AIAA Receptivity to Freestream Disturbances of a Mach 10 Nonequilibrium Reacting Oxygen Flow over A Flat Plate
|
|
|
- Henry Cameron
- 5 years ago
- Views:
Transcription
1 42nd AIAA Aerospace Sciences Meeting and Exhibit 5-8 January 2004, Reno, Nevada AIAA AIAA Receptivity to Freestream Disturbances of a Mach 0 Nonequilibrium Reacting Oxygen Flow over A Flat Plate Yanbao Ma and Xiaolin Zhong University of California, Los Angeles January 5 8, 2004 / Reno, NV For permission to copy or republish, contact the American Institute of Aeronautics and Astronautics 80 Alexander Bell Drive, Suite 500, Reston, Virginia Copyright 2004 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
2
3
4
5
6
7
8
9
10
11
12 8.0 T / T 5.0 T (perfect gas) T (nonequilibrium flow) T v (nonequilibrium flow) 0.0 M 9.5 M 2 (perfect gas) M 2 (nonequilibrium flow) Shock position (perfect gas) Shock position (nonequilibrium flow) y / L u / u p / p Perfect gas Nonequilibrium flow.8.6 Perfect gas Nonequilibrium flow y / L.0 T / T p / p.8.6 Perfect gas Nonequilibrium flow 4.0 Perfect gas Nonequilibrium flow (T) Nonequilibrium flow (T v ) y / L
13 C o a / u. mode I () (F = 5.0e-5) mode I (2) (F = 5.0e-5) Mack modes (F = 5.0e-5) mode I () (F = 3.98e-5) mode I (2) (F = 3.98e-5) Mack modes (F = 3.98e-5) + M 0.04 st mode 2nd mode M ω 0.06 C o 0.00 α i mode I () (F = 5.0e-5) mode I (2) (F = 5.0e-5) Mack modes (F = 5.0e-5) mode I () (F = 3.98e-5) mode I (2) (F = 3.98e-5) Mack modes (F = 3.98e-5) + M M y / L st mode 2nd mode ω F 5.0E-4 4.0E-4 3.0E-4 F = 0.825e-4 F = 0.5e-4 4.0E E-04 n= n= 2 n= 3 n= 4 n= 5 2.0E-4 2.0E-04.0E-4.0E E R
14 3.2E E E-03 n= 6 n= 7 n= 8 n= 9 n=0 4.5E-04 n= 6 n= 7 n= 8 n= 9 n=0.6e E E-04.5E-04.6E-03.2E-03 n= n=2 n=3 n=4 n=5 2.8E-04 n= n=2 n=3 n=4 n=5 2.E E-04.4E E E E-04.5E-04 n= n= 2 n= 3 n= 4 n= 5 a / u.2 LST (mode I ()) LST (Mack modes) Simulation (Mack modes) Simulation (mode I). + M.0E-04 st mode 5.0E M 0.8
15 a / u.2 LST (mode I ()) LST (mode I (2)) LST (Mack modes) Simulation (Mack modes) Simulation (mode I). + M 8.0E E-04 Fast acoustic waves (θ = 0) Perfect gas ( j = ) Nonequilibrium flow ( j = ) Perfect gas ( j = 2 ) Nonequilibrium flow ( j = 2 ) 3.0E E-03 Slow acoustic waves (θ = 0) Perfect gas ( j = ) Nonequilibrium flow ( j = ) Perfect gas ( j = 2 ) Nonequilibrium flow ( j = 2 ) st mode 2nd mode 4.0E M 2.0E-04.0E (a) (b).2 LST (mode I ()) LST (mode I (2)) LST (Mack modes) LST (mode II) Simulation (Mack modes) Simulation (mode I). a / u + M.2 a / u. Fast acoustic waves (θ = 0) LST (mode I ()) LST (mode I (2)) LST (Mack modes) DNS (perfect gas) DNS (nonequilibrium flow) + /M.2 a / u. Slow acoustic waves (θ = 0) LST (mode I ()) LST (mode I (2)) LST (Mack modes) DNS (perfect gas) DNS (nonequilibrium flow) + /M st mode 2nd mode st mode 2nd mode 2nd mode M /M 0.9 -/ M 0.8 (a) 0.8 (b) E-03 α i.0e-03 LST (n = 8) LST (n = 8) LST (n = 8) DNS (n = 8) DNS (n = 0) DNS (n = 5) 36.0 u u r (Simulation) 8.0 u i (Simulation) u r (2nd mode, LST) u i (2nd mode, LST) y / L20 (a) 30.0 v v r (Simulation) 20.0 v i (Simulation) v r (2nd mode, LST) 0.0 v i (2nd mode, LST) y / L20 (b).5 p p r (Simulation) p i (Simulation) p r (2nd mode,lst) p i (2nd mode,lst) 8E3 T 4E3 0E0 T r (Simulation) T i (Simulation) T r (2nd mode,lst) T i (2nd mode, LST) -.0E y / L20 (c) -4E y / L20 (d) -2.0E-03
