DOCSLIB.ORG

Nationaladvisorycommitt

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Nationaladvisorycommitt — . -. .!, + ..? .- - . .%- . .-. .. NATIONALADVISORY COMMITTEE FOR AERONAUTICS - TECHNICAL MEMORANDUM 1270 -J m # m OF VERY HIGH FLIGHT SPEEIX By Eugen Sanger 0 -4- Translation of ZWB Forschungsbericht Nr. 972, , May 19-38 i -+ Washington May 1950 . i. .. ----- . .. .. .... .-. , -L .- ● . NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS IIKENICAL WORANDUM 1270 TKE (MS KCNETIC!SOF WRY HI(2EFLIG3T SPEEDS* By Eugen Sanger ABSTRACT Ih ordinary gas dynamics we use assumptions which also agree with kbetic theoq of gases for smell mean free paths of the air molecules. The air forces thus calculated have to be r=xsmined, if the mean free path is comp=able with the dimensions of the moving body or even with its boundsry layer. This case is very clifficult to celculate. The con- ditions, however, are more simple, if the meen free path is large c- pared to the body length, so that the collisias of molecules with each other can be neglected compared to the collisions with We body surface. Ih order to study the influence of the lsrge mean free path, calcu- lations ere first carried out for the case of extreme rarefaction. Furthermore, the calculatims on this “completely ideal” gas will.be carried out under consideration of -Maxwelltsveloci@ distribution and under the assumption of certain experimental.lyestablished reflection laws for the trsnsl.ational end nontrenslational molecular de~ees of freedao The results thus obtained allow us to find, besides the air pressure forces perpendicular to the surface, also the friction stresses parsJ2el to the surface. — Their general results are calculated out for two practically important cases: for the thin smooth plate end for a projectile-shaped body moving axisUy. The mathematical part of the investigation was carried out prinmrily by Dr. Irene Bredt. *“Gaskinetik sehr hoher Fluggeschwindigketten.” Forschungsbericht Nr. 972, May 31, 1938. 2 - NACA TM 1270 . — —- . I. INTRODUCTION 11. AIR FORCXSON TEE FRONT SIDEOF AI?LATPIA’ZEOELIQUETOT53 AIR STREWM .- 111. AIR FORCES ON TEE FRONT SIDE 03’A FIAT PIATE VERTICAL TO 53 AIR s- . .. ... m. AIR FORCZS ON TH33BACK SIDE OF A FIAT PIATE — v. APPLmm’IoN 13xmmEs — ----- VI. 1. INTRODUCTION With the motion of lmdies at very great atmospheric heights, the air can no longer be considered a centinuous medium, in the sense of .- flow theory. At over ~0 kilmeters altitude, the mean free path of the.air ● molecules till be of the ma@tude of boun- lsyer thickness agd, at over 100 kilometers altitude, of the magnitude Of the moving body itself. ✎ The mean free path at greater heights wiIl”be defjn~tely greater than the body dimensions of the moving body, and ,theespecially simple ‘ conditions of very rmef ied “completely ideal” gases are valid where the effect of the collisions of the molecules with each other disappears ✎ ✎ compared to the effect of the collisions with the moving body. ✎ The air molecules colllde then against the moving b@y as individual -particles,in.dep@@ of each.”other, and are I%flected with a mechsniam ✚ whi~h deviates more or less from the lamwn Newt-onianprinciple of air. .. ✍✎ drag, as shown by the results of the kinetics of very rarefied gases. The velocity of the body will be denoted by v (meters per second) in the following discussion. .