Aerodynamics of 3D Lifting Surfaces Through Vortex Lattice Methods
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The Vortex Lattice Method . for the Rotor-Vortex Interaction Problem
NASA CONTRACTOR NASA CR-2421 REPORT - THE VORTEX LATTICE METHOD . FOR THE ROTOR-VORTEX INTERACTION PROBLEM by Raghuveera Padakannaya Prepared by THE PENNSYL VANIA ST ATE UNIVERSITY University Park, Pa. 16802 for Langley Research Center NATIONAL AERONAUTICS AND SPACE ADMINISTRATION • WASHINGTON, D. C. • JULY 1974 1. Report No. , I 2. Government Accession No. 3. Recipient's Catalog No. CR-Z4Z1 4. TItle and Subtitle 5. Report Date THE VORTEX LATTICE METHOD FOR THE ROTOR-VORTEX JULY 1974 INTERACTION PROBLEM 6. Performing Organization Code 7. Author(s) 8. Performing Organization Report No. Raghuveera Padakannaya 1-------------------------------1 10. Work Unit No. g. Performing Organization Name and Address The Pennsylvania State University 11. Contract or Grant No. University Park, PA 16802 NGR - 39 - 009 - 111 ~------------------------------I13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Contractor Report National Aeronautics and Space Administration 14. Sponsoring Agency Code Washington, D.C. 20546 15. Supplementary Notes Topical report 16. Abstract This study is concerned with the rotor blade-vortex interaction problem and the resulting impul sive airloads which generate undesirable noi se level s. A numerical 1ifting surface method to predict unsteady aerodynamic forces induced on a finite aspect ratio rectangular wing by a straight, free vortex placed at an arbitrary angle in a subsonic incompressible free stream is developed first. Using a rigid wake assumption, the wake vortices are assumed to move down steam with the free steam velocity. Unsteady load.distributions are obtained which compare favorably with the results of planar lifting surface theory. The vortex lattice method has been extended to a single bladed rotor operating at high advance 'ratios aodeocc)untering a ft:eevottex from afixed.wing upstream of the rotor. -
Aerodyn Theory Manual
January 2005 • NREL/TP-500-36881 AeroDyn Theory Manual P.J. Moriarty National Renewable Energy Laboratory Golden, Colorado A.C. Hansen Windward Engineering Salt Lake City, Utah National Renewable Energy Laboratory 1617 Cole Boulevard, Golden, Colorado 80401-3393 303-275-3000 • www.nrel.gov Operated for the U.S. Department of Energy Office of Energy Efficiency and Renewable Energy by Midwest Research Institute • Battelle Contract No. DE-AC36-99-GO10337 January 2005 • NREL/TP-500-36881 AeroDyn Theory Manual P.J. Moriarty National Renewable Energy Laboratory Golden, Colorado A.C. Hansen Windward Engineering Salt Lake City, Utah Prepared under Task No. WER4.3101 and WER5.3101 National Renewable Energy Laboratory 1617 Cole Boulevard, Golden, Colorado 80401-3393 303-275-3000 • www.nrel.gov Operated for the U.S. Department of Energy Office of Energy Efficiency and Renewable Energy by Midwest Research Institute • Battelle Contract No. DE-AC36-99-GO10337 NOTICE This report was prepared as an account of work sponsored by an agency of the United States government. Neither the United States government nor any agency thereof, nor any of their employees, makes any warranty, express or implied, or assumes any legal liability or responsibility for the accuracy, completeness, or usefulness of any information, apparatus, product, or process disclosed, or represents that its use would not infringe privately owned rights. Reference herein to any specific commercial product, process, or service by trade name, trademark, manufacturer, or otherwise does not necessarily constitute or imply its endorsement, recommendation, or favoring by the United States government or any agency thereof. The views and opinions of authors expressed herein do not necessarily state or reflect those of the United States government or any agency thereof. -
6.2 Understanding Flight
