AN1573, Understanding Pressure and Pressure Measurement
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11 Fluid Statics
CHAPTER 11 | FLUID STATICS 357 11 FLUID STATICS Figure 11.1 The fluid essential to all life has a beauty of its own. It also helps support the weight of this swimmer. (credit: Terren, Wikimedia Commons) Learning Objectives 11.1. What Is a Fluid? • State the common phases of matter. • Explain the physical characteristics of solids, liquids, and gases. • Describe the arrangement of atoms in solids, liquids, and gases. 11.2. Density • Define density. • Calculate the mass of a reservoir from its density. • Compare and contrast the densities of various substances. 11.3. Pressure • Define pressure. • Explain the relationship between pressure and force. • Calculate force given pressure and area. 11.4. Variation of Pressure with Depth in a Fluid • Define pressure in terms of weight. • Explain the variation of pressure with depth in a fluid. • Calculate density given pressure and altitude. 11.5. Pascal’s Principle • Define pressure. • State Pascal’s principle. • Understand applications of Pascal’s principle. • Derive relationships between forces in a hydraulic system. 11.6. Gauge Pressure, Absolute Pressure, and Pressure Measurement • Define gauge pressure and absolute pressure. • Understand the working of aneroid and open-tube barometers. 11.7. Archimedes’ Principle • Define buoyant force. • State Archimedes’ principle. • Understand why objects float or sink. • Understand the relationship between density and Archimedes’ principle. 11.8. Cohesion and Adhesion in Liquids: Surface Tension and Capillary Action • Understand cohesive and adhesive forces. • Define surface tension. • Understand capillary action. 11.9. Pressures in the Body • Explain the concept of pressure the in human body. • Explain systolic and diastolic blood pressures. • Describe pressures in the eye, lungs, spinal column, bladder, and skeletal system. -
Pressure, Its Units of Measure and Pressure References
_______________ White Paper Pressure, Its Units of Measure and Pressure References Viatran Phone: 1‐716‐629‐3800 3829 Forest Parkway Fax: 1‐716‐693‐9162 Suite 500 [email protected] Wheatfield, NY 14120 www.viatran.com This technical note is a summary reference on the nature of pressure, some common units of measure and pressure references. Read this and you won’t have to wait for the movie! PRESSURE Gas and liquid molecules are in constant, random motion called “Brownian” motion. The average speed of these molecules increases with increasing temperature. When a gas or liquid molecule collides with a surface, momentum is imparted into the surface. If the molecule is heavy or moving fast, more momentum is imparted. All of the collisions that occur over a given area combine to result in a force. The force per unit area defines the pressure of the gas or liquid. If we add more gas or liquid to a constant volume, then the number of collisions must increase, and therefore pressure must increase. If the gas inside the chamber is heated, the gas molecules will speed up, impact with more momentum and pressure increases. Pressure and temperature therefore are related (see table at right). The lowest pressure possible in nature occurs when there are no molecules at all. At this point, no collisions exist. This condition is known as a pure vacuum, or the absence of all matter. It is also possible to cool a liquid or gas until all molecular motion ceases. This extremely cold temperature is called “absolute zero”, which is -459.4° F. -
CHAPTER TWO - Static Aeroelasticity – Unswept Wing Structural Loads and Performance 21 2.1 Background
Static aeroelasticity – structural loads and performance CHAPTER TWO - Static Aeroelasticity – Unswept wing structural loads and performance 21 2.1 Background ........................................................................................................................... 21 2.1.2 Scope and purpose ....................................................................................................................... 21 2.1.2 The structures enterprise and its relation to aeroelasticity ............................................................ 22 2.1.3 The evolution of aircraft wing structures-form follows function ................................................ 24 2.2 Analytical modeling............................................................................................................... 30 2.2.1 The typical section, the flying door and Rayleigh-Ritz idealizations ................................................ 31 2.2.2 – Functional diagrams and operators – modeling the aeroelastic feedback process ....................... 33 2.3 Matrix structural analysis – stiffness matrices and strain energy .......................................... 34 2.4 An example - Construction of a structural stiffness matrix – the shear center concept ........ 38 2.5 Subsonic aerodynamics - fundamentals ................................................................................ 40 2.5.1 Reference points – the center of pressure..................................................................................... 44 2.5.2 A different -