16 7.5E E-04 Fast acoustic waves (perfect gas) θ = 0 o θ = 22.5 o θ = 45 o θ = 67.5 o 7.5E E-04 Fast acoustic waves (nonequilibrium flow) θ = 0 o θ = 22.5 o θ = 45 o θ = 67.5 o.6e-03.2e E-04 Fast acoustic waves (pefect gas) n= n= 2 n= 3 n= 4 n= 5.6E-03.2E E-04 Fast acoustic waves (nonequilibrium flow) 2.5E (a) E (b) 4.0E-04 (a) 4.0E-04 n= n= 2 n= 3 n= 4 n= 5 (b).5e-03.0e-03 Slow acoustic waves (perfect gas) θ = 0 o θ = 22.5 o θ = 45 o θ = 67.5 o 2.4E-03.8E-03 Slow acoustic waves (nonequilibrium flow) θ = 0 o θ = 22.5 o θ = 45 o θ = 67.5 o.6e-03.2e-03 Fast acoustic waves (pefect gas) n= 6 n= 7 n= 8 n= 9 n=0.6e-03.2e-03 Fast acoustic waves (nonequilibrium flow) n= 6 n= 7 n= 8 n= 9 n=0.2e E E E E E E-04 (a) (b) (c) (d) 5 Response coefficient (K s ) 0 5 Receptivity to slow acoustic waves Perfect gas Noequibrium flow 6.0E E E-04 Fast acoustic waves (pefect gas) n= n=2 n=3 n=4 n=5 6.0E E E-04 Fast acoustic waves (nonequilibrium flow) n= n=2 n=3 n=4 n=5.5e-04.5e θ (degree) (e) (f)
17 .5E-03 Slow acoustic waves (pefect gas).5e-03 Slow acoustic waves (nonequilibrium flow).0e-03.0e-03 n= n= 2 n= 3 n= 4 n= 5 5.0E-04 n= n= 2 n= 3 n= 4 n= 5 (a) 5.0E-04 (b) 25 Receptivity to slow acoustic waves Pefect gas Noequilibrium flow 5.0E E E E-03 Slow acoustic waves (pefect gas) n= 6 n= 7 n= 8 n= 9 n=0 5.0E E E E-03 Slow acoustic waves (nonequilibrium flow) n= 6 n= 7 n= 8 n= 9 n=0 Response coefficient (K s ) E-03.0E-03 5 (c) (d) f* (k Hz) 2.0E-03.5E-03 Slow acoustic waves (pefect gas) n= n=2 n=3 n=4 n=5 2.0E-03.5E-03 Slow acoustic waves (nonequilibrium flow) n= n=2 n=3 n=4 n=5.0e-03.0e E E-04 (e) (f)
AIAA NUMERICAL SIMULATION OF LEADING EDGE RECEPTIVITY OF STETSON'S MACH 8 BLUNT CONE STABILITY EXPERIMENTS. Xiaolin Zhong * and Yanbao Ma
41st Aerospace Sciences Meeting and Exhibit 6-9 January 2003, Reno, Nevada AIAA 2003-1133 NUMERICAL SIMULATION OF LEADING EDGE RECEPTIVITY OF STETSON'S MACH 8 BLUNT CONE STABILITY EXPERIMENTS Xiaolin Zhong
Numerical Study of Hypersonic Receptivity with Thermochemical Non-Equilibrium on a Blunt Cone
University of California Los Angeles Numerical Study of Hypersonic Receptivity with Thermochemical Non-Equilibrium on a Blunt Cone A thesis submitted in partial satisfaction of the requirements for the
Analysis of Shock Motion in STBLI Induced by a Compression Ramp Configuration Using DNS Data
45th AIAA Aerospace Science Meeting and Exhibit, January 8 11, 25/Reno, Nevada Analysis of Shock Motion in STBLI Induced by a Compression Ramp Configuration Using DNS Data M. Wu and M.P. Martin Mechanical
Numerical Study of Hypersonic Receptivity with Thermochemical Non-Equilibrium on a Blunt Cone
4th Fluid Dynamics Conference and Exhibit 8 June - 1 July 1, Chicago, Illinois AIAA 1-4446 Numerical Study of Hypersonic Receptivity with Thermochemical Non-Equilibrium on a Blunt Cone Neal Parsons, Xiaolin
An experimental and computational study of bouncing and deformation in droplet collision
Copyright 1997, American Institute of Aeronautics and Astronautics, Inc. AIAA Meeting Papers on Disc, January 1997 A9715215, AIAA Paper 97-0129 An experimental and computational study of bouncing and deformation
Computation of Shock Waves in Inert Binary Gas Mixtures in Nonequilibrium Using the Generalized Boltzmann Equation
50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 09-12 January 2012, Nashville, Tennessee AIAA 2012-0361 Computation of Shock Waves in Inert Binary Gas Mixtures
Cbmpu t ;ational Magnetohydfodytiamic Model of a Gasdynamic Mirror Propulsion System
AIAA 99470 Cbmpu t ;ational Magnetohydfodytiamic Model of a Gasdynamic Mirror Propulsion System C. J. Ohlandt..and K. G. Powell Department of Aerospace Engineering T. Kammash Qkpartment of Nuclear Engineering
