Aircraft Design最新文献_第5页

Aerodynamic characteristics of multi-surface aircraft configurations 多面飞机构型气动特性研究

Aircraft Design Pub Date : 1999-12-01 DOI: 10.1016/S1369-8869(99)00015-4

Z Pátek , L Smrcek

{"title":"Aerodynamic characteristics of multi-surface aircraft configurations","authors":"Z Pátek , L Smrcek","doi":"10.1016/S1369-8869(99)00015-4","DOIUrl":"https://doi.org/10.1016/S1369-8869(99)00015-4","url":null,"abstract":"<div>This paper describes the wind tunnel testing of a specially designed aircraft model allowing systematic variation of geometric parameters related to overall aircraft configurations. The experiment work was carried out in the 1.8 m low-speed wind tunnel at VZLU, Aeronautical Research and Test Institute in Prague. The resultant data created an aerodynamic database for numerical modelling and verification. In addition, numerical validation of CFD package FLUENT was performed in the computerised fluid dynamic laboratory at the Department of Aerospace Engineering, University of Glasgow as a part of the ongoing research collaboration between both institutions. The wind-tunnel test program had two aims<ul><li>•to provide basic aerodynamic data effects of multi-surface aircraft configurations with a view to assessing the degree to which specific design features such as a combination of canard, wing and tail plane are beneficial to aircraft aerodynamic performance</li><li>•to provide an aerodynamic database for numerical validation.</li></ul>\u0000The aerodynamic data for different geometrical aircraft configurations with the same wing, fuselage, horizontal tail and canard surfaces were compared. The results show the magnitude of lift, drag and pitching moment depending on the angle of attack and various positions of canard, wing and horizontal tail with respect to one another. They have been compared with studied references. The experimental results are in accordance with theoretical predictions.</div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"2 4","pages":"Pages 191-206"},"PeriodicalIF":0.0,"publicationDate":"1999-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(99)00015-4","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"91754927","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: 7

A new numerical design tool for concept evaluation of propeller aircraft 一种新的螺旋桨飞机概念评估数值设计工具

Aircraft Design Pub Date : 1999-09-01 DOI: 10.1016/S1369-8869(99)00012-9

X Xie, Ch Haberland

{"title":"A new numerical design tool for concept evaluation of propeller aircraft","authors":"X Xie, Ch Haberland","doi":"10.1016/S1369-8869(99)00012-9","DOIUrl":"10.1016/S1369-8869(99)00012-9","url":null,"abstract":"<div>Besides the conceptual configuration development of an aircraft, a modern design tool should cover the evaluation of competitor aircraft, allow the assessment of technological and operational scenarios, and thus should have the potential to `right first time design'. For that purpose, the design system VisualCAPDA was developed on the basis of the former CAPDA system by evolutionarily introducing modern software standards under the premise of maximum reusability of existing FORTRAN coded methods. The new system plays the role of a workbench, which has to provide the analysis methods and necessary data. Through a graphical user interface the application of the system comes along as comfortable for the user as possible. In order to cover also turboprop aircraft, new modules with respect to cabin layout, propeller aerodynamic and acoustic analysis, propeller slip stream, engine modeling, geometry modeling are integrated into the design tool. The flexibility of the new system is demonstrated by applying it to the configurational development of propeller aircraft, investigating actual problems such as `Twin or Quad', `Turboprop or Turbofan', and finally, dealing with typical optimization problems.</div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"2 3","pages":"Pages 147-165"},"PeriodicalIF":0.0,"publicationDate":"1999-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(99)00012-9","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"72985433","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

Rotary cockpit compartment—design concept and control strategy 旋转座舱舱室设计概念与控制策略

Aircraft Design Pub Date : 1999-06-01 DOI: 10.1016/S1369-8869(99)00010-5

S.M Malaek, K Hodjat, M Dorri

引用次数: 0

Intake-engine matching for high-speed civil transport powerplant design and analysis 高速民用运输动力装置进气发动机匹配设计与分析

Aircraft Design Pub Date : 1999-06-01 DOI: 10.1016/S1369-8869(99)00009-9

Adolf H.W Bos

{"title":"Intake-engine matching for high-speed civil transport powerplant design and analysis","authors":"Adolf H.W Bos","doi":"10.1016/S1369-8869(99)00009-9","DOIUrl":"10.1016/S1369-8869(99)00009-9","url":null,"abstract":"<div>This paper addresses the necessity to incorporate an intake-engine matching procedure in any procedure to analyze the off-design performance of engines designed to power high-speed civil transport aircraft. Most methods known to the author that are useable in the conceptual design phase of the aircraft (a phase characterized by the fact that very few design variables are known) only analyze the performance of the engine, without taking into account the design and performance of the intake. It will be shown in this paper, that the intake and the design exhibit a strong mutual influence, that cannot be neglected. An alternative method of analysis is presented. Particular reference will be made to the phenomenon of excess air and the resulting spillage drag. It will be shown that spillage air can be quite large in case of an HSCT design, especially in case the engine is designed for a high cruise Mach number. Assuming the presence of a sophisticated intake system generating multiple shocks in order to optimize the intake efficiency at the cruise condition, excess air at lower Mach numbers can amount to more than 60%.</div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"2 2","pages":"Pages 95-104"},"PeriodicalIF":0.0,"publicationDate":"1999-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(99)00009-9","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"80186402","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: 0