Pressure Measuring Instruments
testo-312-2-3-4-P01 21.08.2012 08:49 Seite 1 We measure it. Pressure measuring instruments For gas and water installers testo 312-2 HPA testo 312-3 testo 312-4 BAR °C www.testo.com testo-312-2-3-4-P02 23.11.2011 14:37 Seite 2 testo 312-2 / testo 312-3 We measure it. Pressure meters for gas and water fitters Use the testo 312-2 fine pressure measuring instrument to testo 312-2 check flue gas draught, differential pressure in the combustion chamber compared with ambient pressure testo 312-2, fine pressure measuring or gas flow pressure with high instrument up to 40/200 hPa, DVGW approval, incl. alarm display, battery and resolution. Fine pressures with a resolution of 0.01 hPa can calibration protocol be measured in the range from 0 to 40 hPa. Part no. 0632 0313 DVGW approval according to TRGI for pressure settings and pressure tests on a gas boiler. • Switchable precision range with a high resolution • Alarm display when user-defined limit values are • Compensation of measurement fluctuations caused by exceeded temperature • Clear display with time The versatile pressure measuring instrument testo 312-3 testo 312-3 supports load and gas-rightness tests on gas and water pipelines up to 6000 hPa (6 bar) quickly and reliably. testo 312-3 versatile pressure meter up to Everything you need to inspect gas and water pipe 300/600 hPa, DVGW approval, incl. alarm display, battery and calibration protocol installations: with the electronic pressure measuring instrument testo 312-3, pressure- and gas-tightness can be tested. -
Surface Tension Measurement." Copyright 2000 CRC Press LLC
David B. Thiessen, et. al.. "Surface Tension Measurement." Copyright 2000 CRC Press LLC. <http://www.engnetbase.com>. Surface Tension Measurement 31.1 Mechanics of Fluid Surfaces 31.2 Standard Methods and Instrumentation Capillary Rise Method • Wilhelmy Plate and du Noüy Ring Methods • Maximum Bubble Pressure Method • Pendant Drop and Sessile Drop Methods • Drop Weight or Volume David B. Thiessen Method • Spinning Drop Method California Institute of Technology 31.3 Specialized Methods Dynamic Surface Tension • Surface Viscoelasticity • Kin F. Man Measurements at Extremes of Temperature and Pressure • California Institute of Technology Interfacial Tension The effect of surface tension is observed in many everyday situations. For example, a slowly leaking faucet drips because the force of surface tension allows the water to cling to it until a sufficient mass of water is accumulated to break free. Surface tension can cause a steel needle to “float” on the surface of water although its density is much higher than that of water. The surface of a liquid can be thought of as having a skin that is under tension. A liquid droplet is somewhat analogous to a balloon filled with air. The elastic skin of the balloon contains the air inside at a slightly higher pressure than the surrounding air. The surface of a liquid droplet likewise contains the liquid in the droplet at a pressure that is slightly higher than ambient. A clean liquid surface, however, is not elastic like a rubber skin. The tension in a piece of rubber increases as it is stretched and will eventually rupture. A clean liquid surface can be expanded indefinitely without changing the surface tension. -
Lecture # 04 Pressure Measurement Techniques and Instrumentation
AerE 344 class notes LectureLecture ## 0404 PressurePressure MeasurementMeasurement TechniquesTechniques andand InstrumentationInstrumentation Hui Hu Department of Aerospace Engineering, Iowa State University Ames, Iowa 50011, U.S.A Copyright © by Dr. Hui Hu @ Iowa State University. All Rights Reserved! MeasurementMeasurement TechniquesTechniques forfor ThermalThermal--FluidsFluids StudiesStudies Velocity, temperature, density (concentration), etc.. • Pitot probe • hotwire, hot film Intrusive • thermocouples techniques • etc ... Thermal-Fluids measurement techniques • Laser Doppler Velocimetry (LDV) particle-based • Planar Doppler Velocimetry (PDV) techniques • Particle Image Velocimetry (PIV) • etc… Non-intrusive techniques • Laser Induced Fluorescence (LIF) • Molecular Tagging Velocimetry (MTV) molecule-based • Molecular Tagging Therometry (MTT) techniques • Pressure Sensitive Paint (PSP) • Temperature Sensitive Paint (TSP) • Quantum Dot Imaging • etc … Copyright © by Dr. Hui Hu @ Iowa State University. All Rights Reserved! Pressure measurements • Pressure is defined as the amount of force that presses on a certain area. – The pressure on the surface will increase if you make the force on an area bigger. – Making the area smaller and keeping the force the same also increase the pressure. – Pressure is a scalar F dF P = n = n A dA nˆ dFn dA τˆ Copyright © by Dr. Hui Hu @ Iowa State University. All Rights Reserved! Pressure measurements Pgauge = Pabsolute − Pamb Manometer Copyright © by Dr. Hui Hu @ Iowa State University. All Rights Reserved! -
Pressure Measurement Explained
Pressure measurement explained Rev A1, May 25th, 2018 Sens4Knowledge Sens4 A/S – Nordre Strandvej 119 G – 3150 Hellebaek – Denmark Phone: +45 8844 7044 – Email: [email protected] www.sens4.com Sens4Knowledge Pressure measurement explained Introduction Pressure is defined as the force per area that can be exerted by a liquid, gas or vapor etc. on a given surface. The applied pressure can be measured as absolute, gauge or differential pressure. Pressure can be measured directly by measurement of the applied force or indirectly, e.g. by the measurement of the gas properties. Examples of indirect measurement techniques that are using gas properties are thermal conductivity or ionization of gas molecules. Before mechanical manometers and electronic diaphragm pressure sensors were invented, pressure was measured by liquid manometers with mercury or water. Pressure standards In physical science the symbol for pressure is p and the SI (abbreviation from French Le Système. International d'Unités) unit for measuring pressure is pascal (symbol: Pa). One pascal is the force of one Newton per square meter acting perpendicular on a surface. Other commonly used pressure units for stating the pressure level are psi (pounds per square inch), torr and bar. Use of pressure units have regional and applicational preference: psi is commonly used in the United States, while bar the preferred unit of measure in Europe. In the industrial vacuum community, the preferred pressure unit is torr in the United States, mbar in Europe and pascal in Asia. Unit conversion Pa bar psi torr atm 1 Pa = 1 1×10-5 1.45038×10-4 7.50062×10-3 9.86923×10-6 1 bar = 100,000 1 14.5038 750.062 0.986923 1 psi = 6,894.76 6.89476×10-2 1 51.7149 6.80460×10-2 1 torr = 133.322 1.33322×10-3 1.933768×10-2 1 1.31579×10-3 1 atm (standard) = 1013.25 1.01325 14.6959 760.000 1 According to the International Organization for Standardization the standard ISO 2533:1975 defines the standard atmospheric pressure of 101,325 Pa (1 atm, 1013.25 mbar or 14.6959 psi). -
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. -
Introduction
CHAPTER 1 Introduction "For some years I have been afflicted with the belief that flight is possible to man." Wilbur Wright, May 13, 1900 1.1 ATMOSPHERIC FLIGHT MECHANICS Atmospheric flight mechanics is a broad heading that encompasses three major disciplines; namely, performance, flight dynamics, and aeroelasticity. In the past each of these subjects was treated independently of the others. However, because of the structural flexibility of modern airplanes, the interplay among the disciplines no longer can be ignored. For example, if the flight loads cause significant structural deformation of the aircraft, one can expect changes in the airplane's aerodynamic and stability characteristics that will influence its performance and dynamic behavior. Airplane performance deals with the determination of performance character- istics such as range, endurance, rate of climb, and takeoff and landing distance as well as flight path optimization. To evaluate these performance characteristics, one normally treats the airplane as a point mass acted on by gravity, lift, drag, and thrust. The accuracy of the performance calculations depends on how accurately the lift, drag, and thrust can be determined. Flight dynamics is concerned with the motion of an airplane due to internally or externally generated disturbances. We particularly are interested in the vehicle's stability and control capabilities. To describe adequately the rigid-body motion of an airplane one needs to consider the complete equations of motion with six degrees of freedom. Again, this will require accurate estimates of the aerodynamic forces and moments acting on the airplane. The final subject included under the heading of atmospheric flight mechanics is aeroelasticity. -
How Do Airplanes
