DOCSLIB.ORG

An Experimental Investigation of Simultaneous Heat-Flux And

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
An Experimental Investigation of Simultaneous Heat-Flux And AIRFOIL, PLATFORM, AND COOLING PASSAGE MEASUREMENTS ON A ROTATING TRANSONIC HIGH-PRESSURE TURBINE DISSERTATION Presented in Partial Fulfillment of the Requirements for the Degree Doctor of Philosophy in the Graduate School of The Ohio State University By Jeremy B. Nickol, M.S. Graduate Program in Mechanical Engineering The Ohio State University 2016 Dissertation Committee: Professor Randall M. Mathison, Advisor Professor Michael G. Dunn, Co-Advisor Professor Sandip Mazumder Professor Jeffrey P. Bons Copyright by Jeremy B Nickol 2016 ABSTRACT An experiment was performed at The Ohio State University Gas Turbine Laboratory for a film-cooled high-pressure turbine stage operating at design-corrected conditions, with variable rotor and aft purge cooling flow rates. Several distinct experimental programs are combined into one experiment and their results are presented. Pressure and temperature measurements in the internal cooling passages that feed the airfoil film cooling are used as boundary conditions in a model that calculates cooling flow rates and blowing ratio out of each individual film cooling hole. The cooling holes on the suction side choke at even the lowest levels of film cooling, ejecting more than twice the coolant as the holes on the pressure side. However, the blowing ratios are very close due to the freestream massflux on the suction side also being almost twice as great. The highest local blowing ratios actually occur close to the airfoil stagnation point as a result of the low freestream massflux conditions. The choking of suction side cooling holes also results in the majority of any additional coolant added to the blade flowing out through the leading edge and pressure side rows. A second focus of this dissertation is the heat transfer on the rotor airfoil, which features uncooled blades and blades with three different shapes of film cooling hole: cylindrical, diffusing fan shape, and a new advanced shape. Shaped cooling holes have ii previously shown immense promise on simpler geometries, but experimental results for a rotating turbine have not previously been published in the open literature. Significant improvement from the uncooled case is observed for all shapes of cooling holes, but the improvement from the round to more advanced shapes is seen to be relatively minor. The reduction in relative effectiveness is likely due to the engine-representative secondary flow field interfering with the cooling flow mechanics in the freestream, and may also be caused by shocks and other compressibility effects within the cooling holes which are not present in low speed experiments. Another major focus of this work is on the forward purge cavity and rotor and stator inner endwalls. Pressure and heat transfer measurements are taken at several locations, and compared as both forward and aft purge flow rates are varied. It is seen that increases in forward purge rates result in a flow blockage and greater pressure on the endwalls both up and downstream of the cavity. Thus, even in locations where the coolant does not directly cover the metal surface, it can have a significant impact on the local pressure loading and heat transfer rate. The heat transfer on the platform further downstream, however, is unchanged by variations in purge flow rates. iii Dedicated to my mother, for instilling my love of learning, and to my father, for creating my obsession with how things work iv ACKNOWLEDGEMENTS This research was partially funded by the Aviation Applied Technology Directorate under Agreement No. W911W6-08-2-0011 and partially funded by the Federal Aviation Administration under Agreement No. DTFAWA-10-C-00040. The U.S. Government is authorized to reproduce and distribute reprints for Government purposes notwithstanding any copyright notation thereon. The views and conclusions contained in this document are those of the authors and not should not be interpreted as representing the official policies, either expressed or implied, of the Aviation Applied Technology Directorate, the Federal Aviation Administration, or the U.S. Government. Approved for public release: distribution is unlimited. First I would like to thank my original advisor, Professor Michael G. Dunn, for first giving me the opportunity to work in The Ohio State University Gas Turbine Laboratory, providing me with four years of financial support through a Graduate Research Associateship, and paying for me to attend conferences in San Antonio, Düsseldorf, Phoenix, and Seoul. Your door has always been open to me, and I can’t count the times you’ve explained something to me, or helped me see the big picture when bogged down with insignificant details. I’ll also miss our Monday-morning quarterbacking, discussions on the relative merits of flat plates, and all of your great stories and one-liners. It has not v only been an honor to work for you for five years, but also a great pleasure. “I haven’t had this