Aircraft Design最新文献_第7页

Navier–Stokes analysis of lift-enhancing tabs on multi-element airfoils 多单元翼型升力增强片的Navier-Stokes分析

Aircraft Design Pub Date : 1998-09-01 DOI: 10.1016/S1369-8869(98)00014-7

Paul G. Carrannanto , Bruce L. Storms , James C. Ross , Russell M. Cummings

引用次数: 20

The conceptual design of deck-launched waverider-configured aircraft 甲板发射乘波器配置飞机的概念设计

Aircraft Design Pub Date : 1998-09-01 DOI: 10.1016/S1369-8869(98)00015-9

Conrad F. Newberry

引用次数: 3

Propulsion system design with smart vortex generators 智能涡发生器推进系统设计

Aircraft Design Pub Date : 1998-09-01 DOI: 10.1016/S1369-8869(98)00012-3

S. Farokhi

{"title":"Propulsion system design with smart vortex generators","authors":"S. Farokhi","doi":"10.1016/S1369-8869(98)00012-3","DOIUrl":"10.1016/S1369-8869(98)00012-3","url":null,"abstract":"<div><p>Adverse flow environments pose challenging design constraints in aircraft engine components and component interactions. Some examples of such flow environments are: steep pressure gradients, random and periodic unsteadiness, shock wave interactions and 3-D boundary layer separation. These adverse flow environments and interactions promote the growth of various kinds of instability waves inherent in gas turbine engines, e.g., vorticity wave, entropy wave and acoustic or pressure wave instabilities. A series of smart subsonic and supersonic flow controllers are presented with applications to the design of aircraft gas turbine engine components. They are <em>on-demand</em> vortex generators capable of injecting co- and counter-rotating streamwise vortices in subsonic, transonic and supersonic flow. The strength and location of the vortex is a control variable and must be optimized via a closed-loop control algorithm. The subsonic smart VG assumes a ramp-type geometry (similar to Wheeler vortex generators) and the smart supersonic VG is a tailored cavity with a movable flap concealing the cavity. The movable flap is actuated inward to expose the cavity to transonic or supersonic flow. The depth of the cavity is controlled via a closed-loop feedback control system which ties the strength of the vortex to the “desired” performance as measured by one or more sensors. Candidate <em>cost functions</em> are proposed in the optimization routine for each component in a gas turbine engine.</p></div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"1 3","pages":"Pages 127-143"},"PeriodicalIF":0.0,"publicationDate":"1998-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(98)00012-3","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"73000881","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 8

A brief look at the legacy and future of the United States Navy’s carrier-based support aircraft 简要介绍美国海军舰载支援飞机的历史和未来

Aircraft Design Pub Date : 1998-06-01 DOI: 10.1016/S1369-8869(98)00007-X

Mark H. Norris

引用次数: 0

Numerical investigation of an airfoil with a Gurney flap 带轮尼襟翼翼型的数值研究

Aircraft Design Pub Date : 1998-06-01 DOI: 10.1016/S1369-8869(98)00010-X

Cory S. Jang , James C. Ross , Russell M. Cummings

{"title":"Numerical investigation of an airfoil with a Gurney flap","authors":"Cory S. Jang , James C. Ross , Russell M. Cummings","doi":"10.1016/S1369-8869(98)00010-X","DOIUrl":"10.1016/S1369-8869(98)00010-X","url":null,"abstract":"<div><p>A two-dimensional numerical investigation was performed to determine the effect of a Gurney flap on a NACA 4412 airfoil. A Gurney flap is a flat plate on the order of 1–3% of the airfoil chord in length, oriented perpendicular to the chord line and located on the airfoil windward side at the trailing edge. The flowfield around the airfoil was numerically predicted using INS2D, an incompressible Navier–Stokes solver, and the one-equation turbulence model of Baldwin and Barth. Gurney flap sizes of 0.5%, 1.0%, 1.25%, 1.5%, 2.0%, and 3.0% of the airfoil chord were studied. Computational results were compared with available experimental results. The numerical solutions show that some Gurney flaps increase the airfoil lift coefficient with only a slight increase in drag coefficient. Use of a 1.5% chord length Gurney flap increases the airfoil lift coefficient by Δ<em>C</em><sub><em>l</em></sub>≈0.3 and decreases the angle of attack required to obtain a given lift coefficient by Δ<em>α</em><sub><em>L</em>=0</sub>>−3°. The numerical solutions show the details of the flow structure at the trailing edge and provide a possible explanation for the increased aerodynamic performance.</p></div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"1 2","pages":"Pages 75-88"},"PeriodicalIF":0.0,"publicationDate":"1998-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(98)00010-X","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"85031072","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 99