6.2 - Understanding Flight Grade 6 Activity Plan Reviews and Updates 6.2 Understanding Flight Objectives: 1. To understand Bernoulli’s Principle 2. To explain drag and how different shapes influence it 3. To describe how the results of similar and repeated investigations testing drag may vary and suggest possible explanations for variations. 4. To demonstrate methods for altering drag in flying devices. Keywords/concepts: Bernoulli’s Principle, pressure, lift, drag, angle of attack, average, resistance, aerodynamics Curriculum outcomes: 107-9, 204-7, 205-5, 206-6, 301-17, 301-18, 303-32, 303-33. Take-home product: Paper airplane, hoop glider Segment Details African Proverb and Cultural “The bird flies, but always returns to Earth.” Gambia Relevance (5min.) Have any of you ever been on an airplane? Have you ever wondered how such a heavy aircraft can fly? Introduce Bernoulli’s Principle and drag. Pre-test Show this video on Bernoulli’s Principle: (10 min.) https://www.youtube.com/watch?v=bv3m57u6ViE Note: To gain the speed so lift can be created the plane has to overcome the force of drag; they also have to overcome this force constantly in flight. Therefore, planes have been designed to reduce drag Demo 1 Use the students to demonstrate the basic properties of (10 min.) Bernoulli’s Principle. Activity 2 Students use paper airplanes to alter drag and hypothesize why (30 min.) different planes performed differently Activity 3 Students make a hoop glider to understand the effects of drag (20 min.) on different shaped objects. Post-test Word scramble. (5 min.) https://www.amazon.com/PowerUp-Smartphone-Controlled- Additional idea Paper-Airplane/dp/B00N8GWZ4M Suggested Interpretation of Proverb What comes up must come down Background Information Bernoulli’s Principle Daniel Bernoulli, an eighteenth-century Swiss scientist, discovered that as the velocity of a fluid increases, its pressure decreases. -
Aerodynamics and Fluid Mechanics
Aerodynamics and Fluid Mechanics Numerical modeling, simulation and experimental analysis of fluids and fluid flows n Jointly with Oerlikon AM GmbH and Linde, the Chair of Aerodynamics and Fluid Mechanics investigates novel manufacturing processes and materials for additive 3D printing. The cooperation is supported by the Bavarian State Ministry for Economic Affairs, Regional Development and Energy. In addition, two new H2020-MSCA-ITN actions are being sponsored by the European Union. The ‘UCOM’ project investigates ultrasound cavitation and shock-tissue interaction, which aims at closing the gap between medical science and compressible fluid mechanics for fluid-mechanical destruction of cancer tissue. With ‘EDEM’, novel technologies for optimizing combustion processes using alternative fuels for large-ship combustion engines are developed. In 2019, the NANOSHOCK research group published A highlight in the field of aircraft aerodynamics in 2019 various articles in the highly-ranked journals ‘Journal of was to contribute establishing a DFG research group Computational Physics’, ‘Physical Review Fluids’ and (FOR2895) on the topic ‘Research on unsteady phenom- ‘Computers and Fluids’. Updates on the NANOSHOCK ena and interactions at high speed stall’. Our subproject open-source code development and research results are will focus on ‘Neuro-fuzzy based ROM methods for load available for the scientific community: www.nanoshock.de calculations and analysis at high speed buffet’. or hwww.aer.mw.tum.de/abteilungen/nanoshock/news. Aircraft and Helicopter Aerodynamics Motivation and Objectives The long-term research agenda is dedi- cated to the continues improvement of flow simulation and analysis capa- bilities enhancing the efficiency of aircraft and helicopter configura- tions with respect to the Flightpath 2050 objectives. -
Vorticity and Vortex Dynamics
Vorticity and Vortex Dynamics J.-Z. Wu H.-Y. Ma M.-D. Zhou Vorticity and Vortex Dynamics With291 Figures 123 Professor Jie-Zhi Wu State Key Laboratory for Turbulence and Complex System, Peking University Beijing 100871, China University of Tennessee Space Institute Tullahoma, TN 37388, USA Professor Hui-Yang Ma Graduate University of The Chinese Academy of Sciences Beijing 100049, China Professor Ming-De Zhou TheUniversityofArizona,Tucson,AZ85721,USA State Key Laboratory for Turbulence and Complex System, Peking University Beijing, 100871, China Nanjing University of Aeronautics and Astronautics Nanjing, 210016, China LibraryofCongressControlNumber:2005938844 ISBN-10 3-540-29027-3 Springer Berlin Heidelberg New York ISBN-13 978-3-540-29027-8 Springer Berlin Heidelberg New York This work is subject to copyright. All rights are reserved, whether the whole or part of the material is concerned, specifically the rights of translation, reprinting, reuse of illustrations, recitation, broad- casting, reproduction on microfilm or in any other way, and storage in data banks. Duplication of this publication or parts thereof is permitted only under the provisions of the German Copyright Law of September 9, 1965, in its current version, and permission for use must always be obtained from Springer. Violations are liable to prosecution under the German Copyright Law. Springer is a part of Springer Science+Business Media. springer.com © Springer-Verlag Berlin Heidelberg 2006 Printed in Germany The use of general descriptive names, registered names, trademarks, etc. in this publication does not imply, even in the absence of a specific statement, that such names are exempt from the relevant pro- tective laws and regulations and therefore free for general use. -