46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference April 2005 Austin, Texas
th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics & Materials Conference - April, Austin, Texas AIAA - AIAA - Bi-stable Cylindrical Space Frames H Ye and S Pellegrino University of Cambridge, Cambridge,
Optimum aerodynamic design using the Navier-Stokes equations
Copyright 1997, American Institute of Aeronautics and Astronautics, Inc. AIAA Meeting Papers on Disc, January 1997 A9715189, AF-AFOSR-91-0391, AIAA Paper 97-0101 Optimum aerodynamic design using the Navier-Stokes
Numerical Simulation of Hypersonic Boundary-Layer Instability in a Real Gas with Two-Dimensional Surface Roughness
AIAA Aviation 22-26 June 2015, Dallas, TX 45th AIAA Fluid Dynamics Conference AIAA 2015-3077 Numerical Simulation of Hypersonic Boundary-Layer Instability in a Real Gas with Two-Dimensional Surface Roughness
Transient growth of a Mach 5.92 flat-plate boundary layer
48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 4-7 January 21, Orlando, Florida AIAA 21-535 Transient growth of a Mach 5.92 flat-plate boundary layer Xiaowen
UCLA UCLA Electronic Theses and Dissertations
UCLA UCLA Electronic Theses and Dissertations Title Effects of Thermochemical Nonequilibrium on Hypersonic Boundary-Layer Instability in the Presence of Surface Ablation or Isolated Two-Dimensional Roughness
AIAA Xiaolin Zhong * RECEPTIVITY OF MACH 6 FLOW OVER A FLARED CONE TO FREESTREAM DISTURBANCE ABSTRACT INTRODUCTION
42nd AIAA Aerospace Sciences Meeting and Exhibit 5-8 January 2004, Reno, Nevada AIAA 2004-253 RECEPTIVITY OF MACH 6 FLOW OVER A FLARED CONE TO FREESTREAM DISTURBANCE Xiaolin Zhong * University of California,
THE calculation of aerodynamic heating rates on hypersonic
294 J. SPACECRAFT, VOL. 40, NO. 2: ENGINEERING NOTES Hypersonic Aerodynamic Heating Prediction Using Weighted Essentially Nonoscillatory Schemes Theodore K. Lee and Xiaolin Zhong University of California,
fluctuations based on the resolved mean flow
Temperature Fluctuation Scaling in Reacting Boundary Layers M. Pino Martín CTR/NASA Ames, Moffett Field, CA 94035 Graham V. Candler Aerospace Engineering and Mechanics University of Minnesota, Minneapolis,
Real Gas and Surface Ablation Effects on Hypersonic Boundary Layer Instability over a Blunt Cone
Real Gas and Surface Ablation Effects on Hypersonic Boundary Layer Instability over a Blunt Cone Clifton H. Mortensen and Xiaolin Zhong University of California, Los Angeles, California, 90095, USA The
Numerical Study of Boundary-Layer Receptivity on Blunt Compression-Cones in Mach-6 Flow with Localized Freestream Hot-Spot Perturbations
Blunt Compression-Cones in Mach-6 Flow with Localized Freestream Hot-Spot Perturbations Yuet Huang 1 and Xiaolin Zhong 2 Mechanical and Aerospace Engineering Department, University of California, Los Angeles,
Feedback Control of Aerodynamic Flows
44th AIAA Aerospace Sciences Meeting and Exhibit 9-12 January 26, Reno, Nevada AIAA 26-843 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, 9 12 Jan, 26. Feedback Control of Aerodynamic
A Non-Intrusive Polynomial Chaos Method For Uncertainty Propagation in CFD Simulations
An Extended Abstract submitted for the 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada January 26 Preferred Session Topic: Uncertainty quantification and stochastic methods for CFD A Non-Intrusive
Multiscale Hydrodynamic Phenomena