much fun since the hogs ate my sister!” Second I’d like to thank my advisor Dr. Randall Mathison. You’ve been my main mentor since I first arrived, teaching me not only the specific processes and systems in place at the GTL, but answering my questions about gas turbine operation and theory, and general engineering and aviation principles as well. You’ve been a great resource to bounce ideas off of, and have always been willing to take the time to point me in the right direction when I got stuck. I would also like to thank the other two professors on my dissertation committee: Dr. Sandip Mazumder, and Dr. Jeff Bons. In addition to serving on my committee, they have been two of the best teachers I have had the privilege of learning from. I would also like to thank Honeywell Engines in Phoenix, Arizona for their continued support of me and this project. Honeywell provided the majority of the engine hardware utilized for this work, as well as much of the funding. In particular, I would like to thank Jong Liu, Kuo-San Ho, and Benjamin Kamrath for performing the CFD computation that is used in this dissertation, Rajiv Rana for extensive work in the design of the experiment, Malak Malak for management of the project, and Mark Morris for many thoughtful comments and contributions. Thanks also go to fellow graduate student Matt Tomko for performing much of the early analysis on the pressure data in the purge cavity, providing me with a good foundation from which to work. vi This dissertation would not have been possible without the technical expertise of Jeff Barton, Dr. Igor Ilyin, Ken Fout, and Jonny Lutz in the design, building, and instrumenting of the experiment. Additionally, thanks to Josh Guith for assisting me in the machine shop on more than one occasion, and undergraduate research assistants Chris Cosher, Kevin McManus, Eric Barbe, Miles Reagans, and Richard Celestina for help with the many miscellaneous tasks associated with the experiment. I am also grateful for the administrative assistance I received. Thanks to Cathy Mitchell, and Steve Pruchnicki for assistance out here at the GTL with purchasing and travel authorization and reimbursement. Janeen Sands was also instrumental for helping me to cut through the red tape and answering my countless questions about the convoluted processes and copious paperwork required to do anything at this University. This dissertation is just one in a long line of works on rotating turbine stages presented by previous graduate students at the Gas Turbine Laboratory. While I have never actually met most of them, I am indebted to countless former GTL graduate students, particularly Dr. Charlie Haldeman, James Murphy, Brian Cohen, Dr. Randy Mathison, Dr. Brian Green, and Dr. Matt Smith for performing previous work that helped lay the groundwork for this experiment, and for learning a number of lessons the hard way so I wouldn’t have to. Despite the overall good experience that working in the GTL has been, I would have gone crazy long before reaching this point had it not been for the many friends that I met along the way. Thanks go to Sanjay Ramdon, Shauna Adams, Imani Adams, Steven vii Ramirez, Arvind Mohan, Bingya Li, Jiazheng Hong, Venkata Subramanian, Yibo Shao, Xiao Wu, Emily Dreyer, Ben Grier, Anna Wu, and Soohyun Im for helping me to escape work when I needed to. Further thanks go to the friends that surrounded me at work every day. Through academic and intellectual discussions, tea breaks, Friday lunches, debugging expeditions, mutual complaining sessions, football arguments, lab cricket, and after-work drinks, I owe my sanity and perseverance to having you guys around me every day. Thanks to Alex Habib, Jonny Lutz, Anshuman Pandey, Chris Cosher, Hannah Pier, Tim Lawler, Matt Tomko, Kiran D’Souza, Miles Reagans, Richard Celestina, Eric Kurstak, and Meng- Hsuan Tien for the countless distractions, conversations, lessons, and for being awesome friends and colleagues. viii VITA January 3, 1990 ..............................................Born—Mayfield Heights, Ohio May 2011 .......................................................B.S. Mechanical Engineering, Rose-Hulman Institute of Technology May 2013 .......................................................M.S. Mechanical Engineering, The Ohio State University October 2011-Present.....................................Graduate Research Associate, The Ohio State University Gas Turbine Lab PUBLICATIONS Nickol, J.B., Mathison, R.M., Malak, M.F., Rana, R., Liu, J.S., 2015, "Time-Resolved Heat Transfer and Surface Pressure Measurements for a Fully Cooled Transonic Turbine Stage", ASME J. Turbomach, 137(9), pp. 091009. Nickol, J.B., Mathison, R.M., Dunn, M.G., 2014, "Heat-Flux Measurements for a Realistic Cooling Hole Pattern With Multiple Flow Conditions", ASME J. Turbomach, 136(3), pp. 031010. Nickol, J.B., Mathison, R.M., Dunn, M.G., Liu, J.S., Malak, M.F., 2016, "Unsteady Heat Transfer and Pressure Measurements on the Airfoil of a Rotating Transonic Turbine with Multiple Cooling Configurations", ASME Turbo Expo 2016, Seoul, Republic of Korea, ASME Paper No.