Basic Aerodynamics
Category B1/B2 according Part-66 Appendix 1 Module 8 Basic Aerodynamics Part 66 Cat. B1 / B2 Module 8 BASIC AERODYNAMICS Vilnius-2017 Issue 1. Effective date 2017-07-28 FOR TRAINING PURPOSES ONLY Page 1 of 74 Category B1/B2 according Part-66 Appendix 1 Module 8 Basic Aerodynamics Table of Contents Part-66 Module 8. Basic Aerodynamics (Cat. B1 and B2) Syllabus ................................................................ 7 Part-66: Appendix I - Basic Knowledge Requirements ................................................................................... 8 8.1 Physics of the Atmosphere ........................................................................................................................... 9 Atmosphere and Basic Aerodynamics ............................................................................................................ 9 Temperature, Pressure and Altitude .............................................................................................................. 9 Density .......................................................................................................................................................... 12 Humidity ....................................................................................................................................................... 12 Absolute Humidity .................................................................................................................................... 13 Relative Humidity and the Dew Point ..................................................................................................... -
Vortex-Lattice Utilization
NASA SP-405 VORTEX-LATTICE UTILIZATION (NRSA-5P-405) V3BTZX- LATTIZZ UTILIZF.TION N76-28163 (?iASA) 409 p HC 611.Ci0 CSCL 31A THRU N76-28186 rn Unclas .- H1/02 47615 A workshop held at LANGLEY RESEARCH CENTER Hampton, Virginia May 17-18, 1976 I NATIONAL AERONAUTICS AND SPAC ERRATA NASA SP-405 VORTEX-LATTICE UTILIZATION Page 231: Figure 6 is in error. Replace figure 6 with the following corrected version. Figure 6.- Span load and section suction distributions on a swept and skewed wing. h = 45O; A = 1; M = 0. NASA SP-405 VORTEX-LATTICE UTILIZATION A workshop held at Langley Research Center, Hampton, Virginia, on May 17-18, 1976 Prepared by Lungley Research Center Srietrlifir and Terhnirnl lrlformdtion Ofice !9'h u 5. b. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Washington, D.C. CONTENTS PREFACE ..................................iii o)tl/7- . 1. HISTORICAL EVOLUTION OF VORTEX-LATTICE METHODS ............ 1 j. John DeYoung, Vought Corporation Hampton Technical Center - SESSION I - CONFIGURATION DESIGN AND ANALYSIS AND WALL EFFECTS Chairman: Percy J. Bobbitt, NASA Langley Research Center A. WING-BODY COMBINATIONS 2. SUBSONIC FINITC ELEMENTS FOR WING-BODY COMBINATIONS ......... 11 James L. Thomas, NASA Langley Research Center 3. EXTENDED APPLICATIONS OF THE VORTEX LATTICE METHOD ......... 27 Luis R. Miranda, Lockheed-California Company B. NONPLANAR CONFIGURATIONS 4. WMERICAL METHOD TO CALCULATE THE INDUCED DRAG OR OPTIMUM LOADING FOR ARBITRARY NON-PLANAR AIRCRAFT ................. 49 James A. Blackwell, Jr., Lockheed-Georgia Company 5. OPTIMIZATION AND DESIGN OF THREE-DIMEKSIONAL AERODYNAMIC CONFIGURATIONS OF ARBITRARY SHAPE BY A VORTEX LATTICE METHOD .............................. 71 Wlnfried M. Feifel, The Boeing Company 6. -
Low-Speed Aerodynamics, Second Edition
