NAWEA 2015 SYMPOSIUM
|
|
- Deborah Baldwin
- 5 years ago
- Views:
Transcription
1 Aerodynamics and Aeroacoustics of Spanwise Wavy Trailing Edge Flatback Airfoils: Design Improvement Seung Joon Yang James D. Baeder Alfred Gessow Rotorcraft Center Department of Aerospace Engineering, University of Maryland NAWEA 2015 SYMPOSIUM Spanwise Wavy Trailing Edge Airfoil 1/ 31 NAWEA 2015
2 Outline Introduction Flatback airfoil drag and noise emission Numerical methods Wavy trailing edge design Wavy trailing edge modification Results and discussions Aerodynamic Characteristics Aeroacoustic Characteristics Conclusion Spanwise Wavy Trailing Edge Airfoil 2/ 31 NAWEA 2015
3 Introduction and Motivation Wind power generation is proportional to square of rotor blade length! * IPCC Special Report on Renewable Energy Sources and Climate Change Mitigation 2011 Higher power generation requires larger blades Demands a structurally robust blade Thicker Airfoil at inboard sections (~40% of blade span!) Spanwise Wavy Trailing Edge Airfoil 3/ 31 NAWEA 2015
4 Introduction: Flatback Airfoil Aerodynamics Sharp TE Flatback TE Advantages Flatback TE airfoil has superior lift performance; delayed stall on upper surface Structurally robust blade design compared to sharp TE airfoil * Baker, Experimental Analysis of Thick Blunt Trailing Edge wind turbine Airfoils, 2006 Spanwise Wavy Trailing Edge Airfoil 4/ 31 NAWEA 2015
5 Introduction: Flatback Airfoil Aerodynamics Sharp TE Flatback TE Flatback TE Sharp TE Increase in drag Disadvantages Flatback TE airfoil suffers from higher drag, lower max L/D Higher acoustical signature compared to sharp TE * Baker, Experimental Analysis of Thick Blunt Trailing Edge wind turbine Airfoils, 2006 Spanwise Wavy Trailing Edge Airfoil 5/ 31 NAWEA 2015
6 Introduction: Flatback Airfoil Noise Emission Flatback TE AoA 4, Re = 3,000,000 Strong vortex shedding Sharp TE Noise spectrum Vortex shedding pattern Disadvantages Flatback TE airfoil high tonal noise Generated by pressure fluctuations at TE because of strong nearly 2-D spanwise coherent vortex shedding * Dale E. Berg and M. Barone, Aerodynamic and Aeroacoustic Properties of a Flatback Airfoil, WINDPOWER 2008, Houston, 2008 Spanwise Wavy Trailing Edge Airfoil 6/ 31 NAWEA 2015
7 Introduction: Spanwise Wavy Trailing Edge Modification Baseline Proposed solution Introduce streamwise vorticity to disintegrate/breakdown spanwise coherent vortex structure Can the trailing edge geometry be modified to reduce drag and noise while maintaining aerodynamic efficiency? Other solutions Splitter plate, serrated TE add on devices * Seung Joon Yang and James D. Baeder, Aerodynamic Drag and Aeroacoustic Noise Mitigation of Flatback Airfoil with Spanwise Wavy Trailng Edge, 33 rd Wind Energy Symposium at Scitech 2015, Kisimmee, FL, 2015 Spanwise Wavy Trailing Edge Airfoil 7/ 31 NAWEA 2015
8 Numerical methods RANS LES hybrid method (OVERTURNS, GPURANS3D) - Laminar Turbulent transition modeling ; γ Re θθ transition model with S-A turbulence model - Delayed Detached Eddy Simulation (DDES) - Spatial reconstruction ; 5 th order WENO - Time marching; Diagonal Alternating Direction Implicit (DADI) - GPU accelerated computation ; Deepthought II cluster at UMD (40 gpu nodes) ; Nvidia Tesla K20m GPUs Nvidia Tesla K20m Processor core 2496 Processor core clock Memory Memory clock Band width 706 MHz 5 GB 2.6 GHz 208 GB/sec * Deepthought II Cluster at UMD, College Park Spanwise Wavy Trailing Edge Airfoil 8/ 31 NAWEA 2015
9 Mesh Generation 271 x 141 x 61 ~ 2.33 milion grid points for each airfoil geometries 50C distance away in the normal to surface direction resolution; Δy/c ~ 5.0µ (y+ ~ 0.8) Validation! 0.5C in span direction 104 grid points at the trailing edge 102 grid points upper/bottom surface near the trailing edge * Seung Joon Yang and James D. Baeder, Aerodynamic Drag and Aeroacoustic Noise Mitigation of Flatback Airfoil with Spanwise Wavy Trailng Edge, 33 rd Wind Energy Symposium at Scitech 2015, Kisimmee, FL, 2015 Spanwise Wavy Trailing Edge Airfoil 9/ 31 NAWEA 2015
10 Wavy trailing edge design: Previous Designs Baseline 1/2flatback-4cyc/C 3/4flatback-4cyc/C Wave formula y = y mmm y mmm local thickness = y 2 cos ω 2ππ l y mmm 4 cyc/c better than 2 cyc/c or 8 cyc/c * James D. Baeder and Seung Joon Yang, Wavy Trailing-Edge Flatback Aerodynamics Using a GPU-Accelerated Navier-Stokes Solver, EWEA Offshoer, Copenhagen, Denmark, 2015, March Spanwise Wavy Trailing Edge Airfoil 10/ 31 NAWEA 2015
11 Baseline Results Base-line cases A. FB (TE thickness 17.50% of C, flatback TE) B. FB (TE thickness 4.62% of C, sharp TE) FB FB Strong nearly 2-D spanwise vortex structure with flatback airfoil Weak spanwise vortex structure with sharp trailing edge airfoil * Seung Joon Yang and James D. Baeder, Aerodynamic Drag and Aeroacoustic Noise Mitigation of Flatback Airfoil with Spanwise Wavy Trailng Edge, 33 rd Wind Energy Symposium at Scitech 2015, Kisimmee, FL, 2015 Spanwise Wavy Trailing Edge Airfoil 11/ 31 NAWEA 2015
12 Previous Wavy Trailing Edge: Flowfield 3/4 flatback 4cyc/C 1/2 flatback 4cyc/C With shallow wavy pattern, still span-wise vortex structure With deeper wavy pattern, more stream-wise vortex structure However, relatively unstable flow at the wave troughs * James D. Baeder and Seung Joon Yang, Wavy Trailing-Edge Flatback Aerodynamics Using a GPU-Accelerated Navier-Stokes Solver, EWEA Offshoer, Copenhagen, Denmark, 2015 Spanwise Wavy Trailing Edge Airfoil 12/ 31 NAWEA 2015