— H we imagine a6 usual.that for the consideration of=.theflow process the body stands still and the medium moves, then v equals the uniform undisturbed flow velocity of dl the air molecules. ✎ . ✎ ,. NACA TM 1270 3 The air molecules have also their ideal random thermal motion. The individual moleculsr thermel velocities sre distributed ccJ& pletely at randcm in all directions and are of completely srbitrary magnitudes, where.the vsrious absolute velocity magnitudes group around a most pro%able value, c (meters per second), according to Maxwell’s distribution, which has the ratio @ ~ to the most applied gas kinetic value of “average molaculer speed E“ (sqyare root of the average of the squqres of all the velocities present). According to the known hk.xwellspeed distribution law, letting P(kg 52/!) equal the total moleculsr mass per unit volume, the mass dp of those molecules having velocities between q and Cx + dcx iS: 2 .% M 4 <e C2 dc (1) T=ij7?c3 x E we consider cmly this mass dp of an otherwise motion– . less (v = O) ~S, the molecules of whioh are moving with the particular speed c= in random directions, &en the quentj.w Q– of molecules striking per seccmd on a unit surface of a motionless plane wall can be calculated, imaging that ell.1velocities Cx are plotted from the ‘ center of a sphere with rsdius Cx. The conditions of figure 1 are the result of sn inclination angle @ between the well.normal and the veloci@ directicm under consideration, and of the moleculer qusn– tity @ ~ which passes through the striped srea cll of the spliere 4CX% surface. Then: — --- — ...— - 4 NACA TM i270 . — .- If, with,the aid .ofM&weld.’s equatlmn, we include in our cd.cu- . Mkion aUI.molecules with the various pos~ible speeds Cx between.–O snd .w, the total mass F of the molecules”colliding per second will”. be: as one can find in any tetibook of gas kinetics. me pressure of the — motionless gas against the stationary wall can be calculated similsrly.— The impulse dip ,pe~endfcular to the,.- @th [email protected] of _ .._. particulti speed Cx are striking the wall at an LU@e $ will be: . -z n/2 dp 2 . dip = — Cx COS2 g al?= y CX2-” 4CX% . I$&O “ “- and the impulse of all molecules striking the wall: . .2 . (3) --- JCx=o If we double this impulse value because of the elastic rebound alwqys assumed for motionless gases, then we obtain the gas rest pressure ...... , ..* .“”” —.— .— — .— The value of the total impulse is also interesting, i.e., the sum . ..— -. of all single molecular iqulses which strike per second on the unit- area. —. NACA TM 2.!270 The totel impulse of the molecular mass d~ corresponding to a ??@iCti~ Cx will be: It iS thus 1.5 times greater than the effective impulse %? agaimt the plate. The total impulse 1 is also greater in the same ratio. II. AIR FORCES ON THE FRONT SIDE OF A FIAT PIATE OBIZQ~ TO THE AIR STREAM H we consider again the mass dp of molecules with speeds between Cx and Cx + dcx (sJnost equal)’ snd if we exam3ne its action on a flat plate in an air stream with en angle of attack a, then this process can be illustrated by figure 2, if we further as6um& that v sin a < Cx. The uniform velocity v of the individual molecule ccmibineswith the ideal random velocity (which csn have any space direction) to give a resultant, the components of which are: perpendicular to the -plate: vsina+cxcos@ pa&eJJel to the plate and to v Cos a: vcosa+cYsinticos.- $ ~arallel to,the plate end perpendicular to v cos a: Cxzsin @ sin $ snd for which the absolute value is therefore: w= v2 + 2vcx (sin a cos @ + cos a sin @ cos ~ + cx2) From the sphere of all.possible directions of Gx, a spherical sector with the half opening sngle COSZ= v sin cL/cx is excluded, in which the speed component v sin a + Cx cos @ is directed a- from the plate, i.e., the molecules of this @ range do not strike the’plate. The integration over the velocity directions of all col.lidtagmolecules is not from @ = O to ~ as with the motionless gas, but from @ . 0 to n =X* , —. 6 mcA m 1270” . ..