Mission and concept evaluation for a multirole, mission-adaptable air vehicle 多用途、任务适应性飞行器的任务和概念评估

Aircraft Design Pub Date : 1999-06-01 DOI: 10.1016/S1369-8869(99)00003-8

V.L. Wells , J.W. Rutherford , A.M. Corgiat

{"title":"Mission and concept evaluation for a multirole, mission-adaptable air vehicle","authors":"V.L. Wells , J.W. Rutherford , A.M. Corgiat","doi":"10.1016/S1369-8869(99)00003-8","DOIUrl":"10.1016/S1369-8869(99)00003-8","url":null,"abstract":"<div>The paper describes the results from a concept exploration study to assess the feasibility of a modular/reconfigurable rotorcraft designated the “multirole, mission-adaptable air vehicle (MRMAAV)”. The initial phase of the study consisted of developing mission and operational requirements for the vehicle. This phase resulted in the assessment that the aircraft should be considered primarily an attack vehicle but with the capability, through reconfiguration, for performing several alternate missions. Evaluation of several high-speed rotorcraft concepts led to the selection of two platform configurations for further study. These included the variable-diameter compound helicopter (VDCH) and the joined-wing tilt rotor (JWTR). Detailed sizing efforts focused on the VDCH as the more feasible of the two concepts. Innovative aspects of the air vehicle include variable-diameter main rotor, turboshaft/turbofan convertible engine, virtual-canopy cockpit, and reconfigurable payload bay. The mission-equipment package is highlighted by an autonomous remote sensor platform. The study identifies areas which best lend themselves to a modular or reconfigurable design approach and describes in detail a candidate vehicle meeting the MRMAAV objectives.</div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"2 2","pages":"Pages 65-80"},"PeriodicalIF":0.0,"publicationDate":"1999-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(99)00003-8","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"76422183","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: 6

An air-launched, self-recovering autonomous vehicle concept 一种空中发射、自我回收的自动驾驶概念车

Aircraft Design Pub Date : 1999-06-01 DOI: 10.1016/S1369-8869(99)00005-1

J.W. Rutherford , V.L. Wells

引用次数: 2

Computational investigation of slot blowing for fuselage forebody flow control 机身前体气流控制的狭缝吹气计算研究

Aircraft Design Pub Date : 1999-03-01 DOI: 10.1016/S1369-8869(99)00006-3

Scott M. Murman , Yehia M. Rizk , Russell M. Cummings , Lewis B. Schiff

引用次数: 15

Multidisciplinary design optimization of an electric-powered unmanned air vehicle 电动无人飞行器多学科设计优化

Aircraft Design Pub Date : 1999-03-01 DOI: 10.1016/S1369-8869(99)00002-6

Stephen M. Batill , Marc A. Stelmack , Xiong Qing Yu

引用次数: 20

Derivation of perturbed equations of motion of aircraft 飞行器摄动方程的推导

Aircraft Design Pub Date : 1998-12-01 DOI: 10.1016/S1369-8869(98)00017-2

S. Pradeep

引用次数: 3

Advanced configurations for very large transport airplanes 大型运输机的先进配置

Aircraft Design Pub Date : 1998-12-01 DOI: 10.1016/S1369-8869(98)00018-4

John H. McMasters , Ilan M. Kroo

{"title":"Advanced configurations for very large transport airplanes","authors":"John H. McMasters , Ilan M. Kroo","doi":"10.1016/S1369-8869(98)00018-4","DOIUrl":"10.1016/S1369-8869(98)00018-4","url":null,"abstract":"<div>Recent aerospace industry interest in developing subsonic commercial transport airplanes with at least 50% greater passenger capacity than the largest existing aircraft in this category (e.g. the Boeing 747-400 with approximately 400–450 seats) has generated a number of proposals based primarily on the configuration paradigm established 50 years ago with the Boeing B-47 bomber. While this classic configuration has come to dominate subsonic commercial airplane development since the advent of the Boeing 707/Douglas DC-8 in the mid-1950s, its extrapolation to the size required to carry more than 600–700 passengers raises a number of questions, including:<ul><li>1. How large can an airplane of 707/747 configuration be built and still remain economically and operationally viable?</li><li>2. What configuration alternatives might allow circumvention of practical size limitations inherent in the basic 707/747 configuration?</li><li>3. What new and/or dormant technology elements might be brought together in synergistic ways to resolve or ameliorate very large subsonic airplane problems?</li></ul>\u0000To explore these and a number of related issues, a team of Boeing, university and NASA engineers was formed under the auspices of the NASA Advanced Concepts Program during 1994. The results of a Research Analysis contract (NAS1-20269) focused on a large, unconventional (C-wing) transport configuration for which Boeing and the authors were granted a design patent in 1995 is the subject of this paper which is based on information contained in McMasters et al. (NASA CR 198351, October 1996).</div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"1 4","pages":"Pages 217-242"},"PeriodicalIF":0.0,"publicationDate":"1998-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(98)00018-4","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79356716","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: 63