Load more

Recommended publications
  • Chapter 5 Dimensional Analysis and Similarity
    Chapter 5 Dimensional Analysis and Similarity Motivation. In this chapter we discuss the planning, presentation, and interpretation of experimental data. We shall try to convince you that such data are best presented in dimensionless form. Experiments which might result in tables of output, or even mul- tiple volumes of tables, might be reduced to a single set of curves—or even a single curve—when suitably nondimensionalized. The technique for doing this is dimensional analysis. Chapter 3 presented gross control-volume balances of mass, momentum, and en- ergy which led to estimates of global parameters: mass flow, force, torque, total heat transfer. Chapter 4 presented infinitesimal balances which led to the basic partial dif- ferential equations of fluid flow and some particular solutions. These two chapters cov- ered analytical techniques, which are limited to fairly simple geometries and well- defined boundary conditions. Probably one-third of fluid-flow problems can be attacked in this analytical or theoretical manner. The other two-thirds of all fluid problems are too complex, both geometrically and physically, to be solved analytically. They must be tested by experiment. Their behav- ior is reported as experimental data. Such data are much more useful if they are ex- pressed in compact, economic form. Graphs are especially useful, since tabulated data cannot be absorbed, nor can the trends and rates of change be observed, by most en- gineering eyes. These are the motivations for dimensional analysis. The technique is traditional in fluid mechanics and is useful in all engineering and physical sciences, with notable uses also seen in the biological and social sciences.
    [Show full text]
  • Archives of Thermodynamics
    POLISH ACADEMY OF SCIENCES THERMODYNAMICS AND COMBUSTION COMMITTEE archives of thermodynamics QUARTERLY Vol. 38 2017 Wydawnictwo IMP No. 3 Gdańsk Editorial Office Archives of Thermodynamics The Szewalski Institute of Fluid Flow Machinery, Fiszera 14, 80-231 Gdańsk, Poland, Tel.: (+48) 58-341-12-71 int. 141, E-mail: [email protected] http://www.imp.gda.pl/archives-of-thermodynamics/ http://at.czasopisma.pan.pl/ © by the Polish Academy of Science Publication funding of this journal is provided by resources of the Polish Academy of Sciences and the Szewalski Institute of Fluid-Flow Machinery PASci Terms of subscription outside Poland Annual subscription rate outside Poland (2017) is 120 EUR. Price of single issue is 30 EUR. Back of previously published volumes are available on request. Subscription orders should be sent directly to IMP PAN Publishers, The Szewalski Institute of Fluid-Flow Machinery PASci, ul. Fiszera 14, 80-231 Gdansk, Poland; fax: (+48) 58-341-61-44; e-mail: [email protected]. Payments should be transferred to the bank account of IMP PAN: IBAN 28 1130 1121 0006 5498 9520 0011 at Bank Gospo- darstwa Krajowego; Code SWIFT: GOSKPLPW Warunki prenumeraty w Polsce Roczna prenumerata (2017 r.) wynosi 168 PLN. Cena pojedynczego numeru wynosi 42 PLN. Osiągalne są również wydania archiwalne. Zamówienia z określeniem okresu prenumeraty, nazwiskiem i adresem odbiorcy należy kierować bezpośrednio do Wydawcy (Instytut Maszyn Przepływowych im. R. Szewalskiego PAN, ul. Fiszera 14, 80-231 Gdańsk, Aleksandra Nowaczewska, e-mail: [email protected]).
