DOCSLIB.ORG

Supersonic and Subsonic Projectile Overtaking Problems in Muzzle Gun Applications

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Supersonic and Subsonic Projectile Overtaking Problems in Muzzle Gun Applications AJCPP 2008 March 6-8, 2008, Gyeongju, Korea Supersonic and Subsonic Projectile Overtaking Problems in Muzzle Gun Applications Rajesh Gopalapillai, Suryakant Nagdewe and Heuy Dong Kim School of Mechanical Engineering, Andong National University, 388, Songchun-dong, Andong, Korea [email protected] Toshiaki Setoguchi Department of Mechanical Engineering, Saga University, 1, Honjo, Saga 840-8502, Japan Keywords: Blast Wave, Projectile, Ballistic Range, Overtaking, Chimera Mesh Abstract A projectile when passes through a moving shock ambient gas that has early been perturbed by the blast wave, experiences drastic changes in the aerodynamic wave. Behind the contact surface, an unsteady jet is forces as it moves from a high-pressure region to a developed by the discharge of the compressed gas. low pressure region. These sudden changes in the This unsteady jet may often be accompanied by a forces are attributed to the wave structures produced shock wave, the strength of which is again dependent by the projectile-flow field interaction, and are on the projectile acceleration4. responsible for destabilizing the trajectory of the Following the unsteady jet, the projectile is projectile. These flow fields are usually encountered discharged, consequently leading to strong interaction in the vicinity of the launch tube exit of a ballistic between the projectile and the unsteady jet when the range facility, thrusters, retro-rocket firings, silo former passes through the preceding unsteady jet. The injections, missile firing ballistics, etc. In earlier effects of this interaction are usually reflected in the works, projectile was assumed in a steady flow field unsteady fluctuating forces that act on the projectile when the computations start and the blast wave itself5. As the projectile’s motion proceeds, a bow maintains a constant strength. However, in real shock wave may be produced in front of the projectile, situations, the projectile produces transient effects in depending on the projectile speed and local flow the flow field which have a deterministic effect on the states. Therefore, the projectile flow field, being time- overtaking process. In the present work, the dependent, has a strong dependence on the preceding overtaking problem encountered in the near-field of PBW and bow shock wave. As time advances, the muzzle guns is investigated for several projectile projectile may or may not overtake the preceding Mach numbers. Computations have been carried out PBW in a short distance, subject to certain conditions using a chimera mesh scheme. The results show that, which will be discussed later, in more detail. the unsteady wave structures are completely different Meanwhile, the high-pressure gas which, in from that of the steady flow field where the blast wave general, is obtained by the combustion explosion in maintains a constant strength, and the supersonic and the ballistic range6, and used to drive the projectile subsonic overtaking conditions cannot be initially, is discharged, immediately after the distinguished by identifying the projectile bow shock projectile is ejected from the launch tube. The wave only. secondary blast wave (SBW) is formed due to the sudden discharge of the high-pressure combustion gas. Introduction The so called Ritchmyer-Meshcow instability develops when the contact surface following the PBW When a projectile suddenly starts to move in the is swept by the SBW7. launch tube of a ballistic range, a series of A highly under-expanded supersonic jet is compression waves are formed ahead of the projectile produced due to the discharge of the high-pressure due to its piston effect. These compression waves combustion gas. Inside the jet, a strong Mach disk is coalesce into a normal shock wave in which its formed to match the pressure levels behind the strength depends on the acceleration of the projectile. moving projectile. If the discharged high-pressure The shock wave propagates towards the exit of the combustion gas maintains a constant mass flow rate, launch tube, and is discharged from the launch tube, the under-expanded jet structure will be steady8, forming a spherical blast wave due to the shock unlike the unsteady jet produced by the discharge of diffraction at the exit of the launch tube. This blast the compressed gas in between the normal shock wave is usually called the primary blast wave (PBW) wave and the projectile in the very beginning9. and develops with associated starting vortices at the As described above, the flow field around the exit of the launch tube1-3. moving projectile is highly complicated as well as Shortly after the discharge of the shock wave strongly time-dependent. There are various types of from the launch tube, the compressed gas in between interactions among the shear layers, shock waves, the shock wave and moving projectile inside the wake flow behind the projectile