The Parameters Optimization of Fusion Winglet Based on Orthogonal Experiment Yue LUO 1, *, Qi WANG 1, Qi DU 1 and Hou-An DING 1
|
|
- Elinor Watson
- 6 years ago
- Views:
Transcription
1 2016 International Conference on Control and Automation (ICCA 2016) ISBN: The Parameters Optimization of Fusion Winglet Based on Orthogonal Experiment Yue LUO 1, *, Qi WANG 1, Qi DU 1 and Hou-An DING 1 1 School of Aircraft Engineering, Nanchang Hangkong University, Nanchang , China *Corresponding author Key words: Fusion winglet, Orthogonal experiment, Aerodynamic calculations, Parameter optimization. Abstract: The installation of winglet is an important method to reduce the induced drag, but if the winglet design is not good enough will increase weight and drag, and result in reducing the lift-drag ratio of the plane. With the small jets as the research object, referred the wing of "longhorns" to build basic airplane wing, with installation of fusion winglet. According to the 5 parameters of winglet established test models by the use of orthogonal test method, the test models were aerodynamic simulated and analyzed by Fluent, and studied the impact of 5 parameters on the lift-drag ratio. The results showed that: the setting angle has the greatest impact on the aerodynamic performance of winglet, and the model of winglet has better lift-drag characteristic which was optimized by orthogonal test, thus to provide theoretical basis for parametric design of winglet. Introduction Friction drag, pressure drag, interference drag and induced drag are the four main drag sources of aircraft. With the energy shortage problem has become increasingly prominent, it is particularly important to reduce the drag and improve the lift drag ratio as to aircraft conceptual design. Wing as one of the most important parts of the aircraft, which bears most of the aircraft lift and a part of drag[1], with installation of winglet at the end of wing, which can effectively reduce the induced drag of the aircraft, thereby improving the aerodynamic performance of the aircraft[3]. However, aerodynamic performance of winglet is influenced by many parameters, such as height, camber angle, sweep angle,setting angle, etc[3]. In this paper, with the small jet as the research object, referred the wing of "longhorns" to build basic wing, then established test models of fusion winglet by the use of orthogonal experiment method, which were aerodynamic calculated by Fluent, and optimized the parameters of winglet, it will help to improve the lift-drag ratio of the aircraft. Modeling of Fusion Winglet The model of the fusion winglet consists of basic wing and winglet, the main design parameters of the basic wing is shown in Table 1.
2 Table 1. The main design parameters of the basic wing. Name of basic wing parameters Airfoil Parameter Value NASA0614 Semispan l 8.4m Aspect ratio 7 Mean chord b 1.2m Root chord b 0 1.8m Tip chord b 1 0.6m Leading sweep 15 The establishment of 3D model of winglet is shown in Figure 1. The 5 basic parameters of winglet consist of height h, camber angle φ, sweep angle Λ, taper ratio λ(λ=b2/b3)and setting angle ψ, is shown in Figure 2. The airfoil of winglet is the same as the basic wing. The transition of fusion winglet between the basic wing and winglet is smooth, so in this paper, the tip chord of basic wing b1 is equal to the root chord of winglet b2, so that b1=b2, and b3 is the tip chord of winglet. Figure 1. 3D model of fusion winglet. camber angle φ sweep angle Λ height h root chord of winglet b 2 setting angle ψ tip chord of winglet b 3 Figure 2. Basic parameters of winglet. Establishment and Calculation of Orthogonal Test Models Orthogonal test design method is a king of optimization design technology [4], which has the advantage of being able to get a satisfactory test results with small number of test times, very short test time and very low test cost [5].
3 The symbol of the orthogonal table is Ln(q m ), L represents an orthogonal table, n represents the number of test times, m represents the number of factors, q represents the number of factor levels. So in this paper, m represents the parameters of winglet, respectively A (height), B (camber angle), C (sweep angle), D (taper ratio), E (setting angle), therefore, in this experiment design m=5. According to the parameter selection principle of winglet[3], in this experiment design, each factor takes five levels, among them the height of winglet were taken as semispan l 5%, 10%, 15%, 20%, 25%, built the comparison table of orthogonal test factors and levels is shown in Table 2. Level Table 2. The comparison table of orthogonal test factors and levels. Factor A(height) B(camber angle) C(sweep angle) E(setting angle) D(taper ratio) [mm] [ ] [ ] [ ] (5%l) (10%l) (15%l) (20%l) (25%l) According to standard orthogonal test table design the winglet test model, built the comparison table of orthogonal test L25(5 5 ), the number of tests are 25 times, but the whole combination experiment needs to be done 3125 times. Thus, the orthogonal experimental design method can greatly reduce the number of tests. Used Gambit to make the mesh generation, the model uses the unstructured tetrahedral meshes. In order to ensure calculation precision, the meshes of the surface of the wing, especially in the wing leading and trailing edges as well as winglet were make necessary encryption processing, and the external flow field of wing is a cuboid. The mesh model of winglet is shown in Figure 3, the number of total meshes are 2.3 million. The orthogonal test models were made aerodynamic calculation by Fluent, in this paper used N-S equation, the model of turbulence is k-epsilon model, the conditions of the calculation were: height H=10000m, angle of attack α=2, flight mach number Ma=0.6, mean aerodynamic chord b=1.2m, the external flow field was set as idea gas, the coupling form between velocity and pressure is SIMPLE. The orthogonal test model comparison table and calculation results is shown in Table 3. Figure 3. The mesh model of winglet.