    [Show full text]
  • Summary of Dimensionless Numbers of Fluid Mechanics and Heat Transfer 1. Nusselt Number Average Nusselt Number: Nul = Convective
    Jingwei Zhu http://jingweizhu.weebly.com/course-note.html Summary of Dimensionless Numbers of Fluid Mechanics and Heat Transfer 1. Nusselt number Average Nusselt number: convective heat transfer ℎ퐿 Nu = = L conductive heat transfer 푘 where L is the characteristic length, k is the thermal conductivity of the fluid, h is the convective heat transfer coefficient of the fluid. Selection of the characteristic length should be in the direction of growth (or thickness) of the boundary layer; some examples of characteristic length are: the outer diameter of a cylinder in (external) cross flow (perpendicular to the cylinder axis), the length of a vertical plate undergoing natural convection, or the diameter of a sphere. For complex shapes, the length may be defined as the volume of the fluid body divided by the surface area. The thermal conductivity of the fluid is typically (but not always) evaluated at the film temperature, which for engineering purposes may be calculated as the mean-average of the bulk fluid temperature T∞ and wall surface temperature Tw. Local Nusselt number: hxx Nu = x k The length x is defined to be the distance from the surface boundary to the local point of interest. 2. Prandtl number The Prandtl number Pr is a dimensionless number, named after the German physicist Ludwig Prandtl, defined as the ratio of momentum diffusivity (kinematic viscosity) to thermal diffusivity. That is, the Prandtl number is given as: viscous diffusion rate ν Cpμ Pr = = = thermal diffusion rate α k where: ν: kinematic viscosity, ν = μ/ρ, (SI units : m²/s) k α: thermal diffusivity, α = , (SI units : m²/s) ρCp μ: dynamic viscosity, (SI units : Pa ∗ s = N ∗ s/m²) W k: thermal conductivity, (SI units : ) m∗K J C : specific heat, (SI units : ) p kg∗K ρ: density, (SI units : kg/m³).
    [Show full text]
  • Heat and Mass Correlations
    Heat and Mass Correlations Alexander Rattner, Jonathan Bohren November 13, 2008 Contents 1 Dimensionless Parameters 2 2 Boundary Layer Analogies - Require Geometric Similarity 2 3 External Flow 3 3.1 External Flow for a Flat Plate . 3 3.2 Mixed Flow Over a plate . 4 3.3 Unheated Starting Length . 4 3.4 Plates with Constant Heat Flux . 4 3.5 Cylinder in Cross Flow . 4 3.6 Flow over Spheres . 5 3.7 Flow Through Banks of Tubes . 6 3.7.1 Geometric Properties . 6 3.7.2 Flow Correlations . 7 3.8 Impinging Jets . 8 3.9 Packed Beds . 9 4 Internal Flow 9 4.1 Circular Tube . 9 4.1.1 Properties . 9 4.1.2 Flow Correlations . 10 4.2 Non-Circular Tubes . 12 4.2.1 Properties . 12 4.2.2 Flow Correlations . 12 4.3 Concentric Tube Annulus . 13 4.3.1 Properties . 13 4.3.2 Flow Correlations . 13 4.4 Heat Transfer Enhancement - Tube Coiling . 13 4.5 Internal Convection Mass Transfer . 14 5 Natural Convection 14 5.1 Natural Convection, Vertical Plate . 15 5.2 Natural Convection, Inclined Plate . 15 5.3 Natural Convection, Horizontal Plate . 15 5.4 Long Horizontal Cylinder . 15 5.5 Spheres . 15 5.6 Vertical Channels . 16 5.7 Inclined Channels . 16 5.8 Rectangular Cavities . 16 5.9 Concentric Cylinders . 17 5.10 Concentric Spheres . 17 1 JRB, ASR MEAM333 - Convection Correlations 1 Dimensionless Parameters Table 1: Dimensionless Parameters k α Thermal diffusivity ρcp τs Cf 2 Skin Friction Coefficient ρu1=2 α Le Lewis Number - heat transfer vs.
    [Show full text]
  • A Similarity Analysis for Heat Transfer in Newtonian and Power Law Fluids Using the Instantaneous Wall Shear Stress
    A Similarity Analysis for Heat Transfer in Newtonian and Power Law Fluids Using the Instantaneous Wall Shear Stress Trinh, Khanh Tuoc [email protected] B.H.P. Wilkinson [email protected] Institute of Food Nutrition and Human Health Massey University, New Zealand N.K.Kiaka [email protected] Department of Applied sciences The Papua New Guinea University of technology Abstract This paper presents a technique that collapses existing experimental data of heat transfer in pipe flow of Newtonian and power law fluids into a single master curve. It also discusses the theoretical basis of heat, mass and momentum analogies and the implications of the present analysis to visualisations of turbulence. Key words: Heat transfer, transition, turbulence, Newtonian, power law, instantaneous wall shear stress, similarity plot 1 Introduction The study of heat and mass transfer has been dominated from an early stage by the similar form of the equations of heat, mass and momentum. Following Boussinesq (1877), the transport flux (e.g. of heat) can be defined in terms of an eddy viscosity d q k E (1) h dy where is the temperature y the normal distance from the wall k the thermal conductivity Eh the eddy thermal diffusivity q the rate of heat transfer flux the fluid density Equation (1) may be rearranged as y q q w dy (2) E 0 1 h k which is very similar to the equation for momentum transport y U w dy (3) E 0 1 Where U U u* , y yu* yu* and Cp w u* q w have been normalised with the friction velocity u* w and the fluid apparent viscosity .
