Active Control of Flow Over an Oscillating NACA 0012 Airfoil
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Notes on Earth Atmospheric Entry for Mars Sample Return Missions
NASA/TP–2006-213486 Notes on Earth Atmospheric Entry for Mars Sample Return Missions Thomas Rivell Ames Research Center, Moffett Field, California September 2006 The NASA STI Program Office . in Profile Since its founding, NASA has been dedicated to the • CONFERENCE PUBLICATION. Collected advancement of aeronautics and space science. The papers from scientific and technical confer- NASA Scientific and Technical Information (STI) ences, symposia, seminars, or other meetings Program Office plays a key part in helping NASA sponsored or cosponsored by NASA. maintain this important role. • SPECIAL PUBLICATION. Scientific, technical, The NASA STI Program Office is operated by or historical information from NASA programs, Langley Research Center, the Lead Center for projects, and missions, often concerned with NASA’s scientific and technical information. The subjects having substantial public interest. NASA STI Program Office provides access to the NASA STI Database, the largest collection of • TECHNICAL TRANSLATION. English- aeronautical and space science STI in the world. language translations of foreign scientific and The Program Office is also NASA’s institutional technical material pertinent to NASA’s mission. mechanism for disseminating the results of its research and development activities. These results Specialized services that complement the STI are published by NASA in the NASA STI Report Program Office’s diverse offerings include creating Series, which includes the following report types: custom thesauri, building customized databases, organizing and publishing research results . even • TECHNICAL PUBLICATION. Reports of providing videos. completed research or a major significant phase of research that present the results of NASA For more information about the NASA STI programs and include extensive data or theoreti- Program Office, see the following: cal analysis. -
Technology for Pressure-Instrumented Thin Airfoil Models
NASA-CR-3891 19850015493 NASA Contractor Report 3891 i 1 Technology for Pressure-Instrumented Thin Airfoil Models David A. Wigley ., ..... " .... _' /, !..... .,L_. '' CONTRACT NAS1-17571 MAY 1985 ( • " " c _J ._._l._,.. ¸_ - j, ;_.. , r_ '._:i , _ . ; . ,. NIA NASA Contractor Report 3891 Technology for Pressure-Instrumented Thin Airfoil Models David A. Wigley Applied Cryogenics & Materials Consultants, Inc. New Castle, Delaware Prepared for Langley Research Center under Contract NAS1-17571 N//X National Aeronautics and Space Administration Scientific and Technical InformationBranch 1985 Use of trademarks or names of manufacturers in this report does not constitute an official endorsement of such products or manufacturers, either expressed or implied, by the National Aeronautics and Space Administration. FINAL REPORT ON PHASE 1 OF NASA CONTRACT NASI-17571 "TECHNOLOGY FOR PRESSURE-INSTRUMENTED THIN AIRFOIL MODELS" PROJECT SU_IARY The objective of Phase 1 of this research was to identify, then select and evaluate, the most appropriate combination of materials and fabrication techniques required to produce a Pressure Instrumented Thin Airfoil model for testing in a Cryogenic wind Tunnel ( PITACT ). Particular attention was to be given to proving the feasability and reliability of each sub-stage and ensuring that they could be combined together without compromising the quality of the resultant segment or model. In order to provide a sharp focus for this research, experimental samples were to be fabricated as if they were trailing edge segments of a 6% thick supercritical airfoil, number 0631X7, scaled to a 325mm (13in.) chord, the maximum likely to be tested in the 13in. x 13in. adaptive wall test section of the 0.3m Transonic Cryogenic Tunnel at NASA Langley Research Center. -
Aerodynamics of High-Performance Wing Sails
Aerodynamics of High-Performance Wing Sails J. otto Scherer^ Some of tfie primary requirements for tiie design of wing sails are discussed. In particular, ttie requirements for maximizing thrust when sailing to windward and tacking downwind are presented. The results of water channel tests on six sail section shapes are also presented. These test results Include the data for the double-slotted flapped wing sail designed by David Hubbard for A. F. Dl Mauro's lYRU "C" class catamaran Patient Lady II. Introduction The propulsion system is probably the single most neglect ed area of yacht design. The conventional triangular "soft" sails, while simple, practical, and traditional, are a long way from being aerodynamically desirable. The aerodynamic driving force of the sails is, of course, just as large and just as important as the hydrodynamic resistance of the hull. Yet, designers will go to great lengths to fair hull lines and tank test hull shapes, while simply drawing a triangle on the plans to define the sails. There is no question in my mind that the application of the wealth of available airfoil technology will yield enormous gains in yacht performance when applied to sail design. Re cent years have seen the application of some of this technolo gy in the form of wing sails on the lYRU "C" class catamar ans. In this paper, I will review some of the aerodynamic re quirements of yacht sails which have led to the development of the wing sails. For purposes of discussion, we can divide sail require ments into three points of sailing: • Upwind and close reaching. -
