An asymptotic theory of supersonic propeller noise

A theory for predicting the noise field of supersonic propellers with realistic blade geometries is presented. The theory, which utilizes a large-blade-count approximation, provides an efficient formula for predicting the radiation of sound from all three sources of propeller noise. Comparisons with a full numerical integration indicate that the levels predicted by this formula are quite accurate. Calculations also show that, for high speed propellers, the noise radiated by the Lighthill quadrupole source is rather substantial when compared with the noise radiated by the blade thickness and loading sources. Results from a preliminary application of the theory indicate that the peak noise level generated by a supersonic propeller initially increases with increasing tip helical Mach number, but is eventually reaches a plateau and does not increase further. The predicted trend shows qualitative agreement with the experimental observations

Prediction of noise field of a propfan at angle of attack

A method for predicting the noise field of a propfan operating at an angle of attack to the oncoming flow is presented. The method takes advantage of the high-blade-count of the advanced propeller designs to provide an accurate and efficient formula for predicting their noise field. The formula, which is written in terms of the Airy function and its derivative, provides a very attractive alternative to the use of numerical integration. A preliminary comparison shows rather favorable agreement between the predictions from the present method and the experimental data

Contra-Rotating Open Rotor Tone Noise Prediction

Reliable prediction of contra-rotating open rotor (CROR) noise is an essential element of any strategy for the development of low-noise open rotor propulsion systems that can meet both the community noise regulations and cabin noise limits. Since CROR noise spectra exhibit a preponderance of tones, significant efforts have been directed towards predicting their tone content. To that end, there has been an ongoing effort at NASA to assess various in-house open rotor tone noise prediction tools using a benchmark CROR blade set for which significant aerodynamic and acoustic data have been acquired in wind tunnel tests. In the work presented here, the focus is on the nearfield noise of the benchmark open rotor blade set at the cruise condition. Using an analytical CROR tone noise model with input from high-fidelity aerodynamic simulations, tone noise spectra have been predicted and compared with the experimental data. Comparisons indicate that the theoretical predictions are in good agreement with the data, especially for the dominant tones and for the overall sound pressure level of tones. The results also indicate that, whereas the individual rotor tones are well predicted by the combination of the thickness and loading sources, for the interaction tones it is essential that the quadrupole source is also included in the analysis

Influence of vane sweep on rotor-stator interaction noise

The influence of vane sweep in rotor-stator interaction noise is investigated. In an analytical approach, the interaction of a convected gust representing the rotor viscous wake, with a cascade of cascade of finite span swept airfoils, representing the stator, is analyzed. The analysis is based on the solution of the exact linearized equations of motion. High frequency convected gusts for which noise generation is concentrated near the leading edge of airfoils is considered. In a preliminary study, the problem of an isolated finite span swept airfoil interacting with a convected gust is analyzed. Results indicate that sweep can substantially reduce the farfield noise levels for a single airfoil. Using the single airfoil model, an approximate solution to the problem of noise radiation from a cascade of finite span swept airfoils interacting with a convected gust is derived. A parametric study of noise generated by gust cascade interaction is carried out to assess the effectiveness of vane sweep in reducing rotor-stator interaction noise. The results show that sweep is beneficial in reducing noise levels. Rotor wake twist or circumferential lean substantially influences the effectiveness of vane sweep. The orientation of vane sweep must be chosen to enhance the natural phase lag caused by wake lean, in which case rather small sweep angles substantially reduce the noise levels

Progress Toward N+1 Noise Goal

A review of the progress made towards achieving the Subsonic Fixed Wing project's noise goal for the next generation single aisle aircraft is presented. The review includes the technology path selected for achieving the goal as well as highlights from several in-house and partnership test programs that have contributed to this effort. In addition, a detailed, self-consistent, analysis of the aircraft system noise for a conceptual next generation single aisle aircraft is also presented. The results indicate that with the current suite of noise reduction technologies incorporated into the conceptual aircraft a cumulative noise reduction margin of 26 EPNdB could be expected. This falls 6 dB short of the N+1 goal, which is 32 EPNdB below Stage 4 noise standard. Potential additional noise reduction technologies to help achieve the goal are briefly discussed

Emerging Community Noise Reduction Approaches

An overview of the current NASA research portfolio in the area of aircraft noise reduction is presented. The emphasis of the research described herein is on meeting the aggressive near- and mid-term national goals for reducing aircraft noise emissions, which NASA internal studies have shown to be feasible using noise reduction technologies currently being developed in-house or in partnership with NASA s industry and academic partners. While NASA has an active research effort in airframe noise reduction, this overview focuses on propulsion noise reduction only