    [Show full text]
  • On Dimensionless Numbers
    chemical engineering research and design 8 6 (2008) 835–868 Contents lists available at ScienceDirect Chemical Engineering Research and Design journal homepage: www.elsevier.com/locate/cherd Review On dimensionless numbers M.C. Ruzicka ∗ Department of Multiphase Reactors, Institute of Chemical Process Fundamentals, Czech Academy of Sciences, Rozvojova 135, 16502 Prague, Czech Republic This contribution is dedicated to Kamil Admiral´ Wichterle, a professor of chemical engineering, who admitted to feel a bit lost in the jungle of the dimensionless numbers, in our seminar at “Za Plıhalovic´ ohradou” abstract The goal is to provide a little review on dimensionless numbers, commonly encountered in chemical engineering. Both their sources are considered: dimensional analysis and scaling of governing equations with boundary con- ditions. The numbers produced by scaling of equation are presented for transport of momentum, heat and mass. Momentum transport is considered in both single-phase and multi-phase flows. The numbers obtained are assigned the physical meaning, and their mutual relations are highlighted. Certain drawbacks of building correlations based on dimensionless numbers are pointed out. © 2008 The Institution of Chemical Engineers. Published by Elsevier B.V. All rights reserved. Keywords: Dimensionless numbers; Dimensional analysis; Scaling of equations; Scaling of boundary conditions; Single-phase flow; Multi-phase flow; Correlations Contents 1. Introduction .................................................................................................................
    [Show full text]
  • Radiation and Chemical Reaction Effects on Thermophoretic MHD Flow Over an Aligned Isothermal Permeable Surface with Heat Source
    Chemical and Process Engineering Research www.iiste.org ISSN 2224-7467 (Paper) ISSN 2225-0913 (Online) Vol.31, 2015 Radiation and Chemical Reaction Effects on Thermophoretic MHD Flow over an Aligned Isothermal Permeable Surface with Heat Source C S K Raju 1 N.Sandeep 1* M.Jayachandra Babu 1 V.Sugunamma 2 1.Department of Mathematics, VIT University, Vellore (T.N.) - 632014, India 2.Department of Mathematics, Sri Venkateswara University, Tirupati (A.P.) -517502, India E-mail: [email protected] Abstract Radiation and chemical reaction effects on thermophoretic MHD flow over an inclined isothermal permeable surface in presence of heat generation/absorption, viscous dissipation is analyzed numerically. The governing equations are reduced to nonlinear ordinary differential equations by using similarity transformation and then solved numerically using bvp4c solver with MATLAB Package. The effects of governing parameters on dimensionless quantities like velocity, temperature, concentration, skin friction, wall heat flux and wall deposition flux are discussed for both suction and injection cases. Results are presented graphically and through tables. Keywords: Magnetohydrodynamics, Thermophresis, Radiation, Dissipation, Heat source. 1. Introduction Thermophoresis has potential applications like air cleaning, aerosol particles sampling, nuclear reactor safety, micro electronics manufacturing etc. Thermophoresis describes the migration of suspended small micron sized particles in a non isothermal gas to the direction with decreasing thermal gradient and the velocity acquired by the particle is known as thermophoretic velocity. The detailed discussion about this study was given by (Derjaguin and Yalamov, 1965). Thermophoresis of aerosol particles in laminar boundary layer on flat plate was analyzed by (Goren, 1977). Thermophoretic hydromagnetic flow over radiate isothermal inclined plate by considering heat source was discussed by (Noor et.al, 2013).