4 Factor Test Number Table 3. The orthogonal test model comparison table and calculation results. A (height) [mm] B (camber angle ) [ ] C (sweep angle) [ ] D (taper ratio) E (setting angle ) [ ] Lift-Drag Ratio k Analysis of Calculation Results According to the results of orthogonal experiment numerical calculation, made analysis of range values of each factor.[6,7] Figured out total response value K of each factor level, and figured out range value R of each factor based on the total response value K, then found out the order of each factor importance according to the numerical value of range value R. The results of all the individual level of each factor are accumulated, the cumulative value is the total response value K. The total response value K of level is greater, it means its performance is better. Therefore, we can figure out the optimal level of each factor according to K. For example, the factor of height is A, the level 1 of A is h=420mm, the total response value of lift-drag ratio of factor level 1 is KA1, the expression of KA1 is show in Eq. 1, the same can be used for other factors and levels. The range value R is an index to measure the importance of factors of orthogonal test[6,8], it is the difference between maximum and minimum total response values of a factor. For example, the expression RA of factor A is shown in Eq. 2, the range value R is greater means this factor is more important in the orthogonal test. (1) (2)
5 Based on calculation and analysis, the analysis table of results is shown in Table 4. Index Lift-Dra g Ratio Table 4. The analysis table of results. Factor Total Response Value of Each Level X Range The Optimal Level 1 Level 2 Level 3 Level 4 Level 5 Value R Level A B C D E Compared with the range value R of each factor based on Table 4. We can the order of R from larger to little as E>A>B>D>C, thus we could find out the descending impact of factors on lift-drag ratio was: setting angle, height, camber angle, taper ratio, sweep angle. According to the optimal level of the each factor, built the optimal parameter combination as A1B2C5D5E4. The lift-drag ratio of the optimal configuration was 9.43 which was calculated by Fluent. Because the height of the optimal configuration is 420mm which is the minimum of 5 levels, in order to ensure the accuracy of the calculation, calculated three additional models which are: basic wing, h=180mm and h=260mm(the other four parameters remain the same), the result is shown in Table 5. Table 5. The results of additional models. Model Lift Coefficient Drag Coefficient Lift-Drag Ratio Basic h=180mm h=260mm h=420mm (the optimal configuration) As seen in table 5, after the installation of winglet, the lift-drag ratio of aircraft can be increased significantly. And the height of winglet is not the smaller the better, it reaches the maximum value at about h=420mm. The results showed that: the model of winglet has better lift-drag characteristic which was optimized by orthogonal test. Conclusions (1) After the installation of winglet, the lift-drag ratio of aircraft can be increased significantly; (2) The descending impact of parameters of fusion winglet on lift-drag ratio was: setting angle, height, camber angle, taper ratio, sweep angle; (3) The model of winglet has better lift-drag characteristic which was optimized by orthogonal test. References [1] Xiao-lei Liu, Wei-ping Shi, Song Li, Study on Simulating the Drag Reduction Characteristics of Winglet, J. Engineering & Test. 2010, 50(1): 3-5. In Chinese. [2] Biao Jiang, Jie Li, Aerodynamic Analysis of Civil Aircraft Equipped with Winglet on Numerical Simulation, J. Aeronautical Computing Technique. 2011, 41(1): In Chinese. [3] Yong-quan Jiang, Aircraft Winglet Design, Aviation Industry Press, Beijing, 2009, chapter 2. [4] Hao-yang Wu, Bing-guo Chang, et al, A Special Case of Genetic Algorithm-Orthogonal Experimental Design Method, J. Journal of Software. 2001, 12(1): In Chinese. [5] Rui-jiang Liu, Ye-wang Zhang, Chong-wei Wen, Jian Tang, Study on the Design and Analysis Methods of Orthogonal Experiment, J. Experimental Technology and Managment. 2010, 9(27): In Chinese.
6 [6] Yong-ping Liao, Qin-yu Yan, Application of Orthogonal Test Method in Mechanical Industry, China Agricultural Machinery Press, Beijing, [7] Zhong-an Xu, Tian-bao Wang, et al, Brief Introduction to the Orthogonal Test Design, J. SCI/TECH Information Development & Economy. 2002, 5(12): In Chinese. [8] Jing-li Cheng, Min Zheng, Jian-qing Lou, Comparison of Several Common Optimal Experimental Design Methods, J. Research and Exploration in Laboratory. 2012, 7(31): In Chinese.