- —- The molecular mms. co~iding per second against tbe unit plate ‘“-- .,: area with the selected speed Cx is therefore: .— — — m— % .. —. .+ .dp d~ = (v sin a + Cx Cos * )2C=% -- 4CX2’“J@o .— — . For v sin a > cx the integration extends over t~e whole sphere _. .7 from @ = O to YC &d the “moleculsrmass coiliding against the ylate _ -. ..—= with selected.speed Cx is m d~=~ (v sin a + Cx cos @)2cx2fi‘sin @ d~ = “dpv gin a“ ““ .- — . “2” J$&O . NACA ‘IW11270 . Both equations naturally give the same value for v sin a = Cx. With the aid of Maxwell’s distritition equation the total moleculsr mass colliding on the unit area per unit tfme within the speed range Cx =0 to mwil.l be: m v sins 1 F= +2. Tsinadp E Cx f3iIla++sm2”dp+c~ J(c=- sin a MCx=0 2 (4) 2 vsina 2 _—Cx Vcx ~’ ~c ● 4P sinae ~ x v f Cx=o Thus the number of the colliding molecules is known, and for cal- culation of the forces acting on the plate, we must now detemnine what hrpulse the molectiar mass under consideration produces in the direct- ions in question. The impulse perpendicular to the plate, ip and the impulse psrallel to it iT will be examined separately. ● . 8 NACATM;270 . We find for the impulse per second perpendicular to tke plate --- 3-C-2 dp ..—. 1. If T sln a < Cx: dip = (v sin a,+ Cx Cos @)%? “X2” J+0 .- &fl+Lst ia 3 ““ Cx Y( ) .. 1-r dp —, 2.~ VSill CL>Cx: dip- (v 19inal+ c~ Cos @)% =“+0 J — .- dpc22+~ — 6X ( This sumation of the impulse components over allpos~ible direc- tions yields the total impulse, perpendicular to.the plate~of the air —— : molecules striking t~e unit area per second with.a speed Cx dete~ mined by” dp. NACA TM 3.270 9 . The further summaticm of the impulses over KLl speeds c= with the aid of Mexwellts distribution equation results in the total impulse ‘P acting per second perpendicular to the plate: , Vsina g 1 c~ k- ~2 +’ =$P 2+6— Si112adcx ~Te ( CX2 ) [JCx=o 1 If we set a= O then equation (5) gives the impulse of the motion- ~ess gas against the motionless wall, equaticm (3).
Load more

Recommended publications
  • Schlieren Imaging of Loud Sounds and Weak Shock Waves in Air Near the Limit of Visibility
    Shock Waves DOI 10.1007/s00193-009-0226-6 ORIGINAL ARTICLE Schlieren imaging of loud sounds and weak shock waves in air near the limit of visibility Michael John Hargather · Gary S. Settles · Matthew J. Madalis Received: 27 April 2009 / Accepted: 4 August 2009 © Springer-Verlag 2009 Abstract A large schlieren system with exceptional sensi- Keywords Shock waves · Nonlinear acoustics · Sound · tivity and a high-speed digital camera are used to visualize Noise · Schlieren · High-speed imaging loud sounds and a variety of common phenomena that pro- duce weak shock waves in the atmosphere. Frame rates var- PACS 42.79.Mt · 43.25.+y ied from 10,000 to 30,000frames/s with microsecond frame exposures. Sound waves become visible to this instrumenta- tion at frequencies above 10kHz and sound pressure levels 1 Introduction in the 110dB (6.3Pa) range and above. The density gradient produced by a weak shock wave is examined and found to Visualizing sound-wave motion in air has been a dream of sci- depend upon the profile and thickness of the shock as well as entists and engineers for at least a century and a half, although the density difference across it. Schlieren visualizations of sound waves and weak shock waves were initially confused. weak shock waves from common phenomena include loud August Toepler’s (1836–1912) epitaph, “He was the first to trumpet notes, various impact phenomena that compress a see sound,” actually referred to his schlieren imaging of weak bubble of air, bursting a toy balloon, popping a champagne shock waves from electric sparks [1].