M2, Fluid mechanics 2014/2015 Friday, December 5th, 2014 Multiscale Hydrodynamic Phenomena Part I. : 90 minutes, NO documents 1. Quick Questions In few words : 1.1 What is dominant balance? 1.2 What is
Shock tunnel operation and correlation of boundary layer transition on a cone in hypervelocity flow
Shock tunnel operation and correlation of boundary layer transition on a cone in hypervelocity flow J.S. Jewell 1, J.E. Shepherd 1, and I.A. Leyva 2 1 Introduction The Caltech T reflected shock is used
Jun 22-25, 2009/San Antonio, TX
19th AIAA Computational Fluid Dynamics 22-25 June 2009, San Antonio, Texas AIAA 2009-4273 AIAA 2009 4273 An Assessment of Dual-Time Stepping, Time Spectral and Artificial Compressibility based Numerical
Unconventional Thermal Propellant Gauging System
45th AIAA Aerospace Sciences Meeting and Exhibit 8-11 January 2007, Reno, Nevada AIAA 2007-1363 Unconventional Thermal Propellant Gauging System Dr. B. Yendler. Lockheed Martin Mission Services, Sunnyvale,
Nonlinear Transition Stages in Hypersonic Boundary Layers: Fundamental Physics, Transition Control and Receptivity
Nonlinear Transition Stages in Hypersonic Boundary Layers: Fundamental Physics, Transition Control and Receptivity PI: Hermann F. Fasel Co-PI: Anatoli Tumin Christoph Hader, Leonardo Salemi, Jayahar Sivasubramanian
Orbital and Celestial Mechanics
Orbital and Celestial Mechanics John P. Vinti Edited by Gim J. Der TRW Los Angeles, California Nino L. Bonavito NASA Goddard Space Flight Center Greenbelt, Maryland Volume 177 PROGRESS IN ASTRONAUTICS
Chapter 3. Mass Relations in Chemistry; Stoichiometry
Chapter 3 Mass Relations in Chemistry; Stoichiometry Copyright 2001 by Harcourt, Inc. All rights reserved. Requests for permission to make copies of any part of the work should be mailed to the following
A numerical method to simulate hypersonic boundary layers with finite-rate chemistry
Center for Turbulence Research Annual Research Briefs 21 197 A numerical method to simulate hypersonic boundary layers with finite-rate chemistry By O. Marxen, G. Iaccarino AND E. S. G. Shaqfeh 1. Motivation
Numerical simulation of the sound waves interaction with a supersonic boundary layer
Numerical simulation of the sound waves interaction with a supersonic boundary layer S. A. GAPONOV A.N. SEMENOV Khristianovich Institute of Theoretical and Applied Mechanics Novosibirsk 0090 RUSSIA gaponov@itam.nsc.ru
Preliminary Study of the Turbulence Structure in Supersonic Boundary Layers using DNS Data
35th AIAA Fluid Dynamics Conference, June 6 9, 2005/Toronto,Canada Preliminary Study of the Turbulence Structure in Supersonic Boundary Layers using DNS Data Ellen M. Taylor, M. Pino Martín and Alexander
RECENT near-sonic and low-sonic boom transport aircraft
JOURNAL OF AIRCRAFT Vol. 44, No. 6, November December 2007 Aerodynamic Characteristics of Bodies of Revolution at Near-Sonic Speeds Brenda M. Kulfan, John E. Bussoletti, and Craig L. Hilmes The Boeing
compression corner flows with high deflection angle, for example, the method cannot predict the location
4nd AIAA Aerospace Sciences Meeting and Exhibit 5-8 January 4, Reno, Nevada Modeling the effect of shock unsteadiness in shock-wave/ turbulent boundary layer interactions AIAA 4-9 Krishnendu Sinha*, Krishnan
Vibrational degrees of freedom in the Total Collision Energy DSMC chemistry model
Vibrational degrees of freedom in the Total Collision Energy DSMC chemistry model Mark Goldsworthy, Michael Macrossan Centre for Hypersonics, School of Engineering, University of Queensland, Brisbane,