and the moving launch tube is discharged and a contact surface is projectile itself. These complex flow phenomena formed at the boundary of the compressed gas and the 711cannot help but be reflected on the aerodynamic 1 AJCPP 2008 March 6-8, 2008, Gyeongju, Korea forces, thus having major influences on the flight with constant strength. The overtaking process being control and stability of projectile10. purely time-dependant, many questions need to be All these related phenomena take place in a very answered with regard to its transient nature. It is not short interval of time, and the measurement of the known exactly at what conditions the projectile detailed aerodynamics is extremely difficult. So far, overtakes the blast wave and what parameters control the investigation of the projectile aerodynamics and the overtaking problem. Moreover, detailed projectile aeroballistics has been limited to the visualization aerodynamics produced at the instant when it pictures of the flow field using a high-speed optical overtakes the blast wave is an exciting problem to the system11, and quantitative data associated with the aerodynamic designers. flying projectile aerodynamics are sparse to date. It is The present study concerns with the projectile expected that the aerodynamic forces drastically aerodynamics and gets insight into the detailed change as the projectile interacts with the unsteady jet overtaking flow field. One-dimensional analysis has and the shock systems around or it passes through the been performed to shed new light on the overtaking primary blast wave12. For example, as the projectile flow fields. A computational fluid dynamics (CFD) passes through the primary blast wave, or the method using a moving grid system has been projectile interacts with the preceding unsteady jet, it employed to simulate the projectile aerodynamics on experiences a sudden change in the aerodynamic drag. such flow fields. The present computations The aerodynamic force data associated with such successfully represent the projectile aerodynamics situations are highly lacking and have been characteristics and predict well the projectile ambiguously conjectured until now. acceleration, velocity and aerodynamic drag which Only a few works9-12 have been to date made to were hardly obtained in experiments. investigate such interaction flow field around the flying projectile. Thus, the prediction of the unsteady One –Dimensional Analysis of the Projectile projectile aerodynamic data is now one of very Overtaking challenging works which are recently being paid In general, the speed of sound downstream of a much attention from researchers and aerodynamic shock wave is higher than that upstream of it. Thus, a designers as well. wave or an object can overtake the preceding shock Of many aspects of the unsteady projectile wave, depending on the strength of the shock wave aerodynamics described above, one of the most and the speed of the object relative to the flow behind important phenomena occurs as projectile overtakes the shock wave. In order to analyze the projectile the preceding blast wave. Recently, Watanabe, et. al.13 overtaking problems, we assume the overtaking flow investigated the projectile overtaking flow fields to to be unsteady and one-dimensional. The primary study the projectile aerodynamics. They used a one- blast wave is hence assumed as a normal shock wave dimensional analysis to study the overtaking criteria with constant propagation speed. For a given normal and argued that the overtaking process can be either shock wave that propagates at constant speed of Mach subsonic or supersonic based on the projectile Mach number Ms in still air, the flow properties can be number relative to the flow behind the blast wave. calculated behind the shock wave. It is also assumed They arbitrarily assumed the projectile and blast wave that a projectile with speed up is propagating towards Mach numbers and their computations started from a the normal shock wave. steady state solution of the flow field. The blast wave Assuming that the flow states across the shock maintained constant strength throughout their wave are denoted by the subscripts 1 and 2, and the 14 computations. Later, Ahmedika and Shirani have projectile velocity is given by up, the shock wave done viscous computations on transonic and supersonic overtaking flow fields using similar assumptions. In both of these works, the relative projectile Mach number was the major factor to decide the overtaking criterion. However, in actual situations where the blast wave propagation is a transient phenomenon, the strength of the blast wave will be decreasing and the relative
Load more

Recommended publications
  • Experimental Investigation Into Shock Waves Formation and Development Process in Transonic Ow