13 Previous Wavy Trailing Edge: Aerodynamic Performance With shallow wavy pattern, higher lift and reduced drag With deeper wavy pattern, too much loss of lift * James D. Baeder and Seung Joon Yang, Wavy Trailing-Edge Flatback Aerodynamics Using a GPU-Accelerated Navier-Stokes Solver, EWEA Offshoer, Copenhagen, Denmark, 2015 Spanwise Wavy Trailing Edge Airfoil 13/ 31 NAWEA 2015
14 Previous Wavy Trailing Edge: Potential Problems Previous wavy TE Loss of blade volume at troughs weaken blade structural strength? Wavy modification make any difficulty during manufacturing stage? * Seung Joon Yang and James D. Baeder, Aerodynamic Drag and Aeroacoustic Noise Mitigation of Flatback Airfoil with Spanwise Wavy Trailng Edge, 33 rd Wind Energy Symposium at Scitech 2015, Kisimmee, FL, 2015 Spanwise Wavy Trailing Edge Airfoil 1/ 31 NAWEA 2015
15 Design Improvements: Design #1 Can we remove wavy structure on upper surface? Lower half way cut (only Bottom surface wavy TE ) Previous wavy TE Camber recovery helps aerodynamic performance Lower half way cut wavy TE Larger blade volume with design #1 Better manufacturability Spanwise Wavy Trailing Edge Airfoil 2/ 31 NAWEA 2015
16 Design Improvements: Design #2 Can we start wavy structure closer to TE? 90%C cut (wavy TE at 90% of Chord) Previous wavy TE Can we get rid of 2-D spanwise vortex structure With the New Designs?? Wavy TE at 90% of chord Larger blade volume with design #2 Better manufacturability Spanwise Wavy Trailing Edge Airfoil 3/ 31 NAWEA 2015
17 Improved Wavy Trailing Edge Designs A. Lower half cut 3/4 flatback B. Lower half cut 1/2 flatback C. 90C cut 3/4 flatback D. 90C cut 1/2 flatback Structurally enhanced designs A. Lower half cut 3/4 flatback (min. TE thickness 15.38% of C) B. Lower half cut 1/2 flatback (min. TE thickness 13.12% of C) C. 90C cut 3/4 flatback (min. TE thickness 13.12% of C) D. 90C cut 1/2 flatback (min. TE thickness 8.75% of C) Spanwise Wavy Trailing Edge Airfoil 4/ 31 NAWEA 2015
18 Results and Discussion: Flowfield (Iso-vorticity mag.) FB (flatback TE) Lower half cut 3/4 flatback Lower half cut 1/2 flatback FB (sharp TE) 90C cut 3/4 flatback 90C cut 1/2 flatback Lower half cut 3/4 flatback, still has spanwise coherent vortex structure Lower half cut 1/2 flatback, has more streamwise vorticity 90C cut designs work better to break up spanwise vortex Spanwise Wavy Trailing Edge Airfoil 5/ 31 NAWEA 2015
19 Results and Discussion: Flowfield (Vorticity contours) Aerodynamic characteristics; Trailing edge vortex shedding pattern Lower half cut 3/4 flatback Crest Lower half cut 1/2 flatback Crest Trough Trough Both Lower half cut airfoils have similar vortex shedding patterns along span. With shallow wave (3/4 flatback), strong 2-D coherent vortex structure. With deep wave (1/2 flatback), vortex strength now weaken and vortex core is formed at further downstream. Spanwise Wavy Trailing Edge Airfoil 6/ 31 NAWEA 2015
20 Results and Discussion: Flowfield (Vorticity contours) Aerodynamic characteristics; Trailing edge vortex shedding pattern Lower half cut 3/4 flatback Lower half cut 1/2 flatback Trough Crest Trough Crest Both Lower half cut airfoils have similar vortex shedding patterns along span. With shallow wave (3/4 flatback), strong 2-D coherent vortex structure. With deep wave (1/2 flatback), vortex strength now weaken and vortex core is formed at further downstream. Spanwise Wavy Trailing Edge Airfoil 7/ 31 NAWEA 2015
21 Results and Discussion: Flowfield (Vorticity contours) Aerodynamic characteristics; Trailing edge vortex shedding pattern 90C cut 3/4 flatback Crest 90C cut 1/2 flatback Crest Trough Trough With 90%C cut designs, now entirely different vortex shedding patterns at the crest and trough. Now vortex structure is more like 3-D, affected by streamwise vorticity. Spanwise Wavy Trailing Edge Airfoil 8/ 31 NAWEA 2015
22 Results and Discussion: Flowfield (Vorticity contours) Aerodynamic characteristics; Trailing edge vortex shedding pattern 90C cut 3/4 flatback 90C cut 1/2 flatback Trough Crest Trough Crest With 90%C cut designs, now entirely different vortex shedding patterns at the crest and trough. Now vortex structure is more like 3-D, affected by streamwise vorticity. Spanwise Wavy Trailing Edge Airfoil 9/ 31 NAWEA 2015
23 Results and Discussion: Lift vs. AoA Lower half cut 3/4 flatback Lower half cut 1/2 flatback 90C cut 3/4 flatback 90C cut 1/2 flatback Lower half cut 3/4 flatback, only small amount of lift loss. Lower half cut 1/2 flatback, 90C 3/4 flatback, some lift loss, but not a lot. 90C 1/2 flatback, too much loss of lift. (not eligible to be an improved design) Spanwise Wavy Trailing Edge Airfoil 10/ 31 NAWEA 2015
24 Results and Discussion: Lift vs. Drag Polar Lower half cut 3/4 flatback Lower half cut 1/2 flatback 90C cut 3/4 flatback Lower half cut 3/4 flatback, only little amount of lift loss, but too much drag (not eligible as a drag reduced design) Lower half cut 1/2 flatback, 90C 3/4 flatback, some of lift loss, but not a lot and large drag reduction (down to 1/3 of the original flatback design) Spanwise Wavy Trailing Edge Airfoil 11/ 31 NAWEA 2015
25 Results and Discussion: Lift / Drag Map Lower half cut 1/2 flatback 90C cut 3/4 flatback Lower half cut 1/2 flatback, 90C 3/4 flatback have better aerodynamic performance than the original flatback aifoil for both moderate and high angle of attack. 90C 3/4 flatback has broader performance coverage than lower halfway cut 1/2 flatback. Spanwise Wavy Trailing Edge Airfoil 12/ 31 NAWEA 2015