The Numerical Simulation of Civil Transportation High-lift Configuration
Available online at www.sciencedirect.com ScienceDirect Procedia Engineering 00 (2014) 000 000 www.elsevier.com/locate/procedia APISAT2014, 2014 Asia-Pacific International Symposium on Aerospace Technology,
More informationCFD ANALYSIS OF AN RC AIRCRAFT WING
CFD ANALYSIS OF AN RC AIRCRAFT WING Volume-, Issue-9, Sept.-1 1 SHREYAS KRISHNAMURTHY, SURAJ JAYASHANKAR, 3 SHARATH V RAO, ROCHEN KRISHNA T S, SHANKARGOUD NYAMANNAVAR 1,,3,, Department of Mechanical Engineering,
More informationShock Wave Reduction via Wing-Strut Geometry Design
Shock Wave Reduction via Wing-Strut Geometry Design Runze LI, Wei NIU, Haixin CHEN School of Aerospace Engineering Beijing 84, China PADRI, Barcelona (Spain) 27..29 SHORT VERSION Shock Wave Reduction via
More informationCFD Analysis of conceptual Aircraft body
CFD Analysis of conceptual Aircraft body Manikantissar 1, Dr.Ankur geete 2 1 M. Tech scholar in Mechanical Engineering, SD Bansal college of technology, Indore, M.P, India 2 Associate professor in Mechanical
More informationAERODYNAMIC DESIGN OF FLYING WING WITH EMPHASIS ON HIGH WING LOADING
AERODYNAMIC DESIGN OF FLYING WING WITH EMPHASIS ON HIGH WING LOADING M. Figat Warsaw University of Technology Keywords: Aerodynamic design, CFD Abstract This paper presents an aerodynamic design process
More informationAerodynamic Analyses of Aircraft-Blended Winglet Performance
IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE) e-issn: 2278-1684,p-ISSN: 2320-334X, Volume 13, Issue 3 Ver. IV (May- Jun. 2016), PP 65-72 www.iosrjournals.org Aerodynamic Analyses of Aircraft-Blended
More informationAn efficient method for predicting zero-lift or boundary-layer drag including aeroelastic effects for the design environment
The Aeronautical Journal November 2015 Volume 119 No 1221 1451 An efficient method for predicting zero-lift or boundary-layer drag including aeroelastic effects for the design environment J. A. Camberos
More information2008 International Conference on Apperceiving Computing and Intelligence Analysis (ICACIA 2008) Chengdu, China December 2008
2008 International Conference on Apperceiving Computing and Intelligence Analysis (ICACIA 2008) Chengdu, China 13-15 December 2008 IEEE Catalog Number: ISBN: CFP0881F-PRT 978-1-4244-3427-5 TABLE OF CONTENTS
More informationresult, it is very important to design a simulation system for dynamic laser scanning
3rd International Conference on Multimedia Technology(ICMT 2013) Accurate and Fast Simulation of Laser Scanning Imaging Luyao Zhou 1 and Huimin Ma Abstract. In order to design a more accurate simulation
More informationTHE EFFECTS OF THE PLANFORM SHAPE ON DRAG POLAR CURVES OF WINGS: FLUID-STRUCTURE INTERACTION ANALYSES RESULTS
March 18-20, 2013 THE EFFECTS OF THE PLANFORM SHAPE ON DRAG POLAR CURVES OF WINGS: FLUID-STRUCTURE INTERACTION ANALYSES RESULTS Authors: M.R. Chiarelli, M. Ciabattari, M. Cagnoni, G. Lombardi Speaker:
More informationNumerical Simulation Study on Aerodynamic Characteristics of the High Speed Train under Crosswind
2017 2nd International Conference on Industrial Aerodynamics (ICIA 2017) ISBN: 978-1-60595-481-3 Numerical Simulation Study on Aerodynamic Characteristics of the High Speed Train under Crosswind Fan Zhao,
More informationAerodynamic Analysis of Forward Swept Wing Using Prandtl-D Wing Concept
Aerodynamic Analysis of Forward Swept Wing Using Prandtl-D Wing Concept Srinath R 1, Sahana D S 2 1 Assistant Professor, Mangalore Institute of Technology and Engineering, Moodabidri-574225, India 2 Assistant
More informationComputational Investigation of Inviscid Flow over a Wing With Multiple Winglets
Computational Investigation of Inviscid Flow over a Wing With Multiple Winglets P. Sethunathan Assistant Professor,Department of Aeronautical Engineering, Paavaai Group of Institutions, Namakkal, India.
More informationQingdao, , China. China. Keywords: Deep sea Ultrahigh pressure, Water sound acquisition, LabVIEW, NI PXle hardware.
2016 International Conference on Control and Automation (ICCA 2016) ISBN: 978-1-60595-329-8 Research and Design on Water Sound Acquisition System of Deep Sea Ultrahigh Pressure Environment Gang TONG 1,
More informationOptimization of Laminar Wings for Pro-Green Aircrafts
Optimization of Laminar Wings for Pro-Green Aircrafts André Rafael Ferreira Matos Abstract This work falls within the scope of aerodynamic design of pro-green aircraft, where the use of wings with higher
More informationKeywords: CFD, aerofoil, URANS modeling, flapping, reciprocating movement
L.I. Garipova *, A.N. Kusyumov *, G. Barakos ** * Kazan National Research Technical University n.a. A.N.Tupolev, ** School of Engineering - The University of Liverpool Keywords: CFD, aerofoil, URANS modeling,
More informationDevelopment of a Rapid Design System for Aerial Work Truck Subframe with UG Secondary Development Framework
Available online at www.sciencedirect.com Procedia Engineering 15 (2011) 2961 2965 Advanced in Control Engineering and Information Science Development of a Rapid Design System for Aerial Work Truck Subframe
More informationIntroduction to ANSYS CFX
Workshop 03 Fluid flow around the NACA0012 Airfoil 16.0 Release Introduction to ANSYS CFX 2015 ANSYS, Inc. March 13, 2015 1 Release 16.0 Workshop Description: The flow simulated is an external aerodynamics
More informationAERODYNAMIC DESIGN FOR WING-BODY BLENDED AND INLET
25 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES AERODYNAMIC DESIGN FOR WING-BODY BLENDED AND INLET Qingzhen YANG*,Yong ZHENG* & Thomas Streit** *Northwestern Polytechincal University, 772,Xi