A century of phugoid approximations 一个世纪的奇异近似

Aircraft Design Pub Date : 1998-06-01 DOI: 10.1016/S1369-8869(98)00011-1

S. Pradeep

引用次数: 16

Converting A Citation Business Jet to a military trainer 将引文公务机转换为军事教练机

Aircraft Design Pub Date : 1998-03-01 DOI: 10.1016/S1369-8869(98)00006-8

James W. Lyle Jr

{"title":"Converting A Citation Business Jet to a military trainer","authors":"James W. Lyle Jr","doi":"10.1016/S1369-8869(98)00006-8","DOIUrl":"10.1016/S1369-8869(98)00006-8","url":null,"abstract":"<div><p>The United States Navy needed a replacement for aging T-39 Naval Flight Officer (NFO) training aircraft. NFOs perform radar and navigation functions on Navy aircraft. It was decided that conversion of FAA certified business aircraft would be the most economical approach. They also upgraded the ground-based training systems. The Cessna Aircraft Company won the competition, proposing the Citation Model 550 which had to be heavily modified to meet the rigorous training requirements, including high G air intercept maneuvers and high-speed low-level flight. Wing, tail, tailcone, and windshield beef-up and higher thrust engines resulted in a new FAA certification and a new model number assigned to the aircraft as well as the Military T-47A designation. The interior of the aircraft was changed to accommodate an instructor, two students in the cabin and one in the copilot position. The copilot instrument panel was dominated by the radar display similar to Navy attack aircraft and the airplane was flown single pilot. Cessna, on its own initiative, performed a full-scale fatigue life test and gathered field service data to prove the design was satisfactory. The Navy declared the T-47A training system was the most successful during the T-47A tenure.</p></div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"1 1","pages":"Pages 51-60"},"PeriodicalIF":0.0,"publicationDate":"1998-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(98)00006-8","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"74000544","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

Risk analysis: sample application to a totally new aircraft design 风险分析:在全新飞机设计中的应用

Aircraft Design Pub Date : 1998-03-01 DOI: 10.1016/S1369-8869(98)00002-0

Daniele Camatti, Sergio Chiesa, Paolo Maggiore

引用次数: 3

Next generation attack fighter conceptual design study 下一代攻击机概念设计研究

Aircraft Design Pub Date : 1998-03-01 DOI: 10.1016/S1369-8869(98)00005-6

Daniel P. Raymer

{"title":"Next generation attack fighter conceptual design study","authors":"Daniel P. Raymer","doi":"10.1016/S1369-8869(98)00005-6","DOIUrl":"10.1016/S1369-8869(98)00005-6","url":null,"abstract":"<div><p>Current Air Force, Navy, and Marine Corps fighter/attack aviation aircraft are 1970s-vintage designs which will reach the ends of their service lives in the early part of the next century. While the Air Force is developing the highly-advanced F-22, it cannot be used to replace all current assets, especially F-16’s, simply due to cost. A “low-end” complementary design is required, much as the F-16 was the “low” of a “high-low mix” with F-15’s. The Navy’s F-18 E/F will have improved characteristics compared to earlier versions, but it does not fully utilize newer technologies and specifically will not have the attainable levels of stealth and range-payload performance, nor will it offer next-generation STOVL capability for the Marines. RAND’s Project Air Force conducted research into the tradeoffs in requirements specification for a next-generation attack fighter during the period from 1993 to 1995. As a part of that, this author developed and analyzed a representative notional design concept for a Next-Generation Attack Fighter (NGAF), then conducting trade studies of range, performance, payload, and technologies, followed by study of alternative approaches to attaining tri-service capability.</p></div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"1 1","pages":"Pages 43-49"},"PeriodicalIF":0.0,"publicationDate":"1998-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(98)00005-6","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"83060534","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

A flexible method for the off-design analysis of SST powerplant installations suitable for global optimization 一种适合全局优化的SST动力装置非设计分析的灵活方法

Aircraft Design Pub Date : 1998-03-01 DOI: 10.1016/S1369-8869(98)00003-2

Dolf Bos

引用次数: 1