26 Results and Discussion: Acoutic Measurement Details Aeroacoustic characteristics; measurement details - 3 pressure fluctuation measurement points at 3C distance from TE - 0.5C distances between 3 locations - Freestream M = 0.3, Re = 666,000, AoA = 12 SPL db = 10 log 10 ( p 2 p rrr 2 ), 1kHz sampling rates for 1 sec Spanwise Wavy Trailing Edge Airfoil 13/ 31 NAWEA 2015
27 Results and Discussion: Sound Pressure Level Lower half cut 3/4 flatback Lower half cut 1/2 flatback 90C cut 3/4 flatback 90C cut 1/2 flatback Noise emissions reduced about 20 db by the improved wavy trailing edge. Regarding aerodynamic performance, the lower half cut 1/2 and 90C 3/4 flatback may be the best designs acoustic-wise. Spanwise Wavy Trailing Edge Airfoil 14/ 31 NAWEA 2015
28 Results and Discussion: Noise Spectrum (by FFT) peak [db] Const. thickness flatback TE: Tonal noise at low frequency range Noise peak is alleviated by the improved designs. Spanwise Wavy Trailing Edge Airfoil 15/ 31 NAWEA 2015
29 Results and Discussion / Overall Overall (AoA 12 ) Min. TE thic kness Cl Cd Cl/Cd Acoustics Lower half cut 3/4 flatback High Drag High noise 15.38% of C Lower half cut 1/2 flatback 90C cut 3/4 flatback 13.12% of C Best Performance! 13.12% of C C cut 1/2 flatback Low Lift 8.75% of C Best Performance: 90%C cut ¾ flatback & Lower half cut ½ flatback! Spanwise Wavy Trailing Edge Airfoil 16/ 31 NAWEA 2015
30 Conclusions Aerodynamic Performance Larger blade volume with the lower half cut and 90%C cut wavy trailing edges 90%C cut wavy TE more effective to break down spanwise vortex compared to the lower half cut Lower half cut wavy TE 1/2 flatback: small lift loss & large drag reduction, consequently high L/D 90%C cut wavy TE 1/2 flatback: although dramatic drag reduction, too much lift loss, consequently low L/D 90%C cut wavy TE 3/4 flatback: small lift loss & large drag reduction, consequently high L/D Acoustic Noise Reduction Strong magnitude tonal noise peaks at low frequency (100~170 Hz) with const. Flatback airfoil, was reduced up to 20 db (mitigated down to the sharp TE noise level) by the improved designs Although best acoutic noise reduction design is the 90%C cut wavy TE 1/2 flatback, however, relatively worse aerodynamic performance. Best aerodynamic and aeroacoustic performance: Lower half cut wavy TE 1/2 flatback / 90%C cut wavy TE 3/4 flatback Future work Combine to investigate lower half 90%C cut wavy TE 1/2 flatback Spanwise Wavy Trailing Edge Airfoil 17/ 31 NAWEA 2015
31 NAWEA 2015 SYMPOSIUM THANK YOU Acknowledgements UMD supercomputing resources Use of Deepthought II computing cluster Research sponsored by State of Maryland (MHEC/MEA) Spanwise Wavy Trailing Edge Airfoil 18/ 31 NAWEA 2015
Effect of Wavy Trailing Edge on 100meter Flatback Wind Turbine Blade
Journal of Physics: Conference Series PAPER OPEN ACCESS Effect of Wavy Trailing Edge on 100meter Flatback Wind Turbine Blade To cite this article: SJ Yang and J D Baeder 2016 J. Phys.: Conf. Ser. 753 022060
More informationComputational Analysis of Blunt Trailing Edge NACA 0012 Airfoil
Computational Analysis of Blunt Trailing Edge NACA 2 Airfoil Anusha K Department of Aerospace Engineering Madras Institute of Technology, India anusugan7@gmail.com Abstract Blunt trailing edge airfoil
More informationADVANCES IN AERODYNAMICS OF WIND TURBINE BLADES
ADVANCES IN AERODYNAMICS OF WIND TURBINE BLADES Herning / October 3 / 2017 By Jesper Madsen Chief Engineer, Aerodynamics & Acoustics WIND ENERGY DENMARK Annual Event 2017 Agenda 1. Aerodynamic design and
More informationAPPLICATION OF RESEARCH RESULTS AT LM WIND POWER
APPLICATION OF RESEARCH RESULTS AT LM WIND POWER Herning / March 27 / 2014 By Jesper Madsen Chief Engineer Aerodynamics and Acoustics AGENDA 1. EUDP Projects 1. DANAERO MW 2. Optimization of vortex generators
More informationTrailing edge noise production, prediction and control
Trailing edge noise production, prediction and control Con Doolan, Danielle Moreau, Elias Arcondoulis and Cristobal Albarracin School of Mechanical Engineering, University of Adelaide, South Australia,
More informationUniversity of Bristol - Explore Bristol Research. Publisher's PDF, also known as Version of record
Liu, X., Azarpeyvand, M., & Joseph, P. (2015). On the acoustic and aerodynamic performance of serrated airfoils. Paper presented at The 22nd International Congress on Sound and Vibration, Florence, France.
More informationEffect of Co-Flow Jet over an Airfoil: Numerical Approach
Contemporary Engineering Sciences, Vol. 7, 2014, no. 17, 845-851 HIKARI Ltd, www.m-hikari.com http://dx.doi.org/10.12988/ces.2014.4655 Effect of Co-Flow Jet over an Airfoil: Numerical Approach Md. Riajun
More informationWind tunnel effects on wingtip vortices
48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 4-7 January 2010, Orlando, Florida AIAA 2010-325 Wind tunnel effects on wingtip vortices Xin Huang 1, Hirofumi
More informationNUMERICAL SIMULATION OF ACTIVE FLOW CONTROL BASED ON STREAMWISE VORTICES FOR A BLUNT TRAILING EDGE AIRFOIL
BBAA VI International Colloquium on: Bluff Bodies Aerodynamics & Applications Milano, Italy, July, 20-24 2008 NUMERICAL SIMULATION OF ACTIVE FLOW CONTROL BASED ON STREAMWISE VORTICES FOR A BLUNT TRAILING
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 informationNumerical simulation of a flat back airfoil for wind turbine applications.