More informationIntegrated Design Optimization of Aerodynamic and Stealthy Performance for Flying Wing Aircraft
, March 15-17, 2017, Hong Kong Integrated Design Optimization of Aerodynamic and Stealthy Performance for Flying Wing Aircraft Yalin Pan, Jun Huang, Feng Li, and Chuxiong Yan Abstract Flying wing configuration
More informationResearch Of Data Model In Engineering Flight Simulation Platform Based On Meta-Data Liu Jinxin 1,a, Xu Hong 1,b, Shen Weiqun 2,c
Applied Mechanics and Materials Online: 2013-06-13 ISSN: 1662-7482, Vols. 325-326, pp 1750-1753 doi:10.4028/www.scientific.net/amm.325-326.1750 2013 Trans Tech Publications, Switzerland Research Of Data
More informationLift Superposition and Aerodynamic Twist Optimization for Achieving Desired Lift Distributions
48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 4-7 January 2010, Orlando, Florida AIAA 2010-1227 Lift Superposition and Aerodynamic Twist Optimization for
More informationMATH 573 Advanced Scientific Computing
MATH 573 Advanced Scientific Computing Analysis of an Airfoil using Cubic Splines Ashley Wood Brian Song Ravindra Asitha What is Airfoil? - The cross-section of the wing, blade, or sail. 1. Thrust 2. Weight
More informationNUMERICAL 3D TRANSONIC FLOW SIMULATION OVER A WING
Review of the Air Force Academy No.3 (35)/2017 NUMERICAL 3D TRANSONIC FLOW SIMULATION OVER A WING Cvetelina VELKOVA Department of Technical Mechanics, Naval Academy Nikola Vaptsarov,Varna, Bulgaria (cvetelina.velkova1985@gmail.com)
More informationCOMPARISON OF SHOCK WAVE INTERACTION FOR THE THREE-DIMENSIONAL SUPERSONIC BIPLANE WITH DIFFERENT PLANAR SHAPES
26 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES COMPARISON OF SHOCK WAVE INTERACTION FOR THE THREE-DIMENSIONAL SUPERSONIC BIPLANE WITH DIFFERENT PLANAR SHAPES M. Yonezawa*, H. Yamashita* *Institute
More informationDesign and Research on Mechanism of Bionic Flapping-wing Air Vehicle
Vol.8, No.4 (2015), pp. 299-306 http://dx.doi.org/10.14257/ijhit.2015.8.4.31 Design and Research on Mechanism of Bionic Flapping-wing Air Vehicle Yang Yonggang, Xie Youzeng and Huo Lipeng School of Aeronautics
More informationAerodynamic Design of a Tailless Aeroplan J. Friedl
Acta Polytechnica Vol. 4 No. 4 5/2 Aerodynamic Design of a Tailless Aeroplan J. Friedl The paper presents an aerodynamic analysis of a one-seat ultralight (UL) tailless aeroplane named L2k, with a very
More informationAvailable online at ScienceDirect. Procedia Engineering 99 (2015 )
Available online at www.sciencedirect.com ScienceDirect Procedia Engineering 99 (2015 ) 575 580 APISAT2014, 2014 Asia-Pacific International Symposium on Aerospace Technology, APISAT2014 A 3D Anisotropic
More informationParameter Modeling for Single Screw Pump Based On CATIA Secondary Development Platform Heng Fu 1,a, Yanhua Gu 2,b *, Xiaoyu Wang 3,b, Xiu Fang Zhang 4
5th International Conference on Advanced Engineering Materials and Technology (AEMT 205) Parameter Modeling for Single Screw Pump Based On CATIA Secondary Development Platform Heng Fu,a, Yanhua Gu 2,b
More informationAnalysis of an airfoil
UNDERGRADUATE RESEARCH FALL 2010 Analysis of an airfoil using Computational Fluid Dynamics Tanveer Chandok 12/17/2010 Independent research thesis at the Georgia Institute of Technology under the supervision
More informationDynamic Balance Design of the Rotating Arc Sensor Based on PSO Algorithm
016 International Conference on Advanced Manufacture Technology and Industrial Application (AMTIA 016) ISBN: 978-1-60595-387-8 Dynamic Balance Design of the Rotating Arc Sensor Based on PSO Algorithm Ji-zhong
More informationCloud Cavitating Flow around an Axisymmetric Projectile in the shallow water
Cloud Cavitating Flow around an Axisymmetric Projectile in the shallow water 1,2 Chang Xu; 1,2 Yiwei Wang*; 1,2 Jian Huang; 1,2 Chenguang Huang 1 Key Laboratory for Mechanics in Fluid Solid Coupling Systems,
More information2002 International Conference on Machine Learning and Cybernetics. Proceedings Volume 3 of 4
2002 International Conference on Machine Learning and Cybernetics Proceedings Volume 3 of 4 TECHNISCHE INFORMATIO.NSBIBLIOTHEK UNIVERS1TATSBIBLIOTHEK HANNOVER November 4-5, 2002 Prime Hotel Beijing, CHINA
More information2002 International Conference on Machine Learning and Cybernetics. Proceedings Volume 1 of 4
2002 International Conference on Machine Learning and Cybernetics Proceedings Volume 1 of 4 TECHNISCHE INFORMATIONSBIBLiOTHEK UNIVERSITATSBiBLIOTHEK HANNOVCR November 4-5, 2002 Prime Hotel Beijing, CHINA
More informationAPPLICATION OF VARIABLE-FIDELITY MODELS TO AERODYNAMIC OPTIMIZATION
Applied Mathematics and Mechanics (English Edition), 2006, 27(8):1089 1095 c Editorial Committee of Appl. Math. Mech., ISSN 0253-4827 APPLICATION OF VARIABLE-FIDELITY MODELS TO AERODYNAMIC OPTIMIZATION
More informationApplication of STAR-CCM+ to Helicopter Rotors in Hover
Application of STAR-CCM+ to Helicopter Rotors in Hover Lakshmi N. Sankar and Chong Zhou School of Aerospace Engineering, Georgia Institute of Technology, Atlanta, GA Ritu Marpu Eschol CD-Adapco, Inc.,
More informationCalculation and Analysis on Stealth and Aerodynamics Characteristics of a Medium Altitude Long Endurance UAV
Available online at www.sciencedirect.com ScienceDirect Procedia Engineering (214) www.elsevier.com/locate/procedia APISAT214, 214 Asia-Pacific International Symposium on Aerospace Technology, APISAT214
More informationValidation of a numerical simulation tool for aircraft formation flight.