    [Show full text]
  • Gas Kinetics in Galactic Disk. Why We Do Not Need a Dark Matter to Explain Rotation Curves of Spirals? Anton Lipovka
    Gas kinetics in galactic disk. Why we do not need a dark matter to explain rotation curves of spirals? Anton Lipovka To cite this version: Anton Lipovka. Gas kinetics in galactic disk. Why we do not need a dark matter to explain rotation curves of spirals?. 2018. hal-01832309v3 HAL Id: hal-01832309 https://hal.archives-ouvertes.fr/hal-01832309v3 Preprint submitted on 24 Jul 2020 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. Gas kinetics in galactic disk. Why we do not need a dark matter to explain rotation curves of spirals? Lipovka A.A. Department of Research for Physics, Sonora University, 83000, Hermosillo, Sonora, México May 27, 2020 Abstract In present paper, we analyze how the physical properties of gas affect the Rotation Curve (RC) of a spiral galaxy. It is shown, that the observed non-Keplerian RCs measured for outer part of disks, and the observed radial gas distribution are closely related by the diffusion equation, which clearly indicates that no additional mass (Dark Matter) is need. It is stressed, that while the inner part of the RC is subject of the Kepler law, for the correct description of the outer part of the RC, the collisional property of the gas should also be taken into account.
    [Show full text]
  • Project RAND Publication: RA-15022
    , , ,-.. ,'. --. - ~.-~~ UNCLASSIFIED (rA) AERODYNAMICS, GAS DYNAMICS AND HEAT TRANSFER PROBLEMS OF A SATELLITE ROCKET RA-15022 February 1, 1947 UNCLASSI FI ED DOUGLAS AIRCRAFT COMPANY, INC. == DECLASSIFIED lAW E012958 BY EO Review Team DATE &' - ) r; --- :J-cJl r} This document contains information affecting the national defense of the United States within the meaning of the Espionage Act, SO U.S.C., 31 and 32, as amended. Its transmission or the revelation of its contents in any manner to an unauthorized person is prohibited by law. SECRET TABLE OF CONTENTS LIST OF FIGURES ...... , ......................................................... v SUMMARy .........................................................................vii LIST OF SyMBOLS ............................................................... ix I. AERODYNAMICS .............................................................. I A. Drag ....................................................................... l 1. The Drag Forces Exerted on a Supersonic Rocket ......................... 1 2. Approximations Used in the Drag Analysis ............................... 4 3. Methods Employed in Evaluating the Drag ................................ 6 4. The Optimum Shape for a Satellite Rocket ......... , ..................... 8 5. Rarefied Gas Dynamics (Superaerodynamics) ............................. 20 B. Aerodynamics of Stability and Control. .. , ..............•.... : ............. 20 L Control Manent ..................................... '............ , ...... 21 2. Body Moment ..........................................................
    [Show full text]
  • Gas Phase Reaction Kinetics of Neutral Oxygen Species
    National Bureau ot Standards Library, £01 Admin. Bldg. FEB 3 1969 A11102 mbQQb NSRDS-NBS 20 All 1021 46006 /NSflOS-MI? N6S-.UB-CW NBS PUBLICATIONS Gas Phase Reaction Kinetics Of Neutral Oxygen Species U.S. DEPARTMENT OF COMMERCE NATIONAL BUREAU OF STANDARDS National Standard Reference Data Series National Bureau of Standards National Standard Reference Data System, Plan of Operation, NSRDS-NBS 1 — 15 cents* Thermal Properties of Aqueous Uni-univalent Electrolytes, NSRDS-NBS 2 — 45 cents* Selected Tables of Atomic Spectra, Atomic Energy Levels and Multiplet Tables — Si II, Si III, Si IV, NSRDS-NBS 3, Section 1 — 35 cents* Selected Tables of Atomic Spectra, Atomic Energy Levels and Multiplet Tables — Si I, NSRDS-NBS 3, Section 2 — 20 cents* Atomic Transition Probabilities, Volume I, Hydrogen Through Neon, NSRDS-NBS 4 — $2.50* The Band Spectrum of Carbon Monoxide, NSRDS-NBS 5 — 70 cents* Tables of Molecular