University of Louisville ThinkIR: The University of Louisville's Institutional Repository Electronic Theses and Dissertations 4-2010 Numerical simulation of a flat back airfoil for wind turbine applications.
More informationThe Effect of Blade Thickness and Angle of Attack on Broadband Fan Noise
The Effect of Blade Thickness and Angle of Attack on Broadband Fan Noise Stewart Glegg Florida Atlantic University and William Devenport Virginia Tech Work Supported by ONR, Prog. Manager: Dr. Ron Joslin
More informationTHE BRIDGE COLLAPSED IN NOVEMBER 1940 AFTER 4 MONTHS OF ITS OPENING TO TRAFFIC!
OUTLINE TACOMA NARROWS BRIDGE FLOW REGIME PAST A CYLINDER VORTEX SHEDDING MODES OF VORTEX SHEDDING PARALLEL & OBLIQUE FLOW PAST A SPHERE AND A CUBE SUMMARY TACOMA NARROWS BRIDGE, USA THE BRIDGE COLLAPSED
More informationA comparison of NACA 0012 and NACA 0021 self-noise at low Reynolds number
A comparison of NACA 12 and NACA 21 self-noise at low Reynolds number A. Laratro, M. Arjomandi, B. Cazzolato, R. Kelso Abstract The self-noise of NACA 12 and NACA 21 airfoils are recorded at a Reynolds
More informationAerodynamic Analysis of Blended Winglet for Low Speed Aircraft
, July 1-3, 2015, London, U.K. Aerodynamic Analysis of Blended Winglet for Low Speed Aircraft Pooja Pragati, Sudarsan Baskar Abstract This paper provides a practical design of a new concept of massive
More informationAE Dept., KFUPM. Dr. Abdullah M. Al-Garni. Fuel Economy. Emissions Maximum Speed Acceleration Directional Stability Stability.
Aerodynamics: Introduction Aerodynamics deals with the motion of objects in air. These objects can be airplanes, missiles or road vehicles. The Table below summarizes the aspects of vehicle performance
More informationAERODYNAMIC CHARACTERISTICS OF NACA 0012 AIRFOIL SECTION AT DIFFERENT ANGLES OF ATTACK
AERODYNAMIC CHARACTERISTICS OF NACA 0012 AIRFOIL SECTION AT DIFFERENT ANGLES OF ATTACK SUPREETH NARASIMHAMURTHY GRADUATE STUDENT 1327291 Table of Contents 1) Introduction...1 2) Methodology.3 3) Results...5
More informationReduction of Skin Friction Drag in Wings by Employing Riblets
Reduction of Skin Friction Drag in Wings by Employing Riblets Kousik Kumaar. R 1 Assistant Professor Department of Aeronautical Engineering Nehru Institute of Engineering and Technology Coimbatore, India
More informationAnna University Regional office Tirunelveli
Effect of Tubercle Leading Edge Control Surface on the Performance of the Double Delta Wing Fighter Aircraft P Sharmila 1, S Rajakumar 2 1 P.G. Scholar, 2 Assistant Professor, Mechanical Department Anna
More informationExperimental and Theoretical Investigation for the Improvement of the Aerodynamic Characteristic of NACA 0012 airfoil
International Journal of Mining, Metallurgy & Mechanical Engineering (IJMMME) Volume 2, Issue 1 (214) ISSN 232 46 (Online) Experimental and Theoretical Investigation for the Improvement of the Aerodynamic
More informationNUMERICAL INVESTIGATION OF AERODYNAMIC CHARACTERISTICS OF NACA AIRFOIL WITH A GURNEY FLAP
Int. J. Mech. Eng. & Rob. Res. 2012 MasoudJahanmorad Nouri et al., 2012 Research Paper ISSN 2278 0149 www.ijmerr.com Vol. 1, No. 3, October 2012 2012 IJMERR. All Rights Reserved NUMERICAL INVESTIGATION
More informationLecture # 08: Boundary Layer Flows and Drag
AerE 311L & AerE343L Lecture Notes Lecture # 8: Boundary Layer Flows and Drag Dr. Hui H Hu Department of Aerospace Engineering Iowa State University Ames, Iowa 511, U.S.A y AerE343L #4: Hot wire measurements
More informationAeroacoustic and Aerodynamic Performances of an Aerofoil Subjected to Sinusoidal Leading Edges
Aeroacoustic and Aerodynamic Performances of an Aerofoil Subjected to Sinusoidal Leading Edges Tze Pei Chong 1, Alexandros Vathylakis 2, Archie McEwen 3, Foster Kemsley 4, Chioma Muhammad 5 and Saarim
More informationAnalyses of the mechanisms of amplitude modulation of aero-acoustic wind turbine sound
Analyses of the mechanisms of amplitude modulation of aero-acoustic wind turbine sound Andreas Fischer Helge Aagaard Madsen Knud Abildgaard Kragh Franck Bertagnolio DTU Wind Energy Technical University
More informationANALYSIS OF AERODYNAMIC CHARACTERISTICS OF A SUPERCRITICAL AIRFOIL FOR LOW SPEED AIRCRAFT
ANALYSIS OF AERODYNAMIC CHARACTERISTICS OF A SUPERCRITICAL AIRFOIL FOR LOW SPEED AIRCRAFT P.Sethunathan 1, M.Niventhran 2, V.Siva 2, R.Sadhan Kumar 2 1 Asst.Professor, Department of Aeronautical Engineering,
More informationComputational Investigation of Airfoils with Miniature Trailing Edge Control Surfaces
AIAA-24-5 Computational Investigation of Airfoils with Miniature Trailing Edge Control Surfaces Hak-Tae Lee, Ilan M. Kroo Stanford University, Stanford, CA 9435 Abstract Miniature trailing edge effectors
More informationInfluence of wing span on the aerodynamics of wings in ground effect
Influence of wing span on the aerodynamics of wings in ground effect Sammy Diasinos 1, Tracie J Barber 2 and Graham Doig 2 Abstract A computational fluid dynamics study of the influence of wing span has
More informationComputational Analysis of Cavity Effect over Aircraft Wing
World Engineering & Applied Sciences Journal 8 (): 104-110, 017 ISSN 079-04 IDOSI Publications, 017 DOI: 10.589/idosi.weasj.017.104.110 Computational Analysis of Cavity Effect over Aircraft Wing 1 P. Booma
More informationAERODYNAMICS I LECTURE 7 SELECTED TOPICS IN THE LOW-SPEED AERODYNAMICS
LECTURE 7 SELECTED TOPICS IN THE LOW-SPEED AERODYNAMICS The sources of a graphical material used in this lecture are: [UA] D. McLean, Understanding Aerodynamics. Arguing from the Real Physics. Wiley, 2013.