Validation of a numerical simulation tool for aircraft formation flight. T. Melin Fluid and Mechatronic Systems, Department of Management and Engineering, the Institute of Technology, Linköping University,
More informationComputer Aided Drafting, Design and Manufacturing Volume 25, Number 3, September 2015, Page 1
Computer Aided Drafting, Design and Manufacturing Volume 25, Number 3, September 2015, Page 1 CADDM A Turbine Blade Parametric Modeling Method Considering 1-D Heat Transfer Analysis LI Ji-xing 1, XI Ping
More informationModeling three-dimensional dynamic stall
Appl. Math. Mech. -Engl. Ed., 32(4), 393 400 (2011) DOI 10.1007/s10483-011-1424-6 c Shanghai University and Springer-Verlag Berlin Heidelberg 2011 Applied Mathematics and Mechanics (English Edition) Modeling
More information39th AIAA Aerospace Sciences Meeting and Exhibit January 8 11, 2001/Reno, NV
AIAA 1 717 Static Aero-elastic Computation with a Coupled CFD and CSD Method J. Cai, F. Liu Department of Mechanical and Aerospace Engineering University of California, Irvine, CA 92697-3975 H.M. Tsai,
More informationChallenges in Boundary- Layer Stability Analysis Based On Unstructured Grid Solutions
Challenges in Boundary- Layer Stability Analysis Based On Unstructured Grid Solutions Wei Liao National Institute of Aerospace, Hampton, Virginia Collaborators: Mujeeb R. Malik, Elizabeth M. Lee- Rausch,
More informationCOMPUTATIONAL AND EXPERIMENTAL AERODYNAMIC ANALYSIS FOR THE WING OF A MINI UNMANNED AERIAL VEHICLE (UAV)
COMPUTATIONAL AND EXPERIMENTAL AERODYNAMIC ANALYSIS FOR THE WING OF A MINI UNMANNED AERIAL VEHICLE (UAV) José Manuel Herrera Farfán Nohemí Silva Nuñez Hernán Darío Cerón Muñoz Nelson Javier Pedraza Betancourth
More informationAero-engine PID parameters Optimization based on Adaptive Genetic Algorithm. Yinling Wang, Huacong Li
International Conference on Applied Science and Engineering Innovation (ASEI 215) Aero-engine PID parameters Optimization based on Adaptive Genetic Algorithm Yinling Wang, Huacong Li School of Power and
More informationMultidisciplinary design optimization (MDO) of a typical low aspect ratio wing using Isight
Multidisciplinary design optimization (MDO) of a typical low aspect ratio wing using Isight Mahadesh Kumar A 1 and Ravishankar Mariayyah 2 1 Aeronautical Development Agency and 2 Dassault Systemes India
More informationThe Spalart Allmaras turbulence model
The Spalart Allmaras turbulence model The main equation The Spallart Allmaras turbulence model is a one equation model designed especially for aerospace applications; it solves a modelled transport equation
More informationThe Design of Electronic Color Screen Based on Proteus Visual Designer Ting-Yu HOU 1,a, Hao LIU 2,b,*
2016 Joint International Conference on Service Science, Management and Engineering (SSME 2016) and International Conference on Information Science and Technology (IST 2016) ISBN: 978-1-60595-379-3 The
More informationResearch on Heterogeneous Communication Network for Power Distribution Automation
3rd International Conference on Material, Mechanical and Manufacturing Engineering (IC3ME 2015) Research on Heterogeneous Communication Network for Power Distribution Automation Qiang YU 1,a*, Hui HUANG
More informationResearch of the L-Type Gantry Crane s System Based on BP Network and Genetic Algorithm
Sensors & Transducers 2013 by IFSA http//www.sensorsportal.com Research of the L-Type Gantry Crane s System Based on BP Network and Genetic Algorithm LI Yue, FAN Qin College of Machinery and Automation
More information3. Ball Screw Modal Analysis
Abstract Modal Analysis of Ball Screws in AOI Equipment Jian Zhang 1, Dan Xu 1, Ruiting Wang 1 and Fengjiao Wang 1, a 1 LUSTER LightTech Group, Suzhou, 215123, China. a fengjiaowang@lusterinc.com Ball
More informationStudy on Improving the Quality of Reconstructed NURBS Surfaces
Study on Improving the Quality of Reconstructed NURBS Surfaces Shufeng jiang, Shigang Wang, Yong Yan School of Mechatronic Engineering, Qiqihar University, Qiqihar 161006, China Abstract In aspect of surface
More informationApplication of Wray-Agarwal Turbulence Model for Accurate Numerical Simulation of Flow Past a Three-Dimensional Wing-body
Washington University in St. Louis Washington University Open Scholarship Mechanical Engineering and Materials Science Independent Study Mechanical Engineering & Materials Science 4-28-2016 Application