Vibrational Frequencies, Part 1, NSRDS-NBS 6 — 40 cents* High Temperature Properties and Decomposition of Inorganic Salts, Part 1, Sulfates, NSRDS-NBS 7-35 cents* Thermal Conductivity of Selected Materials, NSRDS-NBS 8 — 11.00* Tables of Bimolecular Gas Reactions, NSRDS-NBS 9 — $2.00* Selected Values of Electric Dipole Moments for Molecules in the Gas Phase, NSRDS- NBS 10-40 cents* Tables of Molecular Vibrational Frequencies, Part 2, NSRDS-NBS 11 — 30 cents* Tables for the Rigid Asymmetric Rotor: Transformation Coefficient for Symmetric to Asymmetric Bases and Expectation Values of P§, P|, and Pf, NSRDS-NBS 12 — 60 cents* Hydrogenation
    [Show full text]
  • Gas Kinetics Introduction
    Gas Kinetics Introduction • Most deposition techniques rely on gas flow in a vacuum. • We need a model for understanding; – the speed and energy of the gas molecules as a function of temperature and pressure, – how these molecules interact with each other and their surroundings, – and how mass, heat and momentum is transported by these molecules. The Size of a Molecule (a very rough calculation) • Take water (liquid H2 O) as an example. • Oxygen has 8 protons and 8 neutrons for a total of 16 nucleons and Hydrogen has 1 proton. So water has 16+1+1=18 nucleons −24 m≈PN1 m . ≈ 66 × 10g −23 m18HO= mN 2 = . 99 × g 10 2 d HO2 N1= m 3 = . 35 ×22 molecules 10 / g HO2 HO2 ρ 1= .g 00 cm3 / HO2 1 V = 2= . 99 × −23 10cm 3 molecule / HO2 ρ N HOHO2 2 3 d=2 ×3 V5 . = 64− ×8 10cm HO2 4 HO2 The Distance Between Molecules in a Gas • Now take water vapor (gaseous H2 O). ρ 0= . 8 ×g 10−3 cm3 / HO2 1 −20 3 l V = 3= . 73 × 10cm molecule / HO2 HO2 ρ N HOHO2 2 l=3 V3 . = 34 ×−7 10cm HO2 HO2 l≈ 6 d HO2 HO2 Molecular Velocities • Basic assumptions: – We’ll assume an ideal gas where the gas molecules interact elastically (collisions are similar to the collisions of hard billiard balls). – The distance between molecules are large compared to their sizes. – There are no attractive or repulsive forces between the molecules and each molecule moves independently of the others. Maxwell-Boltzmann Distribution • Under these assumptions, the molecules of a gas have velocities that are distributed according to: 1 dn M ⎛ Mv2 ⎞ where f is the fractional number of 2 ⎜ ⎟ molecules, v is the velocity, M is the f() v= =4πv exp⎜− ⎟ molecular weight, T is the temperature n dv 2πRT ⎝ 2RT ⎠ and R is the universal gas constant.
    [Show full text]
  • Mathematical Modeling of the Shockless Explosion Combustion
    Dissertation Mathematical Modeling of the Shockless Explosion Combustion Phillip Berndt im August 2016 eingereicht am Fachbereich Mathematik und Informatik Freie Universität Berlin zur Erlangung des Grades eines Doktors der Naturwissenschaften Erstgutachter & Betreuer: Prof. Dr.-Ing. Rupert Klein Zweitgutachter: Prof. Dr.-Ing. Christian Oliver Paschereit Drittgutachter: Prof. Dr. rer.nat. Volker John Tag der Disputation: 02. Dezember 2016 Contents 1. Introduction 1 1.1. The Shockless Explosion Combustion . .4 1.2. The Reactive Euler Equations of Fluid Dynamics . .7 1.2.1. The One-Dimensional Reactive Euler Equations . .8 1.2.2. Ignition Delay Time and Excitation Time . 11 1.2.3. Lagrangian Picture . 13 1.2.4. Quasi One-Dimensional Flow . 16 2. Fuel Requirements and Blend Selection 19 2.1. Model Reduction for SEC Fuels . 20 2.2. Model for Idealized SEC Fuels . 24 2.2.1. Single-Stage Model . 25 2.2.2. Two-Stage Extension . 27 2.3. Fuel Selection for the Atmospheric SEC Test Rig . 29 2.4. Numerical Methods for the Simulation of Chemical Kinetics . 32 2.5. Intermediate Conclusion . 35 3. Numerical Methods for Multi-Species Gaseous Flow 37 3.1. Solution of the Riemann Problem for Ideal Gases . 38 3.1.1. Linearization of the Equations . 38 3.1.2. Primitive Form of the Equations . 39 3.1.3. Riemann Invariants . 40 3.1.4. Solution Strategy . 42 3.2. The HLLE Solver in Multi-Species Simulations . 43 3.2.1. Positivity . 44 3.2.2. Pressure Oscillations at Contact Discontinuities . 46 3.2.3. A Note on Larrouturou’s Positivity Correction . 49 3.3.