More informationComputational Analysis of the S Airfoil Aerodynamic Performance
Computational Analysis of the 245-3S Airfoil Aerodynamic Performance Luis Velazquez-Araque and Jiří Nožička 2 Department of Mechanical Engineering National University of Táchira, San Cristóbal 5, Venezuela
More informationResearch Article Numerical Analysis of Wind Turbine Airfoil Aerodynamic Performance with Leading Edge Bump
Mathematical Problems in Engineering Volume 25, Article ID 493253, 8 pages http://dx.doi.org/.55/25/493253 Research Article Numerical Analysis of Wind Turbine Airfoil Aerodynamic Performance with Leading
More informationROAD MAP... D-1: Aerodynamics of 3-D Wings D-2: Boundary Layer and Viscous Effects D-3: XFLR (Aerodynamics Analysis Tool)
Unit D-1: Aerodynamics of 3-D Wings Page 1 of 5 AE301 Aerodynamics I UNIT D: Applied Aerodynamics ROAD MAP... D-1: Aerodynamics of 3-D Wings D-: Boundary Layer and Viscous Effects D-3: XFLR (Aerodynamics
More informationTurbulence Modelling of Deep Dynamic Stall at Low Reynolds Number
, June 30 - July 2, 2010, London, U.K. Turbulence Modelling of Deep Dynamic Stall at Low Reynolds Number Shengyi Wang, Lin Ma, Derek B Ingham, Mohamed Pourkashanian and Zhi Tao Abstract The unsteady separated
More informationThis is the author s final accepted version.
Ibrahim, I.H., Joy, J. and New, T.N. (2016) Numerical Investigation on Flow Separation Control of Low Reynolds Number Sinusoidal Aerofoils. In: 46th AIAA Fluid Dynamics Conference, AIAA AVIATION Forum,
More informationInfluence of rounding corners on unsteady flow and heat transfer around a square cylinder
Influence of rounding corners on unsteady flow and heat transfer around a square cylinder S. K. Singh Deptt. of Mech. Engg., M. B. M. Engg. College / J. N. V. University, Jodhpur, Rajasthan, India Abstract
More informationLift for a Finite Wing. all real wings are finite in span (airfoils are considered as infinite in the span)
Lift for a Finite Wing all real wings are finite in span (airfoils are considered as infinite in the span) The lift coefficient differs from that of an airfoil because there are strong vortices produced
More informationet al. [25], Noack et al. [26] for circular cylinder flows, Van Oudheusden [27] for square cylinder and Durgesh [28] for a flat plate model. The first two modes appear as phase-shifted versions of each
More informationIncompressible Flow over Airfoils
Road map for Chap. 4 Incompressible Flow over Airfoils Aerodynamics 2015 fall - 1 - < 4.1 Introduction > Incompressible Flow over Airfoils Incompressible flow over airfoils Prandtl (20C 초 ) Airfoil (2D)
More informationC-1: Aerodynamics of Airfoils 1 C-2: Aerodynamics of Airfoils 2 C-3: Panel Methods C-4: Thin Airfoil Theory
ROAD MAP... AE301 Aerodynamics I UNIT C: 2-D Airfoils C-1: Aerodynamics of Airfoils 1 C-2: Aerodynamics of Airfoils 2 C-3: Panel Methods C-4: Thin Airfoil Theory AE301 Aerodynamics I : List of Subjects
More informationEFFECT OF GURNEY FLAPS AND WINGLETS ON THE PERFORMANCE OF THE HAWT
Chapter-6 EFFECT OF GURNEY FLAPS AND WINGLETS ON THE PERFORMANCE OF THE HAWT 6.1 Introduction The gurney flap (wicker bill) was a small flat tab projecting from the trailing edge of a wing. Typically it
More informationWESEP 594 Research Seminar
WESEP 594 Research Seminar Aaron J Rosenberg Department of Aerospace Engineering Iowa State University Major: WESEP Co-major: Aerospace Engineering Motivation Increase Wind Energy Capture Betz limit: 59.3%
More informationDesign & Analysis of Natural Laminar Flow Supercritical Aerofoil for Increasing L/D Ratio Using Gurney Flap
Design & Analysis of Natural Laminar Flow Supercritical Aerofoil for Increasing L/D Ratio Using Gurney Flap U.Praveenkumar 1, E.T.Chullai 2 M.Tech Student, School of Aeronautical Science, Hindustan University,
More informationNumerical Investigation of Multi Airfoil Effect on Performance Increase of Wind Turbine
International Journal of Engineering & Applied Sciences (IJEAS) International Journal of Engineering Applied Sciences (IJEAS) Vol.9, Issue 3 (2017) 75-86 Vol.x, Issue x(201x)x-xx http://dx.doi.org/10.24107/ijeas.332075
More informationPart III: Airfoil Data. Philippe Giguère
Part III: Airfoil Data Philippe Giguère Former Graduate Research Assistant (now with GE Wind Energy) Department of Aerospace Engineering University of Illinois at Urbana-Champaign Steady-State Aerodynamics
More informationNumerical simulations of a large offshore wind turbine exposed to turbulent inflow conditions
9 th European Seminar OWEMES 2017 Numerical simulations of a large offshore wind turbine exposed to turbulent inflow conditions Galih Bangga, Giorgia Guma, Thorsten Lutz and Ewald Krämer Institute of Aerodynamics
More informationHigh fidelity gust simulations around a transonic airfoil
High fidelity gust simulations around a transonic airfoil AEROGUST Workshop 27 th - 28 th April 2017, University of Liverpool Presented by B. Tartinville (Numeca) Outline of the presentation 1Objectives
More informationAerodynamic investigation of Winglets on Wind Turbine Blades using CFD