AIAA AEROSPACE M ICRO-LESSON Easily digestible Aerospace Principles revealed for K-12 Students and Educators. These lessons will be sent on a bi-weekly basis and allow grade-level focused learning. - AIAA STEM K-12 Committee. How Do Airplanes Fly? Airplanes – from airliners to fighter jets and just about everything in between – are such a normal part of life in the 21st century that we take them for granted. Yet even today, over a century after the Wright Brothers’ first flights, many people don’t know the science of how airplanes fly. It’s simple, really – it’s all about managing airflow and using something called Bernoulli’s principle. GRADES K-2 Do you know what part of an airplane lets it fly? The answer is the wings. As air flows over the wings, it pulls the whole airplane upward. This may sound strange, but think of the way the sail on a sailboat catches the wind to move the boat forward. The way an airplane wing works is not so different. Airplane wings have a special shape which you can see by looking at it from the side; this shape is called an airfoil. The airfoil creates high-pressure air underneath the wing and low-pressure air above the wing; this is like blowing on the bottom of the wing and sucking upwards on the top of the wing at the same time. As long as there is air flowing over the wings, they produce lift which can hold the airplane up. You can have your students demonstrate this idea (called Bernoulli’s Principle) using nothing more than a sheet of paper and your mouth. -
Total Pressure Measurement
Total Pressure Measurement Vacuum Sensors Display and control unit 5 Accessories Contents Introduction Page 5-3 to 5-6 Hot Cathode Ionization Vacuum Sensorss Page 5-7 to 5-14 Cold Cathode Ionization Vacuum Sensors Page 5-15 to 5-17 Heat Loss Vacuum Sensors Page 5-18 to 5-25 Capacitance Diaphragm Sensors Page 5-26 to 5-30 Relative Pressure Sensors Page 5-31 to 5-33 5 Display and Control Units Page 5-34 to 5-39 Contamination Protection Page 5-39 Cables Page 5-40 to 5-41 5-2 www.vacom-vacuum.com Total Pressure Measurement Introduction For all types of vacuum applications VACOM offers reliable total pressure sensors covering a wide pressure range from atmosphere to XHV. This catalogue introduces VACOM’s own, technologically leading products that can be used out-of-the-box or adapted in a customer specific version. The following chapter provides an overview of VACOM-selected sensors for total pressure measurement as well as suitable controllers. Used to determine the absolute pressure in almost every application. For more detailed information about vacuum gauges please do not hesitate to contact our technical support team. Measuring Principles for Total Pressure Instruments and Typical Measurement Ranges Extreme/Ultra high vacuum High vacuum Medium/Rough vacuum Bourdon 5 Heat loss (Pirani, Thermocouple) Membrane (capacitance, piezo) Wide range (ionization and heat loss) Ionization (Hot Cathode Ionization, Cold Cathode Ionization) Custom made (ionization, heat loss) 10-12 10-10 10-8 10-6 10-4 10-2 100 102 mbar Pressure Units 1 Pa = 0.01 mbar -
Introduction to Aerospace Engineering
Introduction to Aerospace Engineering Lecture slides Challenge the future 1 Introduction to Aerospace Engineering Aerodynamics 11&12 Prof. H. Bijl ir. N. Timmer 11 & 12. Airfoils and finite wings Anderson 5.9 – end of chapter 5 excl. 5.19 Topics lecture 11 & 12 • Pressure distributions and lift • Finite wings • Swept wings 3 Pressure coefficient Typical example Definition of pressure coefficient : p − p -Cp = ∞ Cp q∞ upper side lower side -1.0 Stagnation point: p=p t … p t-p∞=q ∞ => C p=1 4 Example 5.6 • The pressure on a point on the wing of an airplane is 7.58x10 4 N/m2. The airplane is flying with a velocity of 70 m/s at conditions associated with standard altitude of 2000m. Calculate the pressure coefficient at this point on the wing 4 2 3 2000 m: p ∞=7.95.10 N/m ρ∞=1.0066 kg/m − = p p ∞ = − C p Cp 1.50 q∞ 5 Obtaining lift from pressure distribution leading edge θ V∞ trailing edge s p ds dy θ dx = ds cos θ 6 Obtaining lift from pressure distribution TE TE Normal force per meter span: = θ − θ N ∫ pl cos ds ∫ pu cos ds LE LE c c θ = = − with ds cos dx N ∫ pl dx ∫ pu dx 0 0 NN Write dimensionless force coefficient : C = = n 1 ρ 2 2 Vc∞ qc ∞ 1 1 p − p x 1 p − p x x = l ∞ − u ∞ C = ()C −C d Cn d d n ∫ pl pu ∫ q c ∫ q c 0 ∞ 0 ∞ 0 c 7 T=Lsin α - Dcosα N=Lcos α + Dsinα L R N α T D V α = angle of attack 8 Obtaining lift from normal force coefficient =α − α =α − α L Ncos T sin cl c ncos c t sin L N T =cosα − sin α qc∞ qc ∞ qc ∞ For small angle of attack α≤5o : cos α ≈ 1, sin α ≈ 0 1 1 C≈() CCdx − () l∫ pl p u c 0 9 Example 5.11 Consider an airfoil with chord length c and the running distance x measured along the chord.