    [Show full text]
  • The Turbulent Boundary Layer: Experimental Heat Transfer with Strong Favorable Pressure Gradients and Blowing
    THE TURBULENT BOUNDARY LAYER: EXPERIMENTAL HEAT TRANSFER WITH STRONG FAVORABLE PRESSURE GRADIENTS AND BLOWING By D. W. Kearney, R. J. Moffat and W. M. Kays Report No. HTMT-12 Prepared Under Grant NASA JGi--0"5-020-134 for The National Aeronautics and Space Administration (ACCESSION NUMBER) T RU) (CDE) V 0 ' (NASA c1 OR TMX OR NUMBER) 4pY Thermpsciences Division Deparime tof Mechanical Engineering vStanford University Stanford, California April 1970 Reproduced by NATIONAL TECHNICAL I INFORMATION SERVICE U S Departmnt f Commerce -- - - Springfield-- VA 22151 THE TURBULENT BOUNDARY LAYER: EXPERIMENTAL HEAT TRANSFER WITH STRONG FAVORABLE PRESSURE GRADIENTS AND BLOWING By D. W. Kearney, R. J. Moffat and W. M. Kays Report No. HMT-12 Prepared Under Grant NASA NGL-05-020-134 for The National Aeronautics and Space Administration Thermosciences Division Department of Mechanical Engineering Stanford University Stanford,California April 1970 fBgE0IOPAGE .- BSANK NOT FILMED. ACKNOWLEDGMENTS This research was made possible through grants from the National Science Foundation, NSF GK 2201, and the National Aeronautics and Space Administration, NGL 0,5-020-134. The authors wish to express appreciation for the interest of Dr. Royal E. Rostenbach of NSF, and Dr. Robert W. Graham of NASA Lewis Laboratories. The cooperation of R. J. Loyd throughout the experi­ mental program was a necessary factor in its success. The assistance of B. Blackwell and P. Andersen in part of the testing is appreciated. Special credit is due Miss Jan Elliott for her timely and competent handling of the publi­ cation process. iii ABSTRACT Heat transfer experiments have been carried out in air on a turbulent boundary layer subjected to a strongly accelerated free-stream flow, with and without surface transpiration.
    [Show full text]
  • The Pennsylvania State University the Graduate School College of Engineering IMPLEMENTATION of HIGH FST TURBULENT KINETIC ENERGY
    The Pennsylvania State University The Graduate School College of Engineering IMPLEMENTATION OF HIGH FST TURBULENT KINETIC ENERGY DIFFUSION MODEL IN OPENFOAM CODE FOR SIMULATION OF HEAT TRANSFER OVER A GAS TURBINE BLADE A Thesis in Mechanical Engineering by Vedant Chittlangia © 2017 Vedant Chittlangia Submitted in Partial Fulfillment of the Requirements for the Degree of Master of Science December 2017 The thesis of Vedant Chittlangia was reviewed and approved∗ by the following: Savas Yavuzkurt Professor of Mechanical Engineering Thesis Advisor, Chair of Committee Anil Kulkarni Professor of Mechanical Engineering Thesis Reader Karen Thole Distinguished Professor of Mechanical Engineering Head of the Department of Mechanical Engineering ∗Signatures are on file in the Graduate School. ii Abstract Several low-Reynolds number turbulence models are compared for their performance to predict the effect of free-stream turbulence on skin friction coefficient and Stanton number. Initial ef- forts were made to implement a turbulent kinetic energy diffusion model in FLUENT but due to unavailability of the source code the focus was shifted to OpenFOAM, an open-source CFD software. Effect of initial values of free-stream parameters is studied on a flat plate. Launder- Sharma model is modified to account for the effect of free-stream turbulence and length scale by incorporating variable cµ and an additional diffusion term in turbulent kinetic energy trans- port equation. Comprehensive study is carried for better predictions of skin friction coefficient, Stanton number and turbulent kinetic energy profile on a flat plate for different initial turbulent intensities of 1%, 6.53% and 25.7%. The new model is validated for its better performance on a flat plate to predict Stanton number, skin friction coefficient and turbulent kinetic energy profile with close match to the data points.