Risø-R-1543(EN) Aerodynamic investigation of Winglets on Wind Turbine Blades using CFD Jeppe Johansen and Niels N. Sørensen Risø National Laboratory Roskilde Denmark February 26 Author: Jeppe Johansen
More informationA COMPUTATIONAL STUDY ON THE DESIGN OF AIRFOILS FOR A FIXED WING MAV AND THE AERODYNAMIC CHARACTERISTIC OF THE VEHICLE
28 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES A COMPUTATIONAL STUDY ON THE DESIGN OF AIRFOILS FOR A FIXED WING MAV AND THE AERODYNAMIC CHARACTERISTIC OF THE VEHICLE Jung-Hyun Kim*, Kyu-Hong
More informationLecture # 08: Boundary Layer Flows and Controls
AerE 344 Lecture Notes Lecture # 8: Boundary Layer Flows and Controls Dr. Hui Hu Department of Aerospace Engineering Iowa State University Ames, Iowa 511, U.S.A Flow Separation on an Airfoil Quantification
More informationPitching Airfoil Performance Enhancement Using Co-Flow Jet Flow Control at High Mach Number
AIAA SciTech 3-7 January 24, National Harbor, Maryland 52nd Aerospace Sciences Meeting AIAA 24-95 Pitching Airfoil Performance Enhancement Using Co-Flow Jet Flow Control at High Mach Number Alexis Lefebvre,
More informationAn Impeller Blade Analysis of Centrifugal Gas Compressor Using CFD
An Impeller Blade Analysis of Centrifugal Gas Compressor Using CFD Vivek V. Kulkarni Department of Mechanical Engineering KLS Gogte Institute of Technology, Belagavi, Karnataka Dr. Anil T.R. Department
More informationSenior mechanical energy conversion trends
Senior mechanical energy conversion trends Introduction and Analysis to fan blade profile and CFD Simulation Of An Appropriate Blade Profile for improving energy efficiency HAMED ROSTAMALIZADEH 95742906
More informationSIMULATION OF TIP LEAKAGE FLOW AROUND PARTIAL SQUEALER RIMS IN AXIAL TURBINES
SIMULATION OF TIP LEAKAGE FLOW AROUND PARTIAL SQUEALER RIMS IN AXIAL TURBINES Levent Kavurmacioglu 1, Debashis Dey 2 & Cengiz Camci 3 Department of Aerospace Engineering Turbomachinery Heat Transfer Laboratory
More informationGEOMETRY TIP CAP EFFECTS ON FORMATION AND NEAR WAKE EVOLUTION OF THE ROTOR TIP VORTICES
36th AIAA Fluid Dynamics Conference and Exhibit 5-8 June 2006, San Francisco, California AIAA 2006-3376 GEOMETRY TIP CAP EFFECTS ON FORMATION AND NEAR WAKE EVOLUTION OF THE ROTOR TIP VORTICES Roxana Vasilescu
More informationAerodynamic Performance Optimization Of Wind Turbine Blade By Using High Lifting Device
Aerodynamic Performance Optimization Of Wind Turbine Blade By Using High Lifting Device Razeen Ridhwan, Mohamed Alshaleeh, Arunvinthan S Abstract: In the Aerodynamic performance of wind turbine blade by
More informationDesign of the LRP airfoil series using 2D CFD
Journal of Physics: Conference Series OPEN ACCESS Design of the LRP airfoil series using 2D CFD To cite this article: Frederik Zahle et al 2014 J. Phys.: Conf. Ser. 524 012020 View the article online for
More informationNumerical Simulation And Aerodynamic Performance Comparison Between Seagull Aerofoil and NACA 4412 Aerofoil under Low-Reynolds 1
Advances in Natural Science Vol. 3, No. 2, 2010, pp. 244-20 www.cscanada.net ISSN 171-7862 [PRINT] ISSN 171-7870 [ONLINE] www.cscanada.org *The 3rd International Conference of Bionic Engineering* Numerical
More informationWake modelling for offshore wind turbine parks. Jens N. Sørensen Department of Wind Energy Technical University of Denmark
Wake modelling for offshore wind turbine parks Jens N. Sørensen Department of Wind Energy Technical University of Denmark Wake and Wind Farm Aerodynamics Basic questions and issues: How important is the
More informationComputationally Efficient Determination of Long Term Extreme Out-of-Plane Loads for Offshore Turbines
Computationally Efficient Determination of Long Term Extreme Out-of-Plane Loads for Offshore Turbines Anand Natarajan Senior Scientist Wind Energy Department, Risø DTU Denmark Introduction IEC 61400-1
More informationFLOW CONTROL APPLIED TO OUTER WING SLAT-EDGE PROBLEM: CFD & EXPERIMENT
FLOW CONTROL APPLIED TO OUTER WING SLAT-EDGE PROBLEM: CFD & EXPERIMENT IAP 30 March 2017 Tel-Aviv University (TAU) IAI: I. Detinis, M. Steinbuch, S. Segal TAU: M. Lagutin & A. Seifert This study is part
More informationEXPERIMENTAL ANALYSIS OF THE CONFLUENT BOUNDARY LAYER BETWEEN A FLAP AND A MAIN ELEMENT WITH SAW-TOOTHED TRAILING EDGE
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES EXPERIMENTAL ANALYSIS OF THE CONFLUENT BOUNDARY LAYER BETWEEN A FLAP AND A MAIN ELEMENT WITH SAW-TOOTHED TRAILING EDGE Lemes, Rodrigo Cristian,
More informationInvestigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil. Kanin Homsrivaranon
Investigation of Active Flow Control on an Extremely Thick Wind Turbine Airfoil By Kanin Homsrivaranon Submitted to the graduate program in Aerospace Engineering and the Graduate Faculty of the University
More informationAir Craft Winglet Design and Performance: Cant Angle Effect
Journal of Robotics and Mechanical Engineering Research Air Craft Winglet Design and Performance: Cant Angle Effect Eslam Said Abdelghany 1, Essam E Khalil 2*, Osama E Abdellatif 3 and Gamal elhariry 4