P1: JSN/FIO P2: JSN/UKS QC: JSN/UKS T1: JSN CB329-FM CB329/Katz October 3, 2000 15:18 Char Count= 0 Low-Speed Aerodynamics, Second Edition Low-speed aerodynamics is important in the design and operation of aircraft fly- ing at low Mach number and of ground and marine vehicles. This book offers a modern treatment of the subject, both the theory of inviscid, incompressible, and irrotational aerodynamics and the computational techniques now available to solve complex problems. A unique feature of the text is that the computational approach (from a single vortex element to a three-dimensional panel formulation) is interwoven throughout. Thus, the reader can learn about classical methods of the past, while also learning how to use numerical methods to solve real-world aerodynamic problems. This second edition, updates the first edition with a new chapter on the laminar boundary layer, the latest versions of computational techniques, and additional coverage of interaction problems. It includes a systematic treatment of two-dimensional panel methods and a detailed presentation of computational techniques for three- dimensional and unsteady flows. With extensive illustrations and examples, this book will be useful for senior and beginning graduate-level courses, as well as a helpful reference tool for practicing engineers. Joseph Katz is Professor of Aerospace Engineering and Engineering Mechanics at San Diego State University. Allen Plotkin is Professor of Aerospace Engineering and Engineering Mechanics at San Diego State University. i P1: JSN/FIO P2: JSN/UKS QC: JSN/UKS T1: JSN CB329-FM CB329/Katz October 3, 2000 15:18 Char Count= 0 ii P1: JSN/FIO P2: JSN/UKS QC: JSN/UKS T1: JSN CB329-FM CB329/Katz October 3, 2000 15:18 Char Count= 0 Cambridge Aerospace Series Editors: MICHAEL J. -
Explanation and Discovery in Aerodynamics
Explanation and discovery in aerodynamics Gordon McCabe December 22, 2005 Abstract The purpose of this paper is to discuss and clarify the explanations commonly cited for the aerodynamic lift generated by a wing, and to then analyse, as a case study of engineering discovery, the aerodynamic revolutions which have taken place within Formula 1 in the past 40 years. The paper begins with an introduction that provides a succinct summary of the mathematics of fluid mechanics. 1 Introduction Aerodynamics is the branch of fluid mechanics which represents air flows and the forces experienced by a solid body in motion with respect to an air mass. In most applications of aerodynamics, Newtonian fluid mechanics is considered to be empirically adequate, and, accordingly, a body of air is considered to satisfy either the Euler equations or the Navier-Stokes equations of Newtonian fluid mechanics. Let us therefore begin with a succinct exposition of these equations and the mathematical concepts of fluid mechanics. The Euler equations are used to represent a so-called `perfect' fluid, a fluid which is idealised to be free from internal friction, and which does not experience friction at the boundaries which are de¯ned for it by solid bodies.1 A perfect Newtonian fluid is considered to occupy a region of Newtonian space ½ R3, and its behaviour is characterised by a time-dependent velocity vector ¯eld Ut, a time-dependent pressure scalar ¯eld pt, and a time-dependent mass density scalar ¯eld ½t. The internal forces in any continuous medium, elastic or fluid, are represented by a symmetric contravariant 2nd-rank tensor ¯eld σ, called the Cauchy stress tensor, and a perfect fluid is one for which the Cauchy stress tensor has the form σ = ¡pg, where g is the metric tensor representing the spatial geometry. -
MC-F-002.Rotor Aerodynamics. Momentum Theory
Miguel A. Barcala Montejano Ángel A. Rodríguez Sevillano 1 HELICOPTERS Professors: Miguel A. Barcala Montejano Ángel A. Rodríguez Sevillano ROTOR AERODYNAMICS Momentum Theory Vertial Climb Inital thoughts: Vertical climb flight is the easiest flight condition. The velocities in the rotor plane are symmetrical about the rotation axis. The aerodynamic forces on the blades are constant regardless of their angular position. The plane formed by the blade rotor tips is perpendicular to the drive shaft. MT. VERTICAL CLIMBING FLIGHT Miguel A. Barcala Montejano Ángel A. Rodríguez Sevillano 4 Inital thoughts: Vertical climbing flight is the easiest flight condition. There are different theories for studying rotor aerodynamics. The momentum theory. The blade element theory. The vortex theory. Miguel A. Barcala Montejano MT. VERTICAL CLIMBING FLIGHT Ángel A. Rodríguez Sevillano 5 ROTOR AERODYNAMICS VERTICAL CLIMBING FLIGHT MOMENTUM THEORY Thrust and Power Calculations. Hover flight. Velocity and Power ratios. Thurst and Power coefficients. Dimensionless expressions. Miguel A. Barcala Montejano MT. VERTICAL CLIMBING FLIGHT Ángel