Physics and Model Rockets a Teacher’S Guide and Curriculum for Grades 8-11
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Glossary Physics (I-Introduction)
1 Glossary Physics (I-introduction) - Efficiency: The percent of the work put into a machine that is converted into useful work output; = work done / energy used [-]. = eta In machines: The work output of any machine cannot exceed the work input (<=100%); in an ideal machine, where no energy is transformed into heat: work(input) = work(output), =100%. Energy: The property of a system that enables it to do work. Conservation o. E.: Energy cannot be created or destroyed; it may be transformed from one form into another, but the total amount of energy never changes. Equilibrium: The state of an object when not acted upon by a net force or net torque; an object in equilibrium may be at rest or moving at uniform velocity - not accelerating. Mechanical E.: The state of an object or system of objects for which any impressed forces cancels to zero and no acceleration occurs. Dynamic E.: Object is moving without experiencing acceleration. Static E.: Object is at rest.F Force: The influence that can cause an object to be accelerated or retarded; is always in the direction of the net force, hence a vector quantity; the four elementary forces are: Electromagnetic F.: Is an attraction or repulsion G, gravit. const.6.672E-11[Nm2/kg2] between electric charges: d, distance [m] 2 2 2 2 F = 1/(40) (q1q2/d ) [(CC/m )(Nm /C )] = [N] m,M, mass [kg] Gravitational F.: Is a mutual attraction between all masses: q, charge [As] [C] 2 2 2 2 F = GmM/d [Nm /kg kg 1/m ] = [N] 0, dielectric constant Strong F.: (nuclear force) Acts within the nuclei of atoms: 8.854E-12 [C2/Nm2] [F/m] 2 2 2 2 2 F = 1/(40) (e /d ) [(CC/m )(Nm /C )] = [N] , 3.14 [-] Weak F.: Manifests itself in special reactions among elementary e, 1.60210 E-19 [As] [C] particles, such as the reaction that occur in radioactive decay. -
Drag Force Calculation
DRAG FORCE CALCULATION “Drag is the component of force on a body acting parallel to the direction of relative motion.” [1] This can occur between two differing fluids or between a fluid and a solid. In this lab, the drag force will be explored between a fluid, air, and a solid shape. Drag force is a function of shape geometry, velocity of the moving fluid over a stationary shape, and the fluid properties density and viscosity. It can be calculated using the following equation, ퟏ 푭 = 흆푨푪 푽ퟐ 푫 ퟐ 푫 Equation 1: Drag force equation using total profile where ρ is density determined from Table A.9 or A.10 in your textbook A is the frontal area of the submerged object CD is the drag coefficient determined from Table 1 V is the free-stream velocity measured during the lab Table 1: Known drag coefficients for various shapes Body Status Shape CD Square Rod Sharp Corner 2.2 Circular Rod 0.3 Concave Face 1.2 Semicircular Rod Flat Face 1.7 The drag force of an object can also be calculated by applying the conservation of momentum equation for your stationary object. 휕 퐹⃗ = ∫ 푉⃗⃗ 휌푑∀ + ∫ 푉⃗⃗휌푉⃗⃗ ∙ 푑퐴⃗ 휕푡 퐶푉 퐶푆 Assuming steady flow, the equation reduces to 퐹⃗ = ∫ 푉⃗⃗휌푉⃗⃗ ∙ 푑퐴⃗ 퐶푆 The following frontal view of the duct is shown below. Integrating the velocity profile after the shape will allow calculation of drag force per unit span. Figure 1: Velocity profile after an inserted shape. Combining the previous equation with Figure 1, the following equation is obtained: 푊 퐷푓 = ∫ 휌푈푖(푈∞ − 푈푖)퐿푑푦 0 Simplifying the equation, you get: 20 퐷푓 = 휌퐿 ∑ 푈푖(푈∞ − 푈푖)훥푦 푖=1 Equation 2: Drag force equation using wake profile The pressure measurements can be converted into velocity using the Bernoulli’s equation as follows: 2Δ푃푖 푈푖 = √ 휌퐴푖푟 Be sure to remember that the manometers used are in W.C. -
Chapter 4: Immersed Body Flow [Pp
MECH 3492 Fluid Mechanics and Applications Univ. of Manitoba Fall Term, 2017 Chapter 4: Immersed Body Flow [pp. 445-459 (8e), or 374-386 (9e)] Dr. Bing-Chen Wang Dept. of Mechanical Engineering Univ. of Manitoba, Winnipeg, MB, R3T 5V6 When a viscous fluid flow passes a solid body (fully-immersed in the fluid), the body experiences a net force, F, which can be decomposed into two components: a drag force F , which is parallel to the flow direction, and • D a lift force F , which is perpendicular to the flow direction. • L The drag coefficient CD and lift coefficient CL are defined as follows: FD FL CD = 1 2 and CL = 1 2 , (112) 2 ρU A 2 ρU Ap respectively. Here, U is the free-stream velocity, A is the “wetted area” (total surface area in contact with fluid), and Ap is the “planform area” (maximum projected area of an object such as a wing). In the remainder of this section, we focus our attention on the drag forces. As discussed previously, there are two types of drag forces acting on a solid body immersed in a viscous flow: friction drag (also called “viscous drag”), due to the wall friction shear stress exerted on the • surface of a solid body; pressure drag (also called “form drag”), due to the difference in the pressure exerted on the front • and rear surfaces of a solid body. The friction drag and pressure drag on a finite immersed body are defined as FD,vis = τwdA and FD, pres = pdA , (113) ZA ZA Streamwise component respectively. -