More informationDESIGN AND ANALYSIS OF NACA4420 WIND TURBINE AEROFOIL USING CFD
International Journal of Mechanical Engineering and Technology (IJMET) Volume 8, Issue 6, June 2017, pp. 403 410, Article ID: IJMET_08_06_042 Available online at http://www.iaeme.com/ijmet/issues.asp?jtype=ijmet&vtype=8&itype=6
More informationNumerical Analysis of Wings for UAV based on High-Lift Airfoils
Numerical Analysis of Wings for UAV based on High-Lift Airfoils Sachin Srivastava Department of Aeronautical Engineering Malla Reddy College of Engineering & Technology, Hyderabad, Telangana, India Swetha
More informationFLOW SIMULATION OF AN SST CONFIGURATION AT LOW-SPEED AND HIGH-LIFT CONDITIONS
25 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES FLOW SIMULATION OF AN SST CONFIGURATION AT LOW-SPEED AND HIGH-LIFT CONDITIONS Zhong Lei, Dong-Youn Kwak Supersonic Transport Team, Japan Aerospace
More informationCFD Studies on Triangular Micro-Vortex Generators in Flow Control
IOP Conference Series: Materials Science and Engineering PAPER OPEN ACCESS CFD Studies on Triangular Micro-Vortex Generators in Flow Control To cite this article: V Yashodhar et al 2017 IOP Conf. Ser.:
More informationCFD DESIGN STUDY OF A CIRCULATION CONTROL INLET GUIDE VANE OF AN AEROFOIL
Int. J. Mech. Eng. & Rob. Res. 2012 Manjunath Ichchangi and Manjunath H, 2012 Research Paper ISSN 2278 0149 www.ijmerr.com Vol. 1, No. 3, October 2012 2012 IJMERR. All Rights Reserved CFD DESIGN STUDY
More informationEXPERIMENTAL AND NUMERICAL STUDY OF A TWO- ELEMENT WING WITH GURNEY FLAP
25 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES EXPERIMENTAL AND NUMERICAL STUDY OF A TWO- ELEMENT WING WITH GURNEY FLAP F.M. Catalano PhD.( catalano@sc.usp.br ) *, G. L. Brand * * Aerodynamic
More informationNumerical study of Wavy Blade Section for Wind Turbines
Journal of Physics: Conference Series PAPER OPEN ACCESS Numerical study of Wavy Blade Section for Wind Turbines To cite this article: C.M Kobæk and M.O.L Hansen 2016 J. Phys.: Conf. Ser. 753 022039 Recent
More informationA noise generation and propagation model for large wind farms
Wind Farm Noise: Paper ICA2016-86 A noise generation and propagation model for large wind farms Franck Bertagnolio (a) (a) DTU Wind Energy, Denmark, frba@dtu.dk Abstract A wind turbine noise calculation
More informationCFD VALIDATION STUDY OF NEXST-1 NEAR MACH 1
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES CFD VALIDATION STUDY OF NEXST-1 NEAR ACH 1 Keizo Takenaka*, Kazuomi Yamamoto**, Ryoji Takaki** *itsubishi Heavy Industries, Ltd., 10 Oye-cho, inato-ku,
More informationControl of the Spanwise Distribution of Circulation on NACA 0012 and Flat Plate Wings
45th AIAA Aerospace Sciences Meeting and Exhibit 8-11 January 2007, Reno, Nevada AIAA 2007-1121 Control of the Spanwise Distribution of Circulation on NACA 0012 and Flat Plate Wings D. Williams *, S. Doshi,
More informationImproved Aerodynamic Characteristics of Aerofoil Shaped Fuselage than that of the Conventional Cylindrical Shaped Fuselage
International Journal of Scientific & Engineering Research Volume 4, Issue 1, January-213 1 Improved Aerodynamic Characteristics of Aerofoil Shaped Fuselage than that of the Conventional Cylindrical Shaped
More informationNavier Stokes analysis of lift-enhancing tabs on multi-element airfoils
Navier Stokes analysis of lift-enhancing tabs on multi-element airfoils Paul G. Carrannanto, Bruce L. Storms, James C. Ross, Russell M. Cummings Ford Motor Company, Dearborn, MI 48121, USA Aerospace Computing,
More informationLarge Eddy Simulation of Wing Tip Vortex in the Near Field
Large Eddy Simulation of Wing Tip Vortex in the Near Field Li Jiang Jiangang Cai Chaoqun Liu Technical Report 2007-13 http://www.uta.edu/math/preprint/ Large Eddy Simulation of Wing Tip Vortex in the Near
More informationCFD ANALYSIS OF FLOW AROUND AEROFOIL FOR DIFFERENT ANGLE OF ATTACKS
www.mechieprojects.com CFD ANALYSIS OF FLOW AROUND AEROFOIL FOR DIFFERENT ANGLE OF ATTACKS PRESENTATION OUTLINE AIM INTRODUCTION LITERATURE SURVEY CFD ANALYSIS OF AEROFOIL RESULTS CONCLUSIONS www.mechieprojects.com
More informationVolume 2, Issue 5, May- 2015, Impact Factor: Structural Analysis of Formula One Racing Car
Structural Analysis of Formula One Racing Car Triya Nanalal Vadgama 1, Mr. Arpit Patel 2, Dr. Dipali Thakkar 3, Mr. Jignesh Vala 4 Department of Aeronautical Engineering, Sardar Vallabhbhai Patel Institute
More informationInvestigation on 3-D Wing of commercial Aeroplane with Aerofoil NACA 2415 Using CFD Fluent
Investigation on 3-D of commercial Aeroplane with Aerofoil NACA 2415 Using CFD Fluent Rohit Jain 1, Mr. Sandeep Jain 2, Mr. Lokesh Bajpai 3 1PG Student, 2 Associate Professor, 3 Professor & Head 1 2 3
More informationDynamic Stall For A Vertical Axis Wind Turbine In A Two-Dimensional Study
Abstracts of Conference Papers: TSBE EngD Conference, TSBE Centre, University of Reading, Whiteknights, RG6 Dynamic Stall For A Vertical Axis Wind Turbine In A Two-Dimensional Study R. Nobile 1,*, Dr M.
