  
Low Noise ◽  
High Lift ◽  
New Approach ◽  
Low Speed ◽  
Supersonic Aircraft ◽  
Preliminary Aircraft Design ◽  
High Reynolds

Abstract A new approach for low-drag high-lift system design based on the application of viscous flow solvers was developed in the EC research project EPISTLE. Two high-lift systems for a supersonic commercial transport aircraft (SCT) wing were designed, manufactured and wind-tunnel tested. The predicted large drag reductions were fully confirmed by tests at high Reynolds numbers. These drag reductions significantly reduce the low-speed noise of future SCT configurations. This was estimated by preliminary aircraft design tools. Low-speed noise reduction by aerodynamic means is obtained, as effective high-lift systems enable these aircraft to climb faster.

Tradeoff of Airframe Noise and Field Length in Conceptual Design of Airliner

2013 ◽  
Vol 295-298 ◽  
pp. 2026-2029 ◽  
Author(s):  
Manandhar Ashish ◽  
Shuai Zhang ◽  
Xiong Qing Yu
Keyword(s):  
Conceptual Design ◽  
Noise Level ◽  
Aircraft Noise ◽  
Noise Prediction ◽  
Noise Levels ◽  
Wing Area ◽  
Airframe Noise ◽  
Prediction Program ◽  
Noise Signature

The purpose of this paper is to present a tradeoff study of airframe noise and field length due to wing area and flap setting configuration during conceptual design. The aircraft takeoff and landing length is predicted by the Matlab synthesis code for airliner conceptual design. The NASA’s Aircraft Noise Prediction Program (ANOPP) is used to evaluate the airframe noise signature. It is found that: (1) with the increase in wing area both the landing and takeoff field length will be reduced, and approach noise decreases whereas the takeoff noise increases; (2) with the increase in flap setting from 50 to 200, both landing and takeoff field length reduces but the noise level increases during takeoff and decreases during the approach. The results can help designers to select suitable values of wing area and flap setting to meet both the requirements of field length and noise levels.

Comparison of two community noise models applied to a NASA urban air mobility concept vehicle

2021 ◽  
Vol 263 (6) ◽  
pp. 787-798
Author(s):  
Juliet Page ◽  
Stephen A. Rizzi ◽  
Rui Cheng
Keyword(s):  
Noise Exposure ◽  
Simulation Method ◽  
Design Tool ◽  
Noise Model ◽  
Urban Air ◽  
Noise Power ◽  
Modeling Tools ◽  
Community Noise ◽  
Propagation Modeling ◽  
Concept Vehicle

Predictions of community noise exposure from the NASA urban air mobility (UAM) concept vehicles have been conducted for representative operations using the FAA Aviation Environmental Design Tool (AEDT) in order to demonstrate modeling tool interoperability and assess applicability, capabilities and limitations of integrated noise modeling tools. To both quantify limitations and highlight other capabilities, a comparative analysis is performed using a time simulation method, in particular, using the Volpe Advanced Acoustic Model (AAM). Starting with the same source noise model, the 3D directivity of a UAM concept vehicle is predicted in terms of aeroacoustic pressure time histories at a sphere of observers near the vehicle. In addition to distilling those data to a set of noise-power-distance data for input to AEDT, the data are processed preserving directivity, into narrowband, one-twelfth and one-third octave bands for input to AAM. Results from AEDT and AAM modeling are provided for a variety of metrics to demonstrate the effect that source noise and propagation modeling fidelity have on predicted results at receptors over a study area.

scholarly journals Conceptual design of sonic boom stealth supersonic transports

2022 ◽  
Author(s):  
Yicheng Sun ◽  
Howard Smith
Keyword(s):  
Conceptual Design ◽  
Aircraft Design ◽  
Design Model ◽  
Sonic Boom ◽  
Volume Distribution ◽  
Design Environment ◽  
Supersonic Aircraft ◽  
Business Jet ◽  
Multidisciplinary Perspective ◽  
Aircraft Conceptual Design

AbstractThis paper introduces a supersonic transport aircraft design model developed in the GENUS aircraft conceptual design environment. A conceptual design model appropriate to supersonic transports with low-to-medium-fidelity methods are developed in GENUS. With this model, the authors reveal the relationship between the sonic boom signature and the lift and volume distributions and the possibility to optimise the lift distribution and volume distribution together so that they can cancel each other at some region. A new inspiring design concept—sonic boom stealth is proposed by the authors. The sonic boom stealth concept is expected to inspire the supersonic aircraft designers to design low-boom concepts through aircraft shaping and to achieve low ground impacts. A family of different classes of supersonic aircraft, including a single-seat supersonic demonstrator (0.47 psf), a 10-passenger supersonic business jet (0.90 psf) and a 50-seat supersonic airliner (1.02 psf), are designed to demonstrate the sonic boom stealth design principles. Although, there are challenges to balance the volume with packaging and control requirements, these concepts prove the feasibility of low-boom low-drag design for supersonic transports from a multidisciplinary perspective.

scholarly journals Application of Noise Certification Regulations within Conceptual Aircraft Design

