Journal of Aircraft最新文献_第9页

Statistical Analysis of the Surface Roughness on Aircraft Icing 飞机结冰表面粗糙度统计分析

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-12-29 DOI: 10.2514/1.c037403

Denis Sotomayor-Zakharov, Emmanuel Radenac, Mariachiara Gallia, Alberto Guardone, Inken Knop

引用次数: 0

Verification of the [math] Transition Model in OVERFLOW and FUN3D 验证 OVERFLOW 和 FUN3D 中的[数学]转换模型

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-12-28 DOI: 10.2514/1.c037445

Balaji Shankar Venkatachari, Preethi V. Mysore, Nathaniel Hildebrand, Meelan M. Choudhari, Marie F. Denison

引用次数: 0

Toward Estimating Noise–Power–Distance Curves for Propeller-Powered Zero-Emission Hydrogen Aircraft 估算螺旋桨零排放氢气飞机的噪声-功率-距离曲线

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-12-21 DOI: 10.2514/1.c037194

Daniel C. Amargianitakis, Rodney H. Self, Antonio J. Torija, Anderson R. Proença, Athanasios P. Synodinos

{"title":"Toward Estimating Noise–Power–Distance Curves for Propeller-Powered Zero-Emission Hydrogen Aircraft","authors":"Daniel C. Amargianitakis, Rodney H. Self, Antonio J. Torija, Anderson R. Proença, Athanasios P. Synodinos","doi":"10.2514/1.c037194","DOIUrl":"https://doi.org/10.2514/1.c037194","url":null,"abstract":"As part of the UK Research and Innovation project New Aviation, Propulsion, Knowledge and Innovation Network (NAPKIN), a high-level framework was developed for the assessment of the noise impact of the proposed regional-sized hydrogen-powered aircraft. This study consists of the methodology used to generate the industry-standard noise–power–distance (NPD) curves from individual component noise analysis, specifically propeller tonal noise. The model is based on an asymptotic analysis of a frequency domain propeller tonal noise model combined with a linear approximation, taking advantage of the logarithmic nature of noise. An error analysis on the linear approximation assumption proves that the relative error between predicted and actual values of the noise remains below 10% for appropriately chosen baseline points. Verification of the framework was achieved through a bench-marking procedure that compared predictions of departure NPD curves for current technology regional aircraft against published ones over a range of operational power settings. Finally, departure and approach NPD predictions for three of the NAPKIN hydrogen concept aircraft are presented. Concepts featuring a larger, slower-rotating propeller with an increased number of blades relative to the reference aircraft showed benefits over the reference aircraft, despite, in some cases, increases in maximum takeoff weight.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":null,"pages":null},"PeriodicalIF":2.2,"publicationDate":"2023-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138949350","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Meshless Large-Eddy Simulation of Propeller–Wing Interactions with Reformulated Vortex Particle Method 用重新制定的涡流粒子法对螺旋桨与机翼的相互作用进行无网格大埃迪模拟

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-12-21 DOI: 10.2514/1.c037279

Eduardo J. Álvarez, Andrew Ning

{"title":"Meshless Large-Eddy Simulation of Propeller–Wing Interactions with Reformulated Vortex Particle Method","authors":"Eduardo J. Álvarez, Andrew Ning","doi":"10.2514/1.c037279","DOIUrl":"https://doi.org/10.2514/1.c037279","url":null,"abstract":"The vortex particle method (VPM) has gained popularity in recent years due to a growing need to predict complex aerodynamic interactions during the preliminary design of electric multirotor aircraft. However, VPM is known to be numerically unstable when vortical structures break down close to the turbulent regime. In recent work, the VPM has been reformulated as a large-eddy simulation (LES) in a scheme that is both meshless and numerically stable without increasing its computational cost. In this study, we build upon this meshless LES scheme to create a solver for interactional aerodynamics. Propeller blades are introduced through an actuator line model following well-established practices for LES. A novel, vorticity-based actuator surface model (ASM) is developed for wings, which is suitable for propeller–wing interactions when a wake impinges on the surface of a wing. This ASM imposes the no-flow-through condition at the airfoil centerline by calculating the circulation that meets this condition and by immersing the associated vorticity in the LES following a pressure-like distribution. Extensive validation of propeller–wing interactions is presented by simulating a tailplane with tip-mounted propellers and a blown wing with propellers mounted midspan.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":null,"pages":null},"PeriodicalIF":2.2,"publicationDate":"2023-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138950300","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Two Aerodynamic Mid-Fidelity Approaches on a Distributed Propulsion Wing 分布式推进翼的两种空气动力中模拟方法

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-12-18 DOI: 10.2514/1.c037313

Nikolai Herzog, Dennis Keller, Christian Breitsamter

引用次数: 0

Aerostructural Optimization and Comparative Study of Twin-Fuselage and Strut-Braced-Wing Aircraft Configurations 双机身和支撑翼飞机结构优化与比较研究

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-12-09 DOI: 10.2514/1.c037388

Yiyuan Ma, Morteza Abouhamzeh, Ali Elham

引用次数: 0

Structural and Aerodynamic Preliminary Design Optimization for Highly Flexible Wing–Tail Configuration 高柔性翼尾结构与气动初步设计优化