Journal of Computational Physics 157, (2000) doi: /jcph , available online at
Journal of Computational Physics 157, 796 800 000) doi:10.1006/jcph.1999.639, available online at http://www.idealibrary.com on NOTE A Simple Method for Computing Far-Field Sound in Aeroacoustic Computations
Modeling of Plasma Formation in Rarefied Hypersonic Entry Flows
45th AIAA Aerospace Sciences Meeting and Exhibit 8-11 January 2007, Reno, Nevada AIAA 2007-206 Modeling of Plasma Formation in Rarefied Hypersonic Entry Flows Iain D. Boyd University of Michigan, Ann Arbor,
29th AIAA Fluid Dynamics Conference June 15 18, 1998 / Albuquerque, NM
AIAA 98-2808 Turbularization of the Stokes Layer Over a Transpiring Surface J. Barron and W. K. Van Moorhem University of Utah Salt Lake City, UT 84112 29th AIAA Fluid Dynamics Conference June 15 18, 1998
Parallel Circuits. Chapter
Chapter 5 Parallel Circuits Topics Covered in Chapter 5 5-1: The Applied Voltage V A Is the Same Across Parallel Branches 5-2: Each Branch I Equals V A / R 5-3: Kirchhoff s Current Law (KCL) 5-4: Resistance
Analytical Mechanics. of Space Systems. tfa AA. Hanspeter Schaub. College Station, Texas. University of Colorado Boulder, Colorado.
Analytical Mechanics of Space Systems Third Edition Hanspeter Schaub University of Colorado Boulder, Colorado John L. Junkins Texas A&M University College Station, Texas AIM EDUCATION SERIES Joseph A.
Applied Mathematics and Mechanics (English Edition) Transition control of Mach 6.5 hypersonic flat plate boundary layer
Appl. Math. Mech. -Engl. Ed., 40(2), 283 292 (2019) Applied Mathematics and Mechanics (English Edition) https://doi.org/10.1007/s10483-019-2423-8 Transition control of Mach 6.5 hypersonic flat plate boundary
A Jet Formation Criterion for Synthetic Jet Actuators
AIAA 3-636 A Jet Formation Criterion for Synthetic Jet Actuators Yogen Utturkar, Ryan Holman, Rajat Mittal, Bruce Carroll, Mark Sheplak, and Louis Cattafesta University of Florida Gainesville, FL The George
Modeling of Laser Supported Detonation Wave Structure Based on Measured Plasma Properties
9th Plasmadynamics and Lasers Conference - 6 June 8, Seattle, Washington AIAA 8-49 Modeling of Laser Supported Detonation Wave Structure Based on Measured Plasma Properties Keigo Hatai *, Akihiro Fukui,
New DNS Results of Shockwave/Turbulent Boundary Layer Interaction
36th AIAA Fluid Dynamics Conference, June 5 8, 26/San Francisco,California New DNS Results of Shockwave/Turbulent Boundary Layer Interaction M. Wu and M.P. Martin Mechanical and Aerospace Engineering Department
URANS Computations of Cavitating Flow around a 2-D Wedge by Compressible Two-Phase Flow Solver
URANS Computations of Cavitating Flow around a 2-D Wedge by Compressible Two-Phase Flow Solver *Yohan Choe 1), Hyeongjun Kim 1), Chongam Kim 2) 1), 2) Department of Aerospace Engineering, Seoul National
FUNDAMENTALS OF GAS DYNAMICS
FUNDAMENTALS OF GAS DYNAMICS Second Edition ROBERT D. ZUCKER OSCAR BIBLARZ Department of Aeronautics and Astronautics Naval Postgraduate School Monterey, California JOHN WILEY & SONS, INC. Contents PREFACE
Heating effects on the structure of noise sources of high-speed jets
47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition 5-8 January 2009, Orlando, Florida AIAA 2009-291 47th Aerospace Sciences Meeting and Exhibit 5 8 January 2009,
Experimental Investigation of Convoluted Contouring for Aircraft Afterbody Drag Reduction