Aerospace ◽  
2021 ◽  
Vol 8 (8) ◽  
pp. 210
Author(s):  
Michel Nöding ◽  
Lothar Bertsch
Keyword(s):  
Conceptual Design ◽  
Aircraft Design ◽  
Low Noise ◽  
Operating Conditions ◽  
Published Data ◽  
Design Phase ◽  
Simulation Process ◽  
Research Activities ◽  
Conceptual Design Phase ◽  
Conceptual Aircraft Design

ICAO Annex 16 regulations are used to certify the acoustic performance of subsonic transport aircraft. Each aircraft is classified according to the measured EPNL levels at specific certification locations along the approach and departure. By simulating this certification process, it becomes possible to identify all relevant parameters and assess promising measures to reduce the noise certification levels in compliance with the underlying ICAO regulations, i.e., allowable operating conditions of the aircraft. Furthermore, simulation is the only way to enable an assessment of novel technology and non-existing vehicle concepts, which is the main motivation behind the presented research activities. Consequently, the ICAO Annex 16 regulations are integrated into an existing noise simulation framework at DLR, and the virtual noise certification of novel aircraft concepts is realized at the conceptual design phase. The predicted certification levels can be directly selected as design objectives in order to realize an advantageous ICAO noise category for a new aircraft design, i.e., simultaneously accounting for the design and the resulting flight performance. A detailed assessment and identification of operational limits and allowable flight procedures for each conceptual aircraft design under consideration is enabled. Sensitivity studies can be performed for the relevant input parameters that influence the predicted noise certification levels. Specific noise sources with a dominating impact on the certification noise levels can be identified, and promising additional low-noise measures can be applied within the conceptual design phase. The overall simulation process is applied to existing vehicles in order to assess the validity of the simulation resultsfcompared to published data. Thereafter, the process is applied to some DLR low-noise aircraft concepts to evaluate their noise certification levels. These results can then be compared to other standard noise metrics that are typically applied in order to describe aircraft noise, e.g., SEL isocontour areas. It can be demonstrated that certain technologies can significantly reduce the noise impact along most of an approach or departure flight track but have only a limited influence on the noise certification levels and vice versa. Finally, an outlook of the ongoing developments is provided, in order to apply the new simulation process to supersonic aircraft. Newly proposed regulations for such concepts are implemented into the process in order to evaluate these new regulations and enable direct comparison with existing regulations.

scholarly journals Aircraft noise in residential areas, problems of measuring and evaluation

2020 ◽  
Vol 99 (10) ◽  
pp. 1042-1048
Author(s):  
Igor V. Bukhtiyarov ◽  
Nicolay N. Courierov ◽  
Alla V. Lagutina ◽  
Lyudmila V. Prokopenko ◽  
Evgeny V. Zibarev
Keyword(s):  
Low Noise ◽  
Aircraft Noise ◽  
Time Interval ◽  
Residential Areas ◽  
Reference Time ◽  
Sound Levels ◽  
Sound Event ◽  
Noise Assessment ◽  
Normalized Parameters ◽  
Definition Of

The intensity of civil aircraft flights elevates with the increase in the number of passenger and cargo transportation by air. Aircraft noise in the residential area near airports grows up too despite the use of low-noise aircraft models by airlines. This causes an augmentation in the number of complaints of the population in these areas. The Russian Federation’s normative and methodological documents requirements in force relating to measurements and assessment of noise in residential areas, including «aircraft noise», were analyzed. Their requirements in terms of measuring and assessing noise in residential areas, including “aircraft noise”, testifies to the insufficiency and ambiguity of these requirements. The main disadvantages are the lack of a clear definition of which sound event is considered «aircraft noise» and the lack of requirements for the duration of the reference time interval of noise measurement. The foreign experience of measuring and evaluating aircraft noise, as well as the effects of such noise on the population, are considered. This made it possible to determine the necessary and sufficient parameters for noise control in residential areas, including «aircraft noise». There were proposed both a definition of «aircraft noise» and the necessary parameters for its assessment. The necessary duration of the reference time interval for the measurement of normalized parameters was justified. Method for the normalized noise parameters in residential areas measurement using the chronograms of sound levels A was proposed. The technical implementation of such a method is presented. Proposed a definition of «aircraft noise» and measuring normalized parameters in the 15-minute reference time interval for inclusion in regulatory and methodological documents will help to eliminate ambiguity in measurements and noise assessment in residential areas.

Effects of Increased Noise Levels by Supersonic Aircraft on Annoyance Levels and Time Estimations

1980 ◽  
Vol 50 (2) ◽  
pp. 563-569
Author(s):  
John A. Allen
Keyword(s):  
Aircraft Noise ◽  
Noise Levels ◽  
Supersonic Aircraft ◽  
International Airport

Several tests designed to assess the effects of increased noise levels created by the Concorde supersonic aircraft were administered to 48 residents living around Dulles International Airport and 31 persons not living near an airport. Results of a pretest questionnaire and lack of significant changes in annoyance levels and time estimations indicate that, while airport-area residents may be more conscious of aircraft noise, changes in the perceived intensities of sounds may not occur.

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