Introduction to Aerodynamics < 1.7. Dimensional Analysis > Physical
Introduction to Aerodynamics < 1.7. Dimensional analysis > Physical parameters Q: What physical quantities influence forces and moments? V A l Aerodynamics 2015 fall - 1 - Introduction to Aerodynamics < 1.7. Dimensional analysis > Physical parameters Physical quantities to be considered Parameter Symbol units Lift L' MLT-2 Angle of attack α - -1 Freestream velocity V∞ LT -3 Freestream density ρ∞ ML -1 -1 Freestream viscosity μ∞ ML T -1 Freestream speed of sound a∞ LT Size of body (e.g. chord) c L Generally, resultant aerodynamic force: R = f(ρ∞, V∞, c, μ∞, a∞) (1) Aerodynamics 2015 fall - 2 - Introduction to Aerodynamics < 1.7. Dimensional analysis > The Buckingham PI Theorem The relation with N physical variables f1 ( p1 , p2 , p3 , … , pN ) = 0 can be expressed as f 2( P1 , P2 , ... , PN-K ) = 0 where K is the No. of fundamental dimensions Then P1 =f3 ( p1 , p2 , … , pK , pK+1 ) P2 =f4 ( p1 , p2 , … , pK , pK+2 ) …. PN-K =f ( p1 , p2 , … , pK , pN ) Aerodynamics 2015 fall - 3 - < 1.7. Dimensional analysis > The Buckingham PI Theorem Example) Aerodynamics 2015 fall - 4 - < 1.7. Dimensional analysis > The Buckingham PI Theorem Example) Aerodynamics 2015 fall - 5 - < 1.7. Dimensional analysis > The Buckingham PI Theorem Aerodynamics 2015 fall - 6 - < 1.7. Dimensional analysis > The Buckingham PI Theorem Through similar procedure Aerodynamics 2015 fall - 7 - Introduction to Aerodynamics < 1.7. Dimensional analysis > Dimensionless form Aerodynamics 2015 fall - 8 - Introduction to Aerodynamics < 1.8. Flow similarity > Dynamic similarity Two different flows are dynamically similar if • Streamline patterns are similar • Velocity, pressure, temperature distributions are same • Force coefficients are same Criteria • Geometrically similar • Similarity parameters (Re, M) are same Aerodynamics 2015 fall - 9 - Introduction to Aerodynamics < 1.8. -
Aerodynamic Force Measurement on an Icing Airfoil
AerE 344: Undergraduate Aerodynamics and Propulsion Laboratory Lab Instructions Lab #13: Aerodynamic Force Measurement on an Icing Airfoil Instructor: Dr. Hui Hu Department of Aerospace Engineering Iowa State University Office: Room 2251, Howe Hall Tel:515-294-0094 Email:[email protected] Lab #13: Aerodynamic Force Measurement on an Icing Airfoil Objective: The objective of this lab is to measure the aerodynamic forces acting on an airfoil in a wind tunnel using a direct force balance. The forces will be measured on an airfoil before and after the accretion of ice to illustrate the effect of icing on the performance of aerodynamic bodies. The experiment components: The experiments will be performed in the ISU-UTAS Icing Research Tunnel, a closed-circuit refrigerated wind tunnel located in the Aerospace Engineering Department of Iowa State University. The tunnel has a test section with a 16 in 16 in cross section and all the walls of the test section optically transparent. The wind tunnel has a contraction section upstream the test section with a spray system that produces water droplets with the 10–100 um mean droplet diameters and water mass concentrations of 0–10 g/m3. The tunnel is refrigerated by a Vilter 340 system capable of achieving operating air temperatures below -20 C. The freestream velocity of the tunnel can set up to ~50 m/s. Figure 1 shows the calibration information for the tunnel, relating the freestream velocity to the motor frequency setting. Figure 1. Wind tunnel airspeed versus motor frequency setting. The airfoil model for the lab is a finite wing NACA 0012 with a chord length of 6 inches and a span of 14.5 inches. -
Development of Numerical Algorithm Based on a Modified Equation of Fluid Motion with Application to Turbomachinery Flow
Development of Numerical Algorithm Based on a Modified Equation of Fluid Motion with Application to Turbomachinery Flow Von der Fakultät für Ingenieurwissenschaften, Abteilung Maschinenbau der Universität Duisburg-Essen zur Erlangung des akademischen Grades DOKTOR-INGENIEUR genehmigte Dissertation von Bo Wan aus Jiangsu, China Referent: Prof. Dr.-Ing. F.-K. Benra Korreferent: Prof. Dr. S. H. Sohrab Tag der mündlichen Prüfung: 03. September 2012 Abstract On the basis of the scale-invariant theory of statistical mechanics, Sohrab introduced a linear equation termed the “modified equation of fluid motion.” Preliminary investigations have shown that this modified equation can be extended to solve flow problems. Analytical solutions of basic flow problems were derived using this equation. In all cases the match between estimated and experimental data was good. These results stimulated further applications of this modified equation in the development of a CFD code to obtain numerical solutions of turbomachinery flow problems. In the present work, a novel numerical algorithm based on the aforementioned modified equation has been developed to solve turbomachinery flow problems. In order to avoid dealing with more technical conditions on the scale–invariant form of the energy equation, this investigation is restricted to incompressible flow. On the basis of the work done by Sohrab, the derivation process of the modified equation for incompressible flow is presented with more emphasis on its linear property as compared to the Navier–Stokes equation for incompressible flow. Furthermore, a detailed analysis of the present discretisation technique for the modified equation is performed. As compared with the Navier–Stokes equation, the numerical errors resulted from the discretisation of the modified equation, including the truncation and discretisation errors are discussed as well as the stability conditions. -