More informationFluid-Structure Interaction Over an Aircraft Wing
International Journal of Engineering Research and Development e-issn: 2278-067X, p-issn: 2278-800X, www.ijerd.com Volume 13, Issue 4 (April 2017), PP.27-31 Fluid-Structure Interaction Over an Aircraft
More informationNumerical Study of Applications of Active Flow Control for Drag Reduction
Numerical Study of Applications of Active Flow Control for Drag Reduction RAMESH K. AGARWAL Department of Mechanical Engineering and Materials Science Washington University in St. Louis 1 Brookings Drive,
More informationEstimating Vertical Drag on Helicopter Fuselage during Hovering
Estimating Vertical Drag on Helicopter Fuselage during Hovering A. A. Wahab * and M.Hafiz Ismail ** Aeronautical & Automotive Dept., Faculty of Mechanical Engineering, Universiti Teknologi Malaysia, 81310
More informationComputer Aided Drafting, Design and Manufacturing Volume 24, Number 4, December 2014, Page 64
Computer Aided Drafting, Design and Manufacturing Volume 24, Number 4, December 2014, Page 64 CADDM Three Dimensional Modeling of Shaft with Process Structures on CATIA WAN Sheng-lai, WANG Xiao-yu, JIANG
More informationResearch Article A Computational Investigation of Unsteady Aerodynamics of Insect-Inspired Fixed Wing Micro Aerial Vehicle s 2D Airfoil
Advances in Aerospace Engineering, Article ID 5449, 7 pages http://dx.doi.org/1.1155/214/5449 Research Article A Computational Investigation of Unsteady Aerodynamics of Insect-Inspired Fixed Wing Micro
More informationDYNAMICS OF A VORTEX RING AROUND A MAIN ROTOR HELICOPTER
DYNAMICS OF A VORTEX RING AROUND A MAIN ROTOR HELICOPTER Katarzyna Surmacz Instytut Lotnictwa Keywords: VORTEX RING STATE, HELICOPTER DESCENT, NUMERICAL ANALYSIS, FLOW VISUALIZATION Abstract The main goal
More informationAircraft Stability and Performance 2nd Year, Aerospace Engineering. Dr. M. Turner
Aircraft Stability and Performance 2nd Year, Aerospace Engineering Dr. M. Turner Basic Info Timetable 15.00-16.00 Monday ENG LT1 16.00-17.00 Monday ENG LT1 Typical structure of lectures Part 1 Theory Part
More informationTrajectory Planning for Reentry Maneuverable Ballistic Missiles
International Conference on Manufacturing Science and Engineering (ICMSE 215) rajectory Planning for Reentry Maneuverable Ballistic Missiles XIE Yu1, a *, PAN Liang1,b and YUAN ianbao2,c 1 College of mechatronic
More informationPost Stall Behavior of a Lifting Line Algorithm
Post Stall Behavior of a Lifting Line Algorithm Douglas Hunsaker Brigham Young University Abstract A modified lifting line algorithm is considered as a low-cost approach for calculating lift characteristics
More informationOptimum Design of a Flexible Wing Structure to Enhance Roll Maneuver in Supersonic Flow
Optimum Design of a Flexible Wing Structure to Enhance Roll Maneuver in Supersonic Flow Duane E. Veley, Narendra S. Khot, Jeffrey V. Zweber Structures Division, Air Vehicles Directorate, Air Force Research
More informationExperimental study of UTM-LST generic half model transport aircraft
IOP Conference Series: Materials Science and Engineering PAPER OPEN ACCESS Experimental study of UTM-LST generic half model transport aircraft To cite this article: M I Ujang et al 2016 IOP Conf. Ser.:
More informationInternational Conference on Information Sciences, Machinery, Materials and Energy (ICISMME 2015)
International Conference on Information Sciences, Machinery, Materials and Energy (ICISMME 2015) ARINC - 429 airborne communications transceiver system based on FPGA implementation Liu Hao 1,Gu Cao 2,MA
More informationModeling External Compressible Flow
Tutorial 3. Modeling External Compressible Flow Introduction The purpose of this tutorial is to compute the turbulent flow past a transonic airfoil at a nonzero angle of attack. You will use the Spalart-Allmaras
More informationZhi-Quan Luo Electrical and Computer Engineering
Sun, Ruoyu, and Zhi-Quan Luo. 2015. Interference alignment using finite and dependent channel extensions: The single beam case. IEEE Transactions on Information Theory 61 (1) (JAN 01): 239-55. Baligh,
More informationGRID PATTERN EFFECTS ON AERODYNAMIC CHARACTERISTICS OF GRID FINS