A. Rodríguez Sevillano 6 MOMENTUM THEORY INITIAL ASSUMPTIONS High values of Re number flow. Replace the original rotor with blades that rotate for a totally porous disc of the same radius (R) as the rotor replaced . We assume the affected flow through the disc is defined by the streamtube. The fluid flow in the streamtube is considered to be unidimensional, steady and incompressible. The effects of the rotation of the slipstream and loses in the blade tips, are negleted. Miguel A. Barcala Montejano MT. VERTICAL CLIMBING FLIGHT Ángel A. Rodríguez Sevillano 7 MOMENTUM THEORY MATHEMATICAL MODEL Vv The velocity of the upstream rotor fluid is the vertical velocity of the rotor. -
Aerodynamics and Flight Dynamics
Aerodynamics The shuttle vehicle was uniquely winged so it could reenter Earth’s atmosphere and fly to assigned nominal or abort landing strips. and Flight The wings allowed the spacecraft to glide and bank like an airplane Dynamics during much of the return flight phase. This versatility, however, did not come without cost. The combined ascent and re-entry capabilities required a major government investment in new design, development, Introduction verification facilities, and analytical tools. The aerodynamic and Aldo Bordano flight control engineering disciplines needed new aerodynamic and Aeroscience Challenges Gerald LeBeau aerothermodynamic physical and analytical models. The shuttle required Pieter Buning new adaptive guidance and flight control techniques during ascent and Peter Gnoffo re-entry. Engineers developed and verified complex analysis simulations Paul Romere that could predict flight environments and vehicle interactions. Reynaldo Gomez Forrest Lumpkin The shuttle design architectures were unprecedented and a significant Fred Martin challenge to government laboratories, academic centers, and the Benjamin Kirk aerospace industry. These new technologies, facilities, and tools would Steve Brown Darby Vicker also become a necessary foundation for all post-shuttle spacecraft Ascent Flight Design developments. The following section describes a US legacy unmatched Aldo Bordano in capability and its contribution to future spaceflight endeavors. Lee Bryant Richard Ulrich Richard Rohan Re-entry Flight Design Michael Tigges Richard Rohan Boundary Layer Transition Charles Campbell Thomas Horvath 226 Engineering Innovations Aeroscience Challenges One of the first challenges in the development of the Space Shuttle was its aerodynamic design, which had to satisfy the conflicting requirements of a spacecraft-like re-entry into the Earth’s atmosphere where blunt objects have certain advantages, but it needed wings that would allow it to achieve an aircraft-like runway landing. -
Handout-3 Aerodynamics: Aerodynamics Is the Study of The
Handout-3 Review of Fluid Mechanics Terminology Aerodynamics: Aerodynamics is the study of the flow of gases. Aerodynamics: The dynamics of bodies moving relative to gases, especially the interaction of moving objects with the atmosphere. Because the principal application of aerodynamics is the design of airplanes, air is the principal gas with which this science is concerned. Bernoulli's principle, which states that the pressure of a moving gas decreases as its velocity increases, has been used to explain the lift produced by a wing having a curved upper surface and a flat lower surface. Because the flow is faster across the curved surface than across the flat one, a greater pressure is exerted in the upward direction. Aerodynamics is also concerned with the drag caused by air friction, which is reduced by making the surface area of the craft as small as possible. At speeds close to the speed of sound, or Mach 1, there is also a large, sudden increase of drag, which has been called the sonic, or sound, barrier. Aerodynamics is also used in designing automobile bodies and trains for minimum drag and in computing wind stresses on bridges, buildings, and the like. The wind tunnel is one of the basic experimental tools of the aerodynamicist. Aeronautics: Aeronautics is the mathematics and mechanics of flying objects, in particular airplanes. Aeronautics: The design and construction of aircraft. The theory and practice of aircraft navigation. Aerothermodynamics: The study of the thermodynamics of gases, especially at high relative velocities. Bernoulli's equation: A statement of the conservation of energy in a form useful for solving problems involving fluids.