    [Show full text]
  • On Ionospheric Aerodynamics*
    Prog. Aerospace Sei. 1975. Vo}. 16, No. 3. pp. 273-297. Pergamon Press. Printed in Great Britain ON IONOSPHERIC AERODYNAMICS* V. C. LIU The University of Michigan, Ann Arbor Summary--This paper presents theoretical methods to determine the gas dynamic and the electrostatic effects due to the interaction caused by a rapidly moving body in the ionosphere. The principles of the methods are derived from the kinetic theory of collision-free plasma. It is shown that the collective behavior of the collision-free plasma makes it possible to use the fluid approach to treat the problems of ionospheric aerodynamics. Various solutions to the system of fluid and field equations that have direct bearing on the ionospheric aerodynamics are presented and discussed. Physical significances of the mathematical results are stressed. Some outstanding unsolved problems in ionospheric aerodynamics are elaborated and discussed. LIST OF SYMBOLS AND UNITS (EM) l. INTRODUCTION All symbols are defined in the text. Only those that are repeatedly used are listed here. In the description of The advent of space flight which entails the electromagnetic fields Gaussian cgs units are adopted interaction between a rapidly moving, electrically throughout. These symbols are compiled in a separate charged body, e.g. a spacecraft, and a tenuous group with their corresponding quantities in rationalized ionized gas, e.g. the terrestrial ionosphere or the inks units with conversion factors listed in tandem. interplanetary gas, brings the aerodynamicists to GROUP A (electromagnetic) bear with a new aspect of aerodynamics--the ionospheric aerodynamics.t This interdisciplinary Gaussian Quantity mks science which combines gas dynamics with elec- B magnetic induction (47r/p.o)'r-B H magnetic field (4 ~-p.o)'nH tromagnetic fields poses some distinctive traits of c speed of light (~ot~o)-''~ its own even though it shares the basic principles of E electric field (4rr¢o)'r~E plasma physics with studies on electrical discharges 4, electric potential (4,n.eo)'1:~ and nuclear fusion.
    [Show full text]
  • Biosignature Gases in H2-Dominated Atmospheres on Rocky Exoplanets S
    The Astrophysical Journal, 777:95 (19pp), 2013 November 10 doi:10.1088/0004-637X/777/2/95 C 2013. The American Astronomical Society. All rights reserved. Printed in the U.S.A. BIOSIGNATURE GASES IN H2-DOMINATED ATMOSPHERES ON ROCKY EXOPLANETS S. Seager1,2,W.Bains1,3, and R. Hu1 1 Department of Earth, Atmospheric, and Planetary Sciences, Massachusetts Institute of Technology, 77 Massachusetts Avenue, Cambridge, MA 02139, USA 2 Department of Physics, Massachusetts Institute of Technology, 77 Massachusetts Avenue, Cambridge, MA 02139, USA 3 Rufus Scientific Ltd., 37 The Moor, Melbourn, Herts SG8 6ED, UK Received 2013 April 2; accepted 2013 August 13; published 2013 October 18 ABSTRACT Super-Earth exoplanets are being discovered with increasing frequency and some will be able to retain stable H2- dominated atmospheres. We study biosignature gases on exoplanets with thin H2 atmospheres and habitable surface temperatures, using a model atmosphere with photochemistry and a biomass estimate framework for evaluating the plausibility of a range of biosignature gas candidates. We find that photochemically produced H atoms are the most abundant reactive species in H2 atmospheres. In atmospheres with high CO2 levels, atomic O is the major destructive species for some molecules. In Sun-Earth-like UV radiation environments, H (and in some cases O) will rapidly destroy nearly all biosignature gases of interest. The lower UV fluxes from UV-quiet M stars would produce a lower concentration of H (or O) for the same scenario, enabling some biosignature gases to accumulate. The favorability of low-UV radiation environments to accumulate detectable biosignature gases in an H2 atmosphere is closely analogous to the case of oxidized atmospheres, where photochemically produced OH is the major destructive species.