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES GRID PATTERN EFFECTS ON AERODYNAMIC CHARACTERISTICS OF GRID FINS Fumiya Hiroshima, Kaoru Tatsumi* *Mitsubishi Electric Corporation, Kamakura Works,
More informationLAMDES User s Manual VLMpc
LAMDES User s Manual This is a modified version of John Lamar s design program (Ref. 1). It is based on the vortex lattice program VLMpc, but converted to do design and optimization. Basic capabilities
More informationIncompressible Potential Flow. Panel Methods (3)
Incompressible Potential Flow Panel Methods (3) Outline Some Potential Theory Derivation of the Integral Equation for the Potential Classic Panel Method Program PANEL Subsonic Airfoil Aerodynamics Issues
More informationUsage of CFX for Aeronautical Simulations
Usage of CFX for Aeronautical Simulations Florian Menter Development Manager Scientific Coordination ANSYS Germany GmbH Overview Elements of CFD Technology for aeronautical simulations: Grid generation
More informationSmall Height Duct Design for 17 Multicopter Fan Considering Its Interference on Quad-copter
Small Height Duct Design for 17 Multicopter Fan Considering Its Interference on Quad-copter Stremousov K.*, Arkhipov M.* **, Serokhvostov S.* ** * Moscow Institute of Physics and Technology, Department
More informationLES Analysis on Shock-Vortex Ring Interaction
LES Analysis on Shock-Vortex Ring Interaction Yong Yang Jie Tang Chaoqun Liu Technical Report 2015-08 http://www.uta.edu/math/preprint/ LES Analysis on Shock-Vortex Ring Interaction Yong Yang 1, Jie Tang
More informationThe Research of Delay Characteristics in CAN Bus Networked Control System
Journal of Computational Information Systems 9: 18 (2013) 7517 7523 Available at http://www.jofcis.com The Research of Delay Characteristics in CAN Bus Networked Control System Yi WANG 1, Liren HE 2, Ming
More informationIntroduction to CFX. Workshop 2. Transonic Flow Over a NACA 0012 Airfoil. WS2-1. ANSYS, Inc. Proprietary 2009 ANSYS, Inc. All rights reserved.
Workshop 2 Transonic Flow Over a NACA 0012 Airfoil. Introduction to CFX WS2-1 Goals The purpose of this tutorial is to introduce the user to modelling flow in high speed external aerodynamic applications.
More informationAerodynamic Design Optimization of a Kind of Reentry Capsule Based on CFD and Multi-objective Genetic Algorithm
Available online at www.sciencedirect.com ScienceDirect Procedia Engineering00 (2014) 000 000 www.elsevier.com/locate/procedia APISAT2014, 2014 Asia-Pacific International Symposium on Aerospace Technology,
More informationModeling and Analysis of the Support System of Space-based Anti-missile Information Based on UML
2018 International Conference on Modeling, Simulation and Optimization (MSO 2018) ISBN: 978-1-60595-542-1 Modeling and Analysis of the Support System of Space-based Anti-missile Information Based on UML
More informationA method of three-dimensional subdivision of arbitrary polyhedron by. using pyramids
5th International Conference on Measurement, Instrumentation and Automation (ICMIA 2016) A method of three-dimensional subdivision of arbitrary polyhedron by using pyramids LIU Ji-bo1,a*, Wang Zhi-hong1,b,
More informationSPC 307 Aerodynamics. Lecture 1. February 10, 2018
SPC 307 Aerodynamics Lecture 1 February 10, 2018 Sep. 18, 2016 1 Course Materials drahmednagib.com 2 COURSE OUTLINE Introduction to Aerodynamics Review on the Fundamentals of Fluid Mechanics Euler and
More informationResearch on Gear CAD Design Based on UG Platform
2017 5th International Civil Engineering, Architecture and Machinery Conference(ICEAMC 2017) Research on Gear CAD Design Based on UG Platform Ting Liu Jining Polytechnic, Jining, Shandong, China, 272037
More informationGAs for aerodynamic shape design II: multiobjective optimization and multi-criteria design
GAs for aerodynamic shape design II: multiobjective optimization and multi-criteria design D. Quagliarella, A. Vicini C.I.R.A., Centro Italiano Ricerche Aerospaziali Via Maiorise 8143 Capua (Italy) Abstract
More informationRESEARCH ON INTELLIGENT DESIGN AND ACCURATE MODELLING OF SPIRAL BEVEL GEARS BASED ON FUNCTION-TO-FORM MAPPING
INTERNATIONAL DESIGN CONFERENCE - DESIGN 2018 https://doi.org/10.21278/idc.2018.0216 RESEARCH ON INTELLIGENT DESIGN AND ACCURATE MODELLING OF SPIRAL BEVEL GEARS BASED ON FUNCTION-TO-FORM MAPPING Z.-G.