AIAA 99-267 Experimental Investigation of Convoluted Contouring for Aircraft Afterbody Drag Reduction K. A. Deere and C. A. Hunter NASA Langley Research Center Hampton, VA 35th AIAA/ASME/SAE/ASEE Joint
AERODYNAMIC SHAPING OF PAYLOAD FAIRING FOR A LAUNCH VEHICLE Irish Angelin S* 1, Senthilkumar S 2
e-issn 2277-2685, p-issn 2320-976 IJESR/May 2014/ Vol-4/Issue-5/295-299 Irish Angelin S et al./ International Journal of Engineering & Science Research AERODYNAMIC SHAPING OF PAYLOAD FAIRING FOR A LAUNCH
AIAA Development of Optical Components for Space-Based Solar Power System for ISRU and Regenerative Life Support
AIAA 2002-0462 Development of Optical Components for Space-Based Solar Power System for ISRU and Regenerative Life Support T. Nakamura 2110 Omega Road/Suite D San Ramon, CA 94583 B. Comaskey and M. Bell
Defense Technical Information Center Compilation Part Notice
UNCLASSIFIED Defense Technical Information Center Compilation Part Notice ADP014827 TITLE: Transition in Hypersonic Flows Including High-Temperature Gas Effects DISTRIBUTION: Approved for public release,
41st Aerospace Sciences Meeting and Exhibit 6-9 January 2003, Reno, Nevada Modeling shock unsteadiness in shock/turbulence interaction
4st Aerospace Sciences Meeting and Exhibit 6-9 January 003, Reno, Nevada Modeling shock unsteadiness in shock/turbulence interaction AIAA 003-65 Krishnendu Sinha*, Krishnan Mahesh and Graham V. Candler
Analysis of Modified Compressibility Corrections for Turbulence Models
49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 4-7 January 2011, Orlando, Florida AIAA 2011-279 Analysis of Modified Compressibility Corrections for Turbulence
Kinetic Energy Measurement of a 1kW Arcjet by Pitot Probe and Laser Absorption Spectroscopy
26th AIAA Aerodynamic Measurement echnology and Ground esting Conference 23-26 June 2008, Seattle, Washington AIAA 2008-4139 Kinetic Energy Measurement of a 1kW Arcjet by Pitot Probe and Laser Absorption
Design and Optimization of De Lavel Nozzle to Prevent Shock Induced Flow Separation
Advances in Aerospace Science and Applications. ISSN 2277-3223 Volume 3, Number 2 (2013), pp. 119-124 Research India Publications http://www.ripublication.com/aasa.htm Design and Optimization of De Lavel
AIAA Numerical Simulation of Transient Hypersonic Flow with Real Gas Effects
4 (c)l999 American Institute of Aeronautics & Astronautics c A994639 ( AIAA 99-416 Numerical Simulation of Transient Hypersonic Flow with Real Gas Effects Yanbao Ma and Xiaolin Zhong University of California,
Chapter 8. Thermochemistry
Chapter 8 Thermochemistry Copyright 2001 by Harcourt, Inc. All rights reserved. Requests for permission to make copies of any part of the work should be mailed to the following address: Permissions Department,
COMPRESSIBLE BOUNDARY LAYER HEAT FLUX MEASUREMENT USING EMBEDDED THERMOCOUPLES
COMPRESSIBLE BOUNDARY LAYER HEAT FLUX MEASUREMENT USING EMBEDDED THERMOCOUPLES Zhao xuejun1*, Ma yuanhong**, Xiao weizhong3*** *China Academy of Aerospace Aerodynamics, ** China Academy of Aerospace Aerodynamics,
AIAA Computational Analysis of a Pylon-Chevron Core Nozzle Interaction
Computational Analysis of a Pylon-Chevron Core Nozzle Interaction R.H.Thomas, K.W.Kinzie, and S. Paul Pao NASA Langley Research Center Hampton, VA USA 7 th AIAA/CEAS Aeroacoustics Conference 28-30 May
AIRFRAME NOISE MODELING APPROPRIATE FOR MULTIDISCIPLINARY DESIGN AND OPTIMIZATION