    Scientia Iranica B (2017) 24(5), 2457{2465 Sharif University of Technology Scientia Iranica Transactions B: Mechanical Engineering www.scientiairanica.com Experimental investigation into shock waves formation and development process in transonic ow M. Farahani and A. Jaberi Department of Aerospace Engineering, Sharif University of Technology, Tehran, Iran. Received 11 May 2016; received in revised form 12 August 2016; accepted 8 October 2016 KEYWORDS Abstract. An extensive experimental investigation was performed to explore the shock waves formation and development process in transonic ow. Shadowgraph visualization Shock waves technique was employed to provide visual description of the ow eld features. Based on formation process; the visualization, the formation process was categorized into two intrinsically di erent Transonic ow; phases, namely, subsonic and supersonic. The characteristics of subsonic phase are well Shadowgraphy known; however, those of the supersonic one are far less studied. The supersonic phase visualization; itself is made up of two consecutive phases, namely, approaching and sweeping. The e ects Splitting of shock of each phase on the ow eld characteristics and on shaping the supersonic regime were waves; studied in details. In order to generalize the results, three di erent models were tested. A Zeh shock. special terminology is suggested by authors to ease the process description and pave a way for future studies. Above all, as the transition from transonic regime to the supersonic one is a vague concept in terms of physical reasoning, a new explanation is proposed that can be used as a criterion for distinguishing between transonic and supersonic regimes. © 2017 Sharif University of Technology.
    [Show full text]
  • Bifurcating Mach Shock Reflections with Application to Detonation Structure
    BIFURCATING MACH SHOCK REFLECTIONS WITH APPLICATION TO DETONATION STRUCTURE Philip Mach A thesis submitted to the Faculty of Graduate and Postdoctoral Studies in partial fulfillment of the requirements for the degree of MASTER OF APPLIED SCIENCE in Mechanical Engineering Ottawa-Carleton Institute for Mechanical and Aerospace Engineering University of Ottawa Ottawa, Canada August 2011 © Philip Mach, Ottawa, Canada, 2011 ii Abstract Numerical simulations of Mach shock reflections have shown that the Mach stem can bifurcate as a result of the slip line jetting forward. Numerical simulations were conducted in this study which determined that these bifurcations occur when the Mach number is high, the ramp angle is high, and specific heat ratio is low. It was clarified that the bifurcation is a result of a sufficiently large velocity difference across the slip line which drives the jet. This bifurcation phenomenon has also been observed after triple point collisions in detonation simulations. A triple point reflection was modelled as an inert shock reflecting off a wedge, and the accuracy of the model at early times after reflection indicates that bifurcations in detonations are a result of the shock reflection process. Further investigations revealed that bifurcations likely contribute to the irregular structure observed in certain detonations. iii Acknowledgements Firstly, I would like to thank my supervisor, Matei Radulescu, who guided me through the complicated task of learning about the detonation phenomenon, provided me with most of the scripts for the numerical simulations, answered my questions (no matter how dumb they were), and was patient with my progress. I would have obviously been lost without him.
    [Show full text]
  • Investigation of Shock Wave Interactions Involving Stationary
    Investigation of Shock Wave Interactions involving Stationary and Moving Wedges Pradeep Kumar Seshadri and Ashoke De* Department of Aerospace Engineering, Indian Institute of Technology Kanpur, Kanpur, 208016, India. *Corresponding Author: [email protected] Abstract The present study investigates the shock wave interactions involving stationary and moving wedges using a sharp interface immersed boundary method combined with a fifth-order weighted essentially non- oscillatory (WENO) scheme. Inspired by Schardin’s problem, which involves moving shock interaction with a finite triangular wedge, we study influences of incident shock Mach number and corner angle on the resulting flow physics in both stationary and moving conditions. The present study involves three incident shock Mach numbers (1.3, 1.9, 2.5) and three corner angles (60°, 90°, 120°), while its impact on the vorticity production is investigated using vorticity transport equation, circulation, and rate of circulation production. Further, the results yield that the generation of the vorticity due to the viscous effects are quite dominant compared to baroclinic or compressibility effects. The moving cases presented involve shock driven wedge problem. The fluid and wedge structure dynamics are coupled using the Newtonian equation. These shock driven wedge cases show that wedge acceleration due to the shock results in a change in reflected wave configuration from Single Mach Reflection (SMR) to Double Mach Reflection (DMR). The intermediary state between them, the Transition Mach Reflection (TMR), is also observed in the process. The effect of shock Mach number and corner angle on Triple Point (TP) trajectory, as well as on the drag coefficient, is analyzed in this study.