UNIT – 4 FORCES on IMMERSED BODIES Lecture-01
1 UNIT – 4 FORCES ON IMMERSED BODIES Lecture-01 Forces on immersed bodies When a body is immersed in a real fluid, which is flowing at a uniform velocity U, the fluid will exert a force on the body. The total force (FR) can be resolved in two components: 1. Drag (FD): Component of the total force in the direction of motion of fluid. 2. Lift (FL): Component of the total force in the perpendicular direction of the motion of fluid. It occurs only when the axis of the body is inclined to the direction of fluid flow. If the axis of the body is parallel to the fluid flow, lift force will be zero. Expression for Drag & Lift Forces acting on the small elemental area dA are: i. Pressure force acting perpendicular to the surface i.e. p dA ii. Shear force acting along the tangential direction to the surface i.e. τ0dA (a) Drag force (FD) : Drag force on elemental area = p dAcosθ + τ0 dAcos(90 – θ = p dAosθ + τ0dAsinθ Hence Total drag (or profile drag) is given by, Where �� = ∫ � cos � �� + ∫�0 sin � �� = pressure drag or form drag, and ∫ � cos � �� = shear drag or friction drag or skin drag (b) Lift0 force (F ) : ∫ � sin � ��L Lift force on the elemental area = − p dAsinθ + τ0 dA sin(90 – θ = − p dAsiθ + τ0dAcosθ Hence, total lift is given by http://www.rgpvonline.com �� = ∫�0 cos � �� − ∫ p sin � �� 2 The drag & lift for a body moving in a fluid of density at a uniform velocity U are calculated mathematically as 2 � And �� = � � � 2 � Where A = projected area of the body or�� largest= � project� � area of the immersed body. -
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. -
Chapter 4: Immersed Body Flow [Pp
MECH 3492 Fluid Mechanics and Applications Univ. of Manitoba Fall Term, 2017 Chapter 4: Immersed Body Flow [pp. 445-459 (8e), or 374-386 (9e)] Dr. Bing-Chen Wang Dept. of Mechanical Engineering Univ. of Manitoba, Winnipeg, MB, R3T 5V6 When a viscous fluid flow passes a solid body (fully-immersed in the fluid), the body experiences a net force, F, which can be decomposed into two components: a drag force F , which is parallel to the flow direction, and • D a lift force F , which is perpendicular to the flow direction. • L The drag coefficient CD and lift coefficient CL are defined as follows: FD FL CD = 1 2 and CL = 1 2 , (112) 2 ρU A 2 ρU Ap respectively. Here, U is the free-stream velocity, A is the “wetted area” (total surface area in contact with fluid), and Ap is the “planform area” (maximum projected area of an object such as a wing). In the remainder of this section, we focus our attention on the drag forces. As discussed previously, there are two types of drag forces acting on a solid body immersed in a viscous flow: friction drag (also called “viscous drag”), due to the wall friction shear stress exerted on the • surface of a solid body; pressure drag (also called “form drag”), due to the difference in the pressure exerted on the front • and rear surfaces of a solid body. The friction drag and pressure drag on a finite immersed body are defined as FD,vis = τwdA and FD, pres = pdA , (113) ZA ZA Streamwise component respectively. -
Hydraulics Manual Glossary G - 3
Glossary G - 1 GLOSSARY OF HIGHWAY-RELATED DRAINAGE TERMS (Reprinted from the 1999 edition of the American Association of State Highway and Transportation Officials Model Drainage Manual) G.1 Introduction This Glossary is divided into three parts: · Introduction, · Glossary, and · References. It is not intended that all the terms in this Glossary be rigorously accurate or complete. Realistically, this is impossible. Depending on the circumstance, a particular term may have several meanings; this can never change. The primary purpose of this Glossary is to define the terms found in the Highway Drainage Guidelines and Model Drainage Manual in a manner that makes them easier to interpret and understand. A lesser purpose is to provide a compendium of terms that will be useful for both the novice as well as the more experienced hydraulics engineer. This Glossary may also help those who are unfamiliar with highway drainage design to become more understanding and appreciative of this complex science as well as facilitate communication between the highway hydraulics engineer and others. Where readily available, the source of a definition has been referenced. For clarity or format purposes, cited definitions may have some additional verbiage contained in double brackets [ ]. Conversely, three “dots” (...) are used to indicate where some parts of a cited definition were eliminated. Also, as might be expected, different sources were found to use different hyphenation and terminology practices for the same words. Insignificant changes in this regard were made to some cited references and elsewhere to gain uniformity for the terms contained in this Glossary: as an example, “groundwater” vice “ground-water” or “ground water,” and “cross section area” vice “cross-sectional area.” Cited definitions were taken primarily from two sources: W.B. -
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 ..................................................................................................... -
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