Fan Noise Source Diagnostic Test Completed and Documented

The specially organized session offered an international forum to disseminate the results from a year long test that was conducted in 1999 in NASA Glenn Research Center s 9- by 15-Foot Low-Speed Wind Tunnel on a 22-in. scale-model turbofan bypass stage, which was designed to be representative of current aircraft engine technology. The test was a cooperative effort involving Glenn, the NASA Langley Research Center, GE Aircraft Engines, and the Boeing Company. The principal objective of the project was to study the source mechanisms of noise in a modern high-bypass-ratio turbofan engine through detailed aerodynamic and acoustic measurements

Open Rotor Aeroacoustic Modelling

Owing to their inherent fuel efficiency, there is renewed interest in developing open rotor propulsion systems that are both efficient and quiet. The major contributor to the overall noise of an open rotor system is the propulsor noise, which is produced as a result of the interaction of the airstream with the counter-rotating blades. As such, robust aeroacoustic prediction methods are an essential ingredient in any approach to designing low-noise open rotor systems. To that end, an effort has been underway at NASA to assess current open rotor noise prediction tools and develop new capabilities. Under this effort, high-fidelity aerodynamic simulations of a benchmark open rotor blade set were carried out and used to make noise predictions via existing NASA open rotor noise prediction codes. The results have been compared with the aerodynamic and acoustic data that were acquired for this benchmark open rotor blade set. The emphasis of this paper is on providing a summary of recent results from a NASA Glenn effort to validate an in-house open noise prediction code called LINPROP which is based on a high-blade-count asymptotic approximation to the Ffowcs-Williams Hawkings Equation. The results suggest that while predicting the absolute levels may be difficult, the noise trends are reasonably well predicted by this approach

Open Rotor Noise Prediction - A Status Report

No abstract availabl

Partial replication with strong consistency

In response to the increasing expectations of their clients, cloud services exploit geo-replication to provide fault-tolerance, availability and low latency when executing requests. However, cloud platforms tend to adopt weak consistency semantics, in which replicas may diverge in state independently. These systems offer good response times but at the disadvantage of allowing potential data inconsistencies that may affect user experience. Some systems propose to adopt solutions with strong consistency, which are not as efficient but simplify the development of correct applications by guaranteeing that all replicas in the system maintain the same database state. Therefore, it is interesting to explore a system that can offer strong consistency while minimizing its main disadvantage: the impact in performance that results from coordinating every replica in the system. A possible solution to reduce the cost of replica coordination is to support partial replication. Partially replicating a database allows for each server to only be responsible for a subset of the data - a partition - which means that when updating the database only some of replicas have to be synchronized, improving response times. In this dissertation, we propose an algorithm that implements a distributed replicated database that offers strong consistency with support for partial replication. To achieve strong consistency in a partially replicated scenario, our algorithm is in part based on the Clock-SI[10] research, which presents an algorithm that implements a multi-versioned database for strong consistency (snapshot-isolation) and performs the Two-Phase Commit protocol when coordinating replicas during updates. The algorithm is supported by an architecture that simplifies distributing partitions among datacenters and efficiently propagating operations across nodes in the same partition, thanks to the ChainPaxos[27] algorithm.Como forma de responder às expectativas cada vez maiores dos seus clientes, as operadoras cloud tiram partido da geo-replicação para oferecer tolerância a falhas, disponibilidade e baixa latência dos seus sistemas na resposta aos pedidos. No entanto, as plataformas cloud tendem a adotar uma semântica de consistência fraca, na qual as réplicas podem variar em estado de forma independente. Estes sistemas oferecem bons tempos de resposta mas com a desvantagem de que têm de lidar com potenciais inconsistências nos dados que podem ter impacto na experiência dos utilizadores. Alguns sistemas propõem adotar soluções com consistência forte, as quais não são tão eficientes mas simplificam o desenvolvimento de aplicações ao garantir que todas as réplicas do sistema mantêm o mesmo estado da base de dados. É então interessante explorar um sistema que garanta replicação forte mas que minimize a sua principal desvantagem: o impacto de performance no momento de coordenar o estado das réplicas nos sistema. Uma possível solução para reduzir o custo de coordenação das réplicas durante transações é o suporte à replicação parcial. Replicar parcialmente uma base de dados permite que cada servidor seja apenas responsável por uma parte dos dados - uma partição - o que significa que quando são realizadas escritas apenas algumas das réplicas têm de ser sincronizadas, melhorando os tempos de resposta. Neste trabalho propomos um algoritmo que implementa um sistema de armazenamento distríbuido replicado que oferece consistência forte com suporte a replicação parcial. A fim de garantir consistência forte num cenário de replicação parcial, o nosso algoritmo é em parte baseado no algoritmo Clock-SI[10], que implementa uma base de dados parcial com multi-versões para garantir consistência forte (snapshot-isolation) e que realiza o protocolo Two-Phase Commit para coordenar as réplicas no momento de aplicar escritas. O algoritmo é suportado por uma arquitectura que torna simples distribuir partições por vários centros de dados e propagar de forma eficiente operações entre todos os nós numa mesma partição, através do algoritmo ChainPaxos[27]