    [Show full text]
  • Numerical Study of Interaction of a Vortical Density Inhomogeneity with Shock and Expansion Waves
    22/ NASA/CR- 1998-206918 ICASE Report No. 98-10 Numerical Study of Interaction of a Vortical Density Inhomogeneity with Shock and Expansion Waves A. Povitsky ICASE D. Ofengeim University of Manchester Institute of Science and Technology Institute for Computer Applications in Science and Engineering NASA Langley Research Center Hampton, VA Operated by Universities Space Research Association National Aeronautics and Space Administration Langley Research Center Prepared for Langley Research Center under Contract NAS 1-97046 Hampton, Virginia 23681-2199 February 1998 Available from the following: NASA Center for AeroSpace Information (CASI) National Technical Information Service (NTIS) 800 Elkridge Landing Road 5285 Port Royal Road Linthicum Heights, MD 21090-2934 Springfield, VA 22161-2171 (301) 621-0390 (703) 487-4650 NUMERICAL STUDY OF INTERACTION OF A VORTICAL DENSITY INHOMOGENEITY WITH SHOCK AND EXPANSION WAVES A. POVITSKY * AND D. OFENGEIM t Abstract. We studied the interaction of a vortical density in_homogeneity (VDI) with shock and expan- sion waves. We call the VDI the region of concentrated vorticity (vortex) with a density different from that of ambiance. Non-parallel directions of the density gradient normal to the VDI surface and the pressure gradient across a shock wave results in an additional vorticity. The roll-up of the initial round VDI towards a non-symmetrical shape is studied numerically. Numerical modeling of this interaction is performed by a 2-D Euler code. The use of an adaptive unstructured numerical grid makes it possible to obtain high accuracy and capture regions of induced vorticity with a moderate overall number of mesh points. For the validation of the code, the computational results are compared with available experimental results and good agreement is obtained.
    [Show full text]
  • A Numerical Study of Postshock Oscillations in Slowly Moving Shock Waves
    View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by Elsevier - Publisher Connector An lntemattonnl Journal computers & mathematics withapplIcatIona PERGAMON Computers and Mathematics with Applications 46 (2003) 719-739 www.elsevier.com/locate/camwa A Numerical Study of Postshock Oscillations in Slowly Moving Shock Waves Y. STIRIBA* CERFACS/CFD Team, 42 Av. Gaspard Coriolis, 31057 Toulouse Cedex 1, France youssef.stiriba&erfacs.fr R. DONAT+ Dept. de Matem&ica Aplicada, Universidad de Valencia Dr. Moliner 50, 46100 Burjassot (Valencia), Spain donat@uv. es (Received May 2001; revised and accepted October 200.2) Abstract-Godunov-type methods and other shock capturing schemes can display pathological behavior in certain flow situations. This paper discusses the numerical anomaly associated to slowly moving shocks. We present a series of numerical experiments that illustrate the formation and propagation of this pathology, and allows us to establish some conclusions tid question some previous conjectures for the source of the numerical noise. A simple diagnosis on an explicit Steger-Warming scheme shows that some intermediate states in the first time steps deviate from the true direction and contaminate the flow structure. A remedy is presented in the form of a new flux split method with an entropy intermediate state that dissipates the oscillations to a numerically acceptable level, and fix or reduce a variety of numerical pathologies. @ 2003 Elsevier Ltd. All rights reserved. Keywords-Nonlinear systems of conservation laws, Shock capturing schemes, Flux split meth- ods, Slowly moving shocks, Compressible flows. 1. INTRODUCTION The phenomenon of postshock oscillations in slowly moving shock waves is a numerical anomaly that has attracted much attention in recent times [l-6].