Upwind Sail Aerodynamics : a RANS Numerical Investigation Validated with Wind Tunnel Pressure Measurements I.M Viola, Patrick Bot, M
Upwind sail aerodynamics : A RANS numerical investigation validated with wind tunnel pressure measurements I.M Viola, Patrick Bot, M. Riotte To cite this version: I.M Viola, Patrick Bot, M. Riotte. Upwind sail aerodynamics : A RANS numerical investigation validated with wind tunnel pressure measurements. International Journal of Heat and Fluid Flow, Elsevier, 2012, 39, pp.90-101. 10.1016/j.ijheatfluidflow.2012.10.004. hal-01071323 HAL Id: hal-01071323 https://hal.archives-ouvertes.fr/hal-01071323 Submitted on 8 Oct 2014 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. I.M. Viola, P. Bot, M. Riotte Upwind Sail Aerodynamics: a RANS numerical investigation validated with wind tunnel pressure measurements International Journal of Heat and Fluid Flow 39 (2013) 90–101 http://dx.doi.org/10.1016/j.ijheatfluidflow.2012.10.004 Keywords: sail aerodynamics, CFD, RANS, yacht, laminar separation bubble, viscous drag. Abstract The aerodynamics of a sailing yacht with different sail trims are presented, derived from simulations performed using Computational Fluid Dynamics. A Reynolds-averaged Navier- Stokes approach was used to model sixteen sail trims first tested in a wind tunnel, where the pressure distributions on the sails were measured. -
Chapter 1: Introduction
AIRFOIL OPTIMIZATION FOR MORPHING AIRCRAFT A Thesis Submitted to the Faculty of Purdue University by Howoong Namgoong In Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy December 2005 ii I dedicate this thesis to my father, Young Kyu Namgoong in heaven. iii ACKNOWLEDGMENTS Thanks to God for being my guidance of the journey of life. It has been a privilege to be a student of Drs. William A. Crossley and Anastasios S. Lyrintzis. I was able to open my eyes toward the world of design optimization and morphing aircraft with a tremendous help from Dr. Crossley. I learned great knowledge about aerodynamics and received precious advice from Dr. Lyrintzis. I will cherish and miss the moments that we met together for five years. Special thanks to my committee members, Dr. Scott D. King, Dr. Marc H. Williams and Dr. Terrence A. Weisshaar for their invaluable comments and lectures. I also thank to my colleagues and staffs in Purdue AAE department. This work was partially supported by the Air Force Research Laboratory, contract F33615-00-C-3051, and by a Purdue Research Foundation grant. I would like to share this great moment with my lovely wife, Miran who completes my life, and my beautiful son, Young who gives me another reason for living. I will not forget the support from my three sisters, Ran, Eun and Yoon and my brothers in law. I also like to thank my father and mother in law for their support and prayer. Lastly, my deep appreciation goes to my mother, Mal Soon Park who showed me the meaning of true love. -
Airfoil Services
Airfoil Services Airfoil Services has been jointly owned in equal shares by Lufthansa Technik and MTU Aero Engines since 2003. Part of Lufthansa Technik’s Engine Parts & Accessories Repair (EPAR) network, Airfoil Services specializes in the repair of blades from major aircraft engine manufacturers, including General Electric, CFM International and International Aero Engines. Service spectrum Located in Kota Damansara in Malaysia’s state of Selangor, Airfoil Services merges the leading-edge competencies of both parent companies. Airfoil Services is specializing in the repair of engine airfoils for low-pressure turbines and high-pressure compressors of CF6-50, CF6-80, CF34 engines as well as the CFM56 engine family Ȝ Kuala Lumpur and the V2500. The ultra-modern facility is equipped with state-of-the- art machinery and has installed the most advanced repair techniques such as the Advanced Recontouring Process (ARP), also offering special repair methods such as aluminide bronze coating and high velocity oxygen fuel spraying (HVOF). Organized according to the philosophy of lean production, the repairs follow the flow line principle. Key facts Customers benefit from optimized processes and very competitive turnaround times offered at cost-conscious conditions. At the same Founded 1991 time, the quality of work reflects the high standards of the two German Personnel 420 joint venture partners. Capacity 6,000 m2 In focus: Advanced Recontouring Process (ARP) The Advanced Recontouring Process (ARP) is unique worldwide. Worn compressor blades are first electronically analyzed and then re-contoured in a precision method using robot technology. The restored profile of the engine compressor blades is calculated as a factor of the reduced chord-length of the worn blades so that the best possible aerodynamic profile is obtained. -