    [Show full text]
  • An Investigation of Heat Transfer Within Regions of Separated Flow at a Mach Number of 6.0
    NASA TECHNICAL NOTE AN INVESTIGATION OF HEAT TRANSFER WITHIN REGIONS OF SEPARATED FLOW AT A MACH NUMBER OF 6.0 by Paul F. HoZZoway, James Re Sterrett, and Helen S. Creekmore Langley Research Center Lungley Station, Hampton, Va, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION - WASHINGTON, D. C. I TECH LIBRARY KAFB, NY AN INVESTIGATION OF HEAT TRANSFER WITHIN REGIONS OF SEPARATED FLOW AT A MACH NUMBER OF 6.0 By Paul F. Holloway, James R. Sterrett, and Helen S. Creekmore Langley Research Center Langley Station, Hampton, Va. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION For sale by the Clearinghouse for Federal Scientific and Technical Information Springfield, Virginia 22151 - Price $3.00 AN INVESTIGATION OF HEAT TRANSFEZ WITHIN REGIONS OF SEPARATED now AT A MACH NUMBER OF 6.0 By Paul F. Holloway, James R. Sterrett, and Helen S. Creekmore LEtngley Research Center An extensive systematic investigation of the heat transfer associated wlth 1 regions of laminar, transitional, and turbulent separation has been conducted on sharp- and blunt-leading-edge flat plates at a Mach number of 6.0 over a free-stream unit Reynolds number range of approximately 1 x lo6 to 8 x lo6 per foot. Separated regions were forced by forward- and rearward-facing steps, and by loo, 20°, 30°, and 40° wedges located in several longitudinal positions on the plate. It has been shown that upon proper classification of the several types of separated flow, the trends of the heating rates within the regions of separa- tion may be characterized by typical distributions which are essentially inde- pendent of the model geometry (except to the extent that the model-geometry variations affect the location of transition).
    [Show full text]
  • Computational Characterization of Shock Wave
    Iowa State University Capstones, Theses and Graduate Theses and Dissertations Dissertations 2018 Computational characterization of shock wave - boundary layer Interactions on flat plates and compression ramps in laminar, hypersonic flow Eli Ray Shellabarger Iowa State University Follow this and additional works at: https://lib.dr.iastate.edu/etd Part of the Aerospace Engineering Commons Recommended Citation Shellabarger, Eli Ray, "Computational characterization of shock wave - boundary layer Interactions on flat plates and compression ramps in laminar, hypersonic flow" (2018). Graduate Theses and Dissertations. 16465. https://lib.dr.iastate.edu/etd/16465 This Thesis is brought to you for free and open access by the Iowa State University Capstones, Theses and Dissertations at Iowa State University Digital Repository. It has been accepted for inclusion in Graduate Theses and Dissertations by an authorized administrator of Iowa State University Digital Repository. For more information, please contact [email protected]. Computational characterization of shock wave { boundary layer interactions on flat plates and compression ramps in laminar, hypersonic flow by Eli R. Shellabarger A thesis submitted to the graduate faculty in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE Major: Aerospace Engineering Program of Study Committee: Thomas Ward, Major Professor Richard Wlezien Peng Wei The student author, whose presentation of the scholarship herein was approved by the program of study committee, is solely responsible for the content of this thesis. The Graduate College will ensure this thesis is globally accessible and will not permit alterations after a degree is conferred. Iowa State University Ames, Iowa 2018 Copyright c Eli R. Shellabarger, 2018.
    [Show full text]
  • Fluid Numbers
    Fluid Numbers Dimensieloze Navier-Stokes “ ” Froude “ ” “For a ship, the Froude number is defined as: where v is the velocity of the ship, g is the acceleration due to gravity, and L is the length of the ship at the water line level, or Lwl in some notations. It is an important parameter with respect to the ship's drag, or resistance, including the wave making resistance. Note that the Froude number used for ships, by convention, is the square root of the Froude number as defined above.” pag 1 Euler “ ” Reynolds “Reynolds number can be defined for a number of different situations where a fluid is in relative motion to a surface. These definitions generally include the fluid properties of density and viscosity, plus a velocity and a characteristic length or characteristic dimension. This dimension is a matter of convention – for example a radius or diameter are equally valid for spheres or circles, but one is chosen by convention. For aircraft or ships, the length or width can be used. For flow in a pipe or a sphere moving in a fluid the internal diameter is generally used today. Other shapes such as rectangular pipes or non-spherical objects have an equivalent diameter defined. For fluids of variable density such as compressible gases or fluids of variable viscosity such as non-Newtonian fluids, special rules apply. The velocity may also be a matter of convention in some circumstances, notably stirred vessels. The inertial forces, which characterize how much a particular fluid resists any change in motion are not to be confused with inertial forces defined in the classical way.” Invloed van de stromingstoestand: Stroming in leiding onder druk Stroming met vrij oppervlak Stroming rond een lichaam pag 2 Weber “ ” “The Weber number is a dimensionless number in fluid mechanics that is often useful in analysing fluid flows where there is an interface between two different fluids, especially for multiphase flows with strongly curved surfaces.
    [Show full text]