    [Show full text]
  • Chapter Five NORMAL SHOCK WAVES
    Mech 448 QUEEN'S UNIVERSITY Faculty of Engineering and Applied Science Department of Mechanical Engineering MECH 448 Chapter Five COMPRESSIBLE FLUID FLOW NORMAL SHOCK WAVES 2011 NORMAL SHOCK WAVES Mech 448 Mech 448 The changes that occur through a normal shock wave, i.e., SHOCK WAVES: It has been found experimentally that, under a shock wave which is straight with the flow at right angles to the some circumstances, it is possible for an almost spontaneous wave, is shown in the following figure: change to occur in a flow, the velocity decreasing and the pressure increasing through this region of sharp change. The possibility that such a change can occur actually follows from the analysis given below. It has been found experimentally, and it also follows from the analysis given below, that such regions of sharp change can only occur if the initial flow is supersonic. The extremely thin region in which the transition from the supersonic velocity, relatively low pressure state to the state that involves a relatively low velocity and high pressure is termed a shock wave. Mech 448 Mech 448 A shock wave is extremely thin, the shock wave normally A photograph of a normal shock wave is shown in the only being a few mean free paths thick. A shock-wave is following figure: analogous in many ways to a “hydraulic-jump” that occurs in free-surface liquid flows, a hydraulic jump being shown schematically below. A hydraulic jump occurs, for example, in the flow downstream of a weir. 1 Mech 448 Mech 448 In the case of a normal shock wave, the velocities both A complete shock wave may be effectively normal in ahead (i.e.
    [Show full text]
  • Shock Wave Numerical Structure and the Carbuncle Phenomenon
    View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by Open Archive Toulouse Archive Ouverte Shock wave numerical structure and the carbuncle phenomenon Y. Chauvat, J.-M. Moschetta and J. Gressier∗ Department Models for Aerodynamics and Energetics { ONERA Ecole´ Nationale Sup´erieure de l'A´eronautique et de l'Espace 31400 Toulouse, France SUMMARY Since the development of shock-capturing methods, the carbuncle phenomenon has been reported to be a spurious solution produced by almost all currrently available contact-preserving methods. The present analysis indicates that the onset of carbuncle phenomenon is actually strongly related to the shock wave numerical structure. A matrix-based stability analysis as well as Euler finite volume computations are compared to illustrate the importance of the internal shock structure to trigger the carbuncle phenomenon. key words: carbuncle phenomenon, shock-capturing schemes, supersonic flows, Riemann solvers 1. INTRODUCTION Shock-capturing upwind methods developed since the 1980's can be classified into two distinct categories: 1. upwind methods which exactly preserve contact discontinuities (which might be referred to as contact-preserving methods), 2. upwind methods which introduce spurious diffusivity in the resolution of contact discontinuities. Schemes belonging to the second category never produce the carbuncle phenomenon but are hardly suitable for Navier-Stokes computations (e.g. Van Leer's method, see Fig. 3(a)) since they artificially broaden boundary layer profiles. On the other hand, schemes taken from the first category are attractive for viscous computations but turn out to be sensitive to the carbuncle phenomenon at various degrees [1] [2] with very few exceptions [3].