    [Show full text]
  • Kinetic Measurements Using Flow Tubes the Journal of Physical Chemistry, Vol
    Kinetic Measurements Using Flow Tubes The Journal of Physical Chemistry, Vol. 83, No. 1, 1979 3 for diatomics substantial progress has been achieved, as bring experimenitalists and theorists together and to show evidenced by some of the present papers. that the field of thermal elementary reaction kinetics is Lastly, the symposium did achieve its major goal: to alive and well. Kinetic Measurements Using Flow Tubes Carleton J. Howard Aeronomy Laboratory, NOAA Environmental Research Laboratory, Boulder, Colorado 80303 (Received October 6, 1978) Publication costs assisted by the NOAA Environmental Research Laboratory This paper is a selective survey of the chemical kinetic literature involving flow tube measurements of elementary reaction rate constants. It describes the origins of the flow tube method, the experimental technique, the measurement of rate constants, and an analysis of the inherent errors. Emphasis is placed on the discussion of the strengths and limitations of the method as a source of kinetic data. I. Introduction TABLE I: Comparison of Flow Tube and Flash-Photo- In recent years there has been an increasing demand for lysis Kinetic Tecliniques gas phase reaction rate data. Laser development,l at- flow tube flash photolysis mospheric chemi~try,~,~and combustion4 are examples of temperature 200-600 K 100-600 K fields of application of elementary reaction studies. range Committees and organizations have been created to collect, pressure 1-10 torr 5 torr-several evaluate, and disseminate kinetic information. In at- range atmospheres mospheric chemistry, for example, there are serious rate constant (1O-lo-lO-l ') cm3 (10~'o-10~'8)cm3 economic and social implications derived from the ap- range molecule-' s-' molecule-' s-l detection excellent requires fast plication of kinetic data in computer models that assess versatility detector the impact of anthropogenic chemicals on stratospheric reactant excellent limited ozone.
    [Show full text]
  • Gas Kinetics, Vacuum Technology 1. A) Write a Compact Sentence That Describes the Molecular Origin of Gas Pressure, Including Its Temperature and Mass Dependence
    3.155J/6.152J Microelectronic Processing Technology Fall Term, 2003 Bob O'Handley Martin Schmidt Quiz # 1 Out: Oct. 22, 2003 Due: Oct. 22, 2003 Gas kinetics, vacuum technology 1. a) Write a compact sentence that describes the molecular origin of gas pressure, including its temperature and mass dependence. [5] A: P is due to change in momentum Dp = m Dv of molecules striking a surface; velocity increases as T so and accounting for the flux of m Dp ~ mT nv atoms hitting the surface Dp µ J mk T µ x mk T , where n is the B 2 B number density of molecules in chamber. b) In a 50 cm diameter vacuum chamber at room temperature and a pressure of 10 † mT, mostly N2 ( assume a nitrogen molecular diameter of 2 Å), what is the mean free path of the N2 molecules and describe their transport as either viscous or ballistic. [6] A: l = 1.75 cm, viscous. c) You want to reduce the pressure in your diffusion-pumped vacuum chamber from 10-5 Torr to 10-6 Torr. Comment on the efficacy of the following options. i) There is a good diffusion pump 5 feet from your chamber; it is known to produce a vacuum of 10-7 Torr in its chamber. You run a 1/2” tygon tube from that diffusion pump to an inlet valve on your chamber. [3] ii) Bake out your system at about 150oC overnight using heating tape. [3] iii) Pump liquid nitrogen through an unused substrate holder in your chamber. [3] A: i) Conductance of a long thin tube is too poor to allow much pumping; 1/2” diameter ≈ l, so flow is viscous.