More informationResearch of Traffic Flow Based on SVM Method. Deng-hong YIN, Jian WANG and Bo LI *
2017 2nd International onference on Artificial Intelligence: Techniques and Applications (AITA 2017) ISBN: 978-1-60595-491-2 Research of Traffic Flow Based on SVM Method Deng-hong YIN, Jian WANG and Bo
More informationSubsonic Airfoils. W.H. Mason Configuration Aerodynamics Class
Subsonic Airfoils W.H. Mason Configuration Aerodynamics Class Most people don t realize that mankind can be divided into two great classes: those who take airfoil selection seriously, and those who don
More informationAerodynamics of 3D Lifting Surfaces through Vortex Lattice Methods (3) Two implementations of the VLM
Aerodynamics of 3D Lifting Surfaces through Vortex Lattice Methods (3) Two implementations of the VLM Basic Concepts Outline Boundary conditions on the mean surface Vortex Theorems, Biot-Savart Law The
More informationStudy on GA-based matching method of railway vehicle wheels
Available online www.jocpr.com Journal of Chemical and Pharmaceutical Research, 2014, 6(4):536-542 Research Article ISSN : 0975-7384 CODEN(USA) : JCPRC5 Study on GA-based matching method of railway vehicle
More informationProceedings of 2005 International Conference On Machine Learning and Cybernetics. Volume 9 of 9
t»f JT A If I Otemational Viz I iversify in Girminy Proceedings of 2005 International Conference On Machine Learning and Cybernetics Volume 9 of 9 August 18-21, 2005 Ramada Hotel Guangzhou, China IEEE
More informationView-dependent fast real-time generating algorithm for large-scale terrain
Procedia Earth and Planetary Science 1 (2009) 1147 Procedia Earth and Planetary Science www.elsevier.com/locate/procedia The 6 th International Conference on Mining Science & Technology View-dependent
More informationState of the art at DLR in solving aerodynamic shape optimization problems using the discrete viscous adjoint method
DLR - German Aerospace Center State of the art at DLR in solving aerodynamic shape optimization problems using the discrete viscous adjoint method J. Brezillon, C. Ilic, M. Abu-Zurayk, F. Ma, M. Widhalm
More informationComputational Fluid Dynamics Analysis of an Idealized Modern Wingsuit
Washington University in St. Louis Washington University Open Scholarship Mechanical Engineering and Materials Science Independent Study Mechanical Engineering & Materials Science 12-21-2016 Computational
More informationComputer Aided Drafting, Design and Manufacturing Volume 26, Number 4, December 2016, Page 30
Computer Aided Drafting, Design and Manufacturing Volume 26, Number 4, December 2016, Page 30 CADDM Aircraft wing box rapid modeling based on skeleton model Zhang Chao, Xi Ping School of Mechanical Engineering
More informationSubsonic Airfoils. W.H. Mason Configuration Aerodynamics Class
Subsonic Airfoils W.H. Mason Configuration Aerodynamics Class Typical Subsonic Methods: Panel Methods For subsonic inviscid flow, the flowfield can be found by solving an integral equation for the potential
More informationTRANSONIC FLOW PAST SYMMETRICAL UNSWEPT AND SWEPT WINGS WITH ELLIPTIC NOSE
TRANSONIC FLOW PAST SYMMETRICAL UNSWEPT AND SWEPT WINGS WITH ELLIPTIC NOSE A. N. Ryabinin Saint-Petersburg State University, University Emb, St. Petersburg, Russia E-Mail: a.ryabinin@spbu.ru ABSTRACT The
More informationAERODYNAMIC SHAPES DESIGN ON THE BASE OF DIRECT NEWTON TYPE OPTIMIZATION METHOD
AERODYNAMIC SHAPES DESIGN ON THE BASE OF DIRECT NEWTON TYPE OPTIMIZATION METHOD A.V. Grachev*, A.N. Kraiko**, S.A. Takovitskii* *Central Aerohydrodynamic Institute (TsAGI), **Central Institute of Aviation
More informationResearch on friction parameter identification under the influence of vibration and collision
Research on friction parameter identification under the influence of vibration and collision Qiang Chen 1, Yingjun Wang 2, Ying Chen 3 1, 2 Department of Control and System Engineering, Nanjing University,
More informationPARAMETERIZED COMPUTER AIDED DESIGN OF STUBBLE CLEANER
PARAMETERIZED COMPUTER AIDED DESIGN OF STUBBLE CLEANER Lige Wen 1, 2, Jianqiao Li 1,*, Xiuzhi Zhang 2, Benard Chirende 1 1 The Key Laboratory for Terrain-Machine Bionics Engineering, Ministry of Education,
More informationDesign of Liquid Level Control System Based on Simulink and PLC
2017 3rd International Symposium on Mechatronics and Industrial Informatics (ISMII 2017) ISBN: 978-1-60595-501-8 Design of Liquid Level Control System Based on Simulink and PLC Xiuwei FU 1,a, Ying QI 2,b
More informationInfluence of the Optical Multi-Film Thickness on the Saturation of the Structural Color Displayed 1
Advances in Natural Science Vol. 3, No. 2,, pp.317-323 www.cscanada.net ISSN 1715-7862 [PRINT] ISSN 1715-787 [ONLINE] www.cscanada.org *The 3rd International Conference of Bionic Engineering* Influence
More informationDesign of Precise Control and Dynamic Simulation of Manipulator for Die-casting Mould
IOP Conference Series: Materials Science and Engineering PAPER OPEN ACCESS Design of Precise Control and Dynamic Simulation of Manipulator for Die-casting Mould To cite this article: Yi Mei et al 2018
More informationUsing The Heuristic Genetic Algorithm in Multi-runway Aircraft Landing Scheduling
TELKOMNIKA Indonesian Journal of Electrical Engineering Vol.12, No.3, March 2014, pp. 2203 ~ 2211 DOI: http://dx.doi.org/10.11591/telkomnika.v12i3.4488 2203 Using The Heuristic Genetic Algorithm in Multi-runway
More informationInfluence of Geometric Scaling on Linear Cascade Aerodynamic Performance
Available online at www.sciencedirect.com ScienceDirect Procedia Engineering 00 (2014) 000 000 www.elsevier.com/locate/procedia APISAT2014, 2014 Asia-Pacific International Symposium on Aerospace Technology,
More information