More informationAerodynamics and Vortex Structures of a Flapping Airfoil in Forward Flight in Proximity of Ground
Washington University in St. Louis Washington University Open Scholarship Engineering and Applied Science Theses & Dissertations Engineering and Applied Science Spring 5-19-2017 Aerodynamics and Vortex
More informationThe subsonic compressibility effect is added by replacing. with
Swept Wings The main function of a swept wing is to reduce wave drag at transonic and supersonic speeds. Consider a straight wing and a swept wing in a flow with a free-stream velocity V. Assume that the
More informationEffect of Dimple on Aerodynamic Behaviour of Airfoil
Effect of Dimple on Aerodynamic Behaviour of Airfoil Amit Kumar Saraf #1, Dr. Mahendra Pratap Singh *2, Dr. Tej Singh Chouhan #3 #1 Department of Mechanical Engineering, Jagannath University Jaipur, India
More information2-D Computational Analysis of a Vertical Axis Wind Turbine Airfoil
2-D Computational Analysis of a Vertical Axis Wind Turbine Airfoil Akshay Basavaraj1 Student, Department of Aerospace Engineering, Amrita School of Engineering, Coimbatore 641 112, India1 Abstract: This
More informationBlade Design and Performance Analysis of Wind Turbine
International Journal of ChemTech Research CODEN( USA): IJCRGG ISSN : 0974-4290 Vol.5, No.2, pp 1054-1061, April-June 2013 ICGSEE-2013[14 th 16 th March 2013] International Conference on Global Scenario
More informationJet Propulsion. Lecture-17. Ujjwal K Saha, Ph. D. Department of Mechanical Engineering Indian Institute of Technology Guwahati
Lecture-17 Prepared under QIP-CD Cell Project Jet Propulsion Ujjwal K Saha, Ph. D. Department of Mechanical Engineering Indian Institute of Technology Guwahati 1 Lift: is used to support the weight of
More informationEffects of Leading-Edge Protection Tape on Wind Turbine Blade Performance
Effects of Leading-Edge Protection Tape on Wind Turbine Blade Performance by Agrim Sareen, Chinmay A. Sapre and Michael S. Selig REPRINTED FROM WIND ENGINEERING VOLUME 36, NO. 5, 2012 MULTI-SCIENCE PUBLISHING
More informationAN EXPERIMENTAL AND COMPUTATIONAL STUDY OF THE AERODYNAMIC CHARACTERISTICS AN OSCILLATORY PITCHING NACA0012 AEROFOIL
AN EXPERIMENTAL AND COMPUTATIONAL STUDY OF THE AERODYNAMIC CHARACTERISTICS AN OSCILLATORY PITCHING NACA0012 AEROFOIL Ashim Yadav, Simon Prince & Jenny Holt School of Aerospace, Transport and Manufacturing,
More informationNumerical and Experimental Investigations of Lift and Drag Performances of NACA 0015 Wind Turbine Airfoil
International Journal of Materials, Mechanics and Manufacturing, Vol. 3, No., February 2 Numerical and Experimental Investigations of Lift and Drag Performances of NACA Wind Turbine Airfoil İzzet Şahin
More informationNumerical Investigation of Flow Field and Effect of Varying Vortex Generator Location on Wing Performance
American Journal of Fluid Dynamics 2016, 6(1): 11-19 DOI: 10.5923/j.ajfd.20160601.02 Numerical Investigation of Flow Field and Effect of Varying Vortex Generator Location on Wing Performance Shubham Agarwal
More informationCFD development for wind energy aerodynamics
CFD development for wind energy aerodynamics Hamid Rahimi, Bastian Dose, Bernhard Stoevesandt Fraunhofer IWES, Germany IEA Task 40 Kick-off Meeting 12.11.2017 Tokyo Agenda BEM vs. CFD for wind turbine
More informationCFD Analysis of Supercritical Airfoil with Different Camber
CFD Analysis of Supercritical Airfoil with Different Camber S.Manikandan 1, R.G.Bhuvana 2, Sowmya.A.Srinivasan 3 Assistant prof, Department of Aeronautical Engineering, Jeppiaar Engineering College, Chennai,
More informationNumerical computations of a tip vortex including gap with RANS and LES turbulence models
1 Numerical computations of a tip vortex including gap with RANS and LES turbulence models J. Decaix & C. Münch-Alligné, HES SO Valais, Sion, Switzerland G. Balarac, LEGI, Grenoble, France 2 HYDRONET 2
More informationPrinciples of glider flight
Principles of glider flight [ Lecture 1: Lift, drag & glide performance ] Richard Lancaster Email: Richard@RJPLancaster.net Twitter: @RJPLancaster ASK-21 illustrations Copyright 1983 Alexander Schleicher
More informationValidation of the CQU-DTU-LN1 series of airfoils
Journal of Physics: Conference Series OPEN ACCESS Validation of the CQU-DTU-LN1 series of airfoils To cite this article: W Z Shen et al 2014 J. Phys.: Conf. Ser. 555 012093 View the article online for
More informationIJESRT: 8(1), January, 2019 ISSN:
IJESRT: 8(1), January, 2019 ISSN: 2277-9655 International Journal of Engineering Sciences & Research Technology (A Peer Reviewed Online Journal) Impact Factor: 5.164 IJESRT Chief Editor Dr. J.B. Helonde
More informationSelf-noise of NACA 0012 and NACA 0021 airfoils at the onset of stall
Self-noise of NACA 12 and NACA 21 airfoils at the onset of stall Alex Laratro 1,*, Maziar Arjomandi 1, Benjamin Cazzolato 1, and Richard Kelso 1 1 School of Mechanical Engineering, The University of Adelaide,
More informationUnsteady Aerodynamics of Tandem Airfoils Pitching in Phase
Unsteady Aerodynamics of Tandem Airfoils Pitching in Phase Ravindra A Shirsath and Rinku Mukherjee Abstract This paper presents the results of a numerical simulation of unsteady, incompressible and viscous
More informationNUMERICAL INVESTIGATION FOR THE ENHANCEMENT OF THE AERODYNAMIC CHARACTERISTICS OF AN AEROFOIL BY USING A GURNEY FLAP
Geotec., Const. Mat. & Env., ISSN:2186-2990, Japan, DOI: http://dx.doi.org/10.21660/2017.34.2650 NUMERICAL INVESTIGATION FOR THE ENHANCEMENT OF THE AERODYNAMIC CHARACTERISTICS OF AN AEROFOIL BY USING A
More informationEffect of a single leading-edge protuberance on NACA airfoil performance
Effect of a single leading-edge protuberance on NACA 63 4-021 airfoil performance Chang Cai 1, Zhigang Zuo 1, Shuhong Liu 1 *, Yulin Wu 1, ISROMAC 2016 International Symposium on Transport Phenomena and
More information