    [Show full text]
  • The Atmospheric Chemistry of Hydrogen Cyanide (HCN)
    UC Irvine UC Irvine Previously Published Works Title The atmospheric chemistry of hydrogen cyanide (HCN) Permalink https://escholarship.org/uc/item/98d9x8wp Journal Journal of Geophysical Research, 88(C15) ISSN 0148-0227 Authors Cicerone, RJ Zellner, R Publication Date 1983 DOI 10.1029/JC088iC15p10689 License https://creativecommons.org/licenses/by/4.0/ 4.0 Peer reviewed eScholarship.org Powered by the California Digital Library University of California JOURNAL OF GEOPHYSICAL RESEARCH, VOL. 88, NO. C15, PAGES 10,689-10,696, DECEMBER 20, 1983 The AtmosphericChemistry of Hydrogen Cyanide (HCN) R. J. CICERONE National Centerfor AtmosphericResearch R. ZELLNER UniversitdtGSttin•Ten, lnstitut fur PhysikalischeChemie Since 1981,three groupshave reportedspectroscopic detections and measurementsof hydrogency- anidein the atmosphere.HCN concentrations(volume mixing ratios) of (1.5-1.7)x 10-•ø appearto characterizethe stratosphereand the northernhemisphere's nonurban troposphere. In this paper we explorethe atmosphericbehavior of HCN by examiningits chemicaland photochemicalproperties. Its principalsinks are reactionswith atmosphericOH and O(•D); precipitationappears to be a negligible sink. In the stratosphere,vacuum UV photonsalso attack HCN. Atmosphericmodel calculationsshow that HCN shouldbe relativelywell mixedin the troposphereand that its concentrationdecreases slowly with altitudein the stratosphere.Its atmosphericresidence time appearsto be about 2.5 years,although 1-5 yearsis a possiblerange. To maintain the observedatmospheric burden of HCN, an annual source of about 2 x 10TM g nitrogenas HCN is required;we speculateas to the identityof thesesources. Oxidation of HCN by OH, while the major sink for atmosphericHCN, is not simpleor direct.Instead, oxidation proceedsfrom the HCN-OH adduct formed in HCN + OH reactions.These pathways and their uncertainties are outlined here.
    [Show full text]
  • AIAA 98–2445 Prediction and Validation of Mars Pathfinder
    AIAA 98–2445 Prediction and Validation of Mars Pathfinder Hypersonic Aerodynamic Data Base Peter A. Gnoffo, Robert D. Braun, K. James Weilmuenster, Robert A. Mitcheltree, Walter C. Engelund, Richard W. Powell NASA Langley Research Center Hampton, VA 23681-0001 7th AIAA/ASME Joint Thermophysics and Heat Transfer Conference June 15–18, 1998 / Albuquerque, NM For permission to copy or republish, contact the American Institute of Aeronautics and Astronautics 1801 Alexander Bell Drive, Suite 500, Reston, VA 20191 Prediction and Validation of Mars Path nder Hyp ersonic Aero dynamic Data Base Peter A. Gno o, Rob ert D. Braun, K. James Weilmuenster, Rob ert A. Mitcheltree, Walter C. Engelund, Richard W. Powell NASA Langley Research Center Hampton, VA 23681-0001 Post ight analysis of the Mars Path nder hyp ersonic, continuum aero dynamic data base is presented. Measured data include accelerations along the body axis and axis normal directions. Comparisons of pre ight simulation and measurements show good agreement. The prediction of two static instabilities asso ciated with movementof the sonic line from the shoulder to the nose and back was con rmed by measured normal accelerations. Reconstruction of atmospheric density during entry has an uncertainty directly prop ortional to the uncertainty in the predicted axial co ecient. The sensitivity of the moment co ecient to freestream density, kinetic mo dels and center-of-gravity lo cation are examined to provide additional consistency checks of the simulation with ight data. The atmospheric density as derived from axial co ecient and measured axial accelerations falls within the range required for sonic line shift and static stability transition as indep endently determined from normal accelerations.
    [Show full text]