SSA Phase II Final Report.Book
Solid State Aircraft Phase II Project NAS5-03110 Final Report Prepared for: Robert A. Cassanova, Director NASA Institute for Advanced Concepts May 31, 2005 Table of Contents Table of Contents List of Tables .............................................................................................................. iii List of Figures ............................................................................................................. v List of Contributors .................................................................................................. xv Executive Summary ................................................................................................ xvii Chapter 1.0 Introduction ............................................................................................ 1 1.1 SSA Concept Description ..........................................................................................................1 1.2 Flapping Wing Flight ..................................................................................................................4 1.2.1 Insect Flight .........................................................................................................................5 1.2.2 Bird, Mammal and Dinosaur Flight ......................................................................................8 1.2.3 Wing Shape .......................................................................................................................12 1.3 Mission Capabilities .................................................................................................................15 -
List of Symbols
List of Symbols a atmosphere speed of sound a exponent in approximate thrust formula ac aerodynamic center a acceleration vector a0 airfoil angle of attack for zero lift A aspect ratio A system matrix A aerodynamic force vector b span b exponent in approximate SFC formula c chord cd airfoil drag coefficient cl airfoil lift coefficient clα airfoil lift curve slope cmac airfoil pitching moment about the aerodynamic center cr root chord ct tip chord c¯ mean aerodynamic chord C specfic fuel consumption Cc corrected specfic fuel consumption CD drag coefficient CDf friction drag coefficient CDi induced drag coefficient CDw wave drag coefficient CD0 zero-lift drag coefficient Cf skin friction coefficient CF compressibility factor CL lift coefficient CLα lift curve slope CLmax maximum lift coefficient Cmac pitching moment about the aerodynamic center CT nondimensional thrust T Cm nondimensional thrust moment CW nondimensional weight d diameter det determinant D drag e Oswald’s efficiency factor E origin of ground axes system E aerodynamic efficiency or lift to drag ratio EO position vector f flap f factor f equivalent parasite area F distance factor FS stick force F force vector F F form factor g acceleration of gravity g acceleration of gravity vector gs acceleration of gravity at sea level g1 function in Mach number for drag divergence g2 function in Mach number for drag divergence H elevator hinge moment G time factor G elevator gearing h altitude above sea level ht altitude of the tropopause hH height of HT ac above wingc ¯ h˙ rate of climb 2 i unit vector iH horizontal -
Aerodynamic Influence Coefficient Comptuations Using Euler Navier
AIAA JOURNAL Vol. 37, No. 11, November 1999 Aerodynamic Influence Coefficient Computations Using Euler/Navier-Stokes Equations on Parallel Computers Chansup Byun,* Mehrdad Farhangnia, Gurd an Guruswamy. fu P * NASA Ames Research Center, Moffett Field, California 94035-1000 efficienn A t procedur computo et e aerodynamic influence coefficients (AICs), using high-fidelity flow equations suc Euler/Navier-Stokes ha s equations presenteds ,i AICe computee .Th sar perturbiny db g structures using mode shapes. The procedure is developed on a multiple-instruction, multiple-data parallel computer. In addition to discipline parallelizatio coarse-graid nan n parallelizatio floe th w f ndomaino , embarrassingly parallel implemen- tation of ENSAERO code demonstrates linear speedup for a large number of processors. Demonstration of the AIC computatio statir nfo c aeroelasticity analysi arromads sn i a n weo wing-body configuration. Validatioe th f no current procedure is made on a straight wing with arc-airfoil at a subsonic region. The present flutter speed and frequency of the wing show excellent agreement with those results obtained by experiment and NASTRAN. The demonstrated linear scalability for multiple concurrent analyses shows that the three-level parallelism in the code is well suited for the computation of the AICs. Introduction transonic flows over fighter wings undergoing unsteady motions at ODERN design requirement aircrafr sfo t push current tech- small to moderately large angles of attack.3'5 The code has been M nologie sdesige useth n di n proces theio t s r limit somer so - extended to simulate unsteady flows over rigid wing and wing-body times require more advanced technologie meeo st requirementse tth .