    [Show full text]
  • Shock Jump Relations for a Dusty Gas Atmosphere R K Anand
    Shock jump relations for a dusty gas atmosphere R K Anand Shock jump relations for a dusty gas atmosphere R. K. Anand Department of Physics, University of Allahabad, Allahabad-211002, India E-mail: [email protected] Abstract This paper presents generalized forms of jump relations for one dimensional shock waves propagating in a dusty gas. The dusty gas is assumed to be a mixture of a perfect gas and spherically small solid particles, in which solid particle are continuously distributed. The generalized jump relations reduce to the Rankine-Hugoniot conditions for shocks in an idea gas when the mass fraction (concentration) of solid particles in the mixture becomes zero. The jump relations for pressure, density, temperature, particle velocity, and change-in-entropy across the shock front are derived in terms of upstream Mach number. Finally, the useful forms of the shock jump relations for weak and strong shocks, respectively, are obtained in terms of the initial volume fraction of the solid particles. The computations have been performed for various values of mass concentration of the solid particles and for the ratio of density of solid particles to the constant initial density of gas. Tables and graphs of numerical results are presented and discussed. Key words Shock waves . Dusty gas . Solid particles . Shock jump relations . Mach number 1. Introduction Understanding the influence of solid particles on the propagation phenomena of shock waves and on the resulting flow field is of importance for solving many engineering problems in the field of astrophysics and space science research. When a shock wave is propagated through a gas which contains an appreciable amount of dust, the pressure, the temperature and the entropy change across the shock, and the other features of the flow differ greatly from those which arise when the shock passes through a dust-free gas.
    [Show full text]
  • Fluid Dynamics Android Application: an Efficient Semi-Implicit Solver For
    Preprints (www.preprints.org) | NOT PEER-REVIEWED | Posted: 27 October 2019 doi:10.20944/preprints201910.0309.v1 Fluid Dynamics Android Application: An Efficient Semi-implicit Solver for Compressible Flows Shivam Singhaly1, Yayati Gupta2, and Ashish Garg∗y3 1Department of Mechanical Engineering, Indian Institute of Technology Kharagpur 2Department of Computer Science & Engineering, Indian Institute of Information Technology Dharwad 3GATE Aerospace Forum Educational Services, Delhi-110059 Abstract: The computing power of smartphones has not received considerable attention in the mainstream education system. Most of the education-oriented smartphone applications (apps) are limited to general purpose services like Massive Open Online Courses (MOOCs), language learning, and calculators (performing basic mathematical calculations). Greater potential of smartphones lies in educators and researchers developing their customized apps for learners in highly specific domains. In line with this, we present Fluid Dynamics, a highly accurate Android application for measuring flow properties in compressible flows. This app can determine properties across the stationary normal and oblique shock, moving normal shock and across Prandtl − Meyer expansion fan. This app can also measure isentropic flows, Fanno flows, and Rayleigh flows. The functionality of this app is also extended to calculate properties in the atmosphere by assuming the International Standard Atmosphere (ISA) relations and also flows across the Pitot tube. Such measurements are complicated and time-consuming since the relations are implicit and hence require the use of numerical methods, which give rise to repetitive calculations. The app is an efficient semi-implicit solver for gas dynamics formulations and uses underlying numerical methods for the computations in a graphical user interface (GUI), thereby easing and quickening the learning of concerned users.
    [Show full text]
  • Numerical Simulations of Shock Wave Refraction at Inclined Gas Contact Discontinuity
    INTERNATIONAL JOURNAL OF ENVIRONMENTAL & SCIENCE EDUCATION 2016, VOL. 11, NO. 16, 9026-9038 OPEN ACCESS Numerical Simulations of Shock Wave Refraction at Inclined Gas Contact Discontinuity Pavel V. Bulata,b and Konstantin N. Volkovc aNational Research University of Information Technologies, Saint Petersburg, RUSSIA; bMechanics and Optics University ITMO, Saint Petersburg, RUSSIA; cKingston University, London, UNITED KINGDOM ABSTRACT When a shock wave interacts with a contact discontinuity, there may appear a reflected rarefaction wave, a deflected contact discontinuity and a refracted supersonic shock. The numerical simulation of shock wave refraction at a plane contact discontinuity separating gases with different densities is performed. Euler equations describing inviscid compressible flow were discretized using the finite volume method on unstructured meshes and WENO schemes. Time integration was performed using a third-order Runge– Kutta method. The wave structure resulting from regular shock refraction is determined allowing its properties to be explored. In order to visualize and interpret the results of numerical calculations, a procedure for identifying and classifying gas-dynamic discontinuities was applied. The procedure employed dynamic consistency conditions and digital image processing methods to determine flow structure and its quantitative characteristics. The results of the numerical and experimental visualizations were compared (shadow patterns, schlieren images, interferograms). The results computed are in an agreement
    [Show full text]
  • One Dimensional Waves
    • DECEMBER 2019 One Dimensional Waves Application of Shock-Expansion Theory – Lesson 4 Intro Into 1D Wave Motion • So far, we have examined shock and expansion waves generated by flows over objects. These waves are stationary in the object’s reference frame, and steady-state analysis can be applied to derive their relations. • In this lesson we will discuss propagation of transient shocks and expansion waves in one dimension. • We will also briefly outline propagation of small amplitude acoustic waves. • Finally, we will combine these elements of the transient wave theory in the classical Sod shock tube problem. 2 Moving Normal Shock Waves Stationary shock • The governing equations of a moving normal shock can be readily derived from those obtained for the stationary Gas motion shock using the following variables: 푢 푢 Gas motion downstream of 2 1 ‐ 푊 – velocity of the gas ahead of the shock relative to the upstream of shock, shock shock 2 1 ‐ 푊 − 푢푝 – velocity of the gas behind the shock relative to the shock Shock moving with velocity 푊 휌1푊 = 휌2(푊 − 푢푝) 2 Motion induced Stagnant gas 푝 + 휌 푊2 = 푝 + 휌 푊 − 푢 푢 > 0 푊 1 1 2 2 푝 by moving shock 푝 ahead of 2 shock ℎ2 + 1Τ2 푣 = ℎ1 + 1Τ2 푊 − 푢푝 2 1 • The Mach number of the shock is given by: 2 푀1 = 푊Τ푎1 where the speed of sound is: 푎1 = (푑푝Τ푑휌)1 3 Moving Normal Shock Waves • The “jump” relations developed for stationary normal shocks can be easily rewritten for the moving shock using the transformation equation from the previous slide.
    [Show full text]
  • Chapter Eleven/Normal Shock in Converging–Diverging Nozzles ------Chapter Eleven/Normal Shock in Converging–Diverging Nozzles
    UOT Mechanical Department / Aeronautical Branch Gas Dynamics Chapter Eleven/Normal shock in converging–diverging nozzles ------------------------------------------------------------------------------------------------------------------------------ -------------- Chapter Eleven/Normal shock in converging–diverging nozzles We have discussed the isentropic operations of a converging–diverging nozzle. This type of nozzle is physically distinguished by its area ratio, the ratio of the exit area to the throat area. Furthermore, its flow conditions are determined by the operating pressure ratio, the ratio of the receiver (back) pressure to the inlet stagnation (reservoir) pressure ( ⁄ ). From figure (11.1) we identified two significant critical pressure ratios. With , there is no flow in the nozzle (curve 1) from figure (11.1a). As is reduced below , subsonic flow is induced through the nozzle, with pressure decreasing to the throat, and then increasing in the diverging portion of the nozzle (curve 2 and 3).. For any pressure ratio above ⁄ , for curve (a), the nozzle is not choked and has subsonic flow throughout (typical venturi operation). When the back pressure is lowered to that of curve a, sonic flow occurs at the nozzle throat. Pressure ratio ⁄ is called the first critical point which represents flow that is subsonic in both the convergent and divergent sections but is choked with a Mach number of 1.0 in the throat. ((chocked means flow maximum and fixed)) When the back pressure is lowered to that of curve f, subsonic flow exits in the converging section, and sonic flow exits in the throat and it is choked where . A supersonic flow exists in the entire diverging section. This is the third critical point which represents the design operation condition.
    [Show full text]