AIRFRAME NOISE MODELING APPROPRIATE FOR MULTIDISCIPLINARY DESIGN AND OPTIMIZATION AIAA-2004-0689 Serhat Hosder, Joseph A. Schetz, Bernard Grossman and William H. Mason Virginia Tech Work sponsored by NASA
DIRECT SIMULATION CALCULATIONS OF THE RAREFIED HYPERSONIC FLOW PAST A BACKWARD-FACING STEP
9 Brazilian Symposium on Aerospace Eng. & Applications Copyright c 9 by AAB September 14-16, 9, S. J. Campos, SP, Brazil DIRECT SIMULATION CALCULATIONS OF THE RAREFIED HPERSONIC FLOW PAST A BACKWARD-FACING
31th AIAA Fluid Dynamics Conference and Exhibit June 11 14, 2001/Anaheim, CA
AIAA 8 Stability of a Vortex Pair Behind Two-Dimensional Bodies Jinsheng Cai, Feng Liu Department of Mechanical and Aerospace Engineering University of California, Irvine, CA 9697-3975 Shijun Luo Department
38th Aerospace Sciences Meeting & Exhibit IO-13 January 2000 / Reno, NV
(c)2000 American J Institute of Aeronautics 8, Astronautics or published with permission of author(s) and/or author(s); sponsoring organization. 1 3 -m AJA A: m*wa= I.-- JWO:.I 6694, I AIAA 2000-0855 Density
Applied Mathematics and Mechanics (English Edition) Conservation relation of generalized growth rate in boundary layers
Appl. Math. Mech. -Engl. Ed., 39(12), 1755 1768 (2018) Applied Mathematics and Mechanics (English Edition) https://doi.org/10.1007/s10483-018-2394-9 Conservation relation of generalized growth rate in
Hypersonic Blunt Body Thermophysics Using a Unified Kinetic/Continuum Solver
41st AIAA Thermophysics Conference 22-25 June 2009, San Antonio, Texas AIAA 2009-3838 Hypersonic Blunt Body Thermophysics Using a Unified Kinetic/Continuum Solver Andrew J. Lofthouse U.S. Air Force Institute
UNCERTAINTY MODELING VIA FREQUENCY DOMAIN MODEL VALIDATION
AIAA 99-3959 UNCERTAINTY MODELING VIA FREQUENCY DOMAIN MODEL VALIDATION Martin R. Waszak, * NASA Langley Research Center, Hampton, Virginia Dominick Andrisani II, Purdue University, West Lafayette, Indiana
Large-eddy simulations of turbulent reacting stagnation point flows
Copyright 1997, American Institute of Aeronautics and Astronautics, Inc. AIAA Meeting Papers on Disc, January 1997 A9715437, AIAA Paper 97-0372 Large-eddy simulations of turbulent reacting stagnation point
AIAA Investigation of Reynolds Number Effects on a Generic Fighter Configuration in the National Transonic Facility (Invited)
Investigation of Reynolds Number Effects on a Generic Fighter Configuration in the National Transonic Facility (Invited) W. G. Tomek, R. M. Hall, R. A. Wahls, J. M. Luckring, and L. R. Owens NASA Langley
A Non-Intrusive Polynomial Chaos Method for Uncertainty Propagation in CFD Simulations
Missouri University of Science and Technology Scholars' Mine Mechanical and Aerospace Engineering Faculty Research & Creative Works Mechanical and Aerospace Engineering --6 A Non-Intrusive Polynomial Chaos
Control of Shock-Wave / Boundary-Layer Interaction Using Volumetric Energy Deposition
46 th AIAA Aerospace Sciences Meeting, 7 1 Jan. 28, Reno NV Control of Shock-Wave / Boundary-Layer Interaction Using Volumetric Energy Deposition Jonathan Poggie Air Force Research Laboratory, Wright-Patterson
Boundary Layer Stability Analysis for Stetson s Mach 6 Blunt Cone Experiments
Boundary Layer Stability Analysis for Stetson s Mach 6 Blunt Cone Experiments Joseph S. Jewell * and Roger L. Kimmel U.S. Air Force Research Laboratory, WPAFB, OH 533, USA The results of a seminal experimental
Numerical studies of real-gas effects on two-dimensional hypersonic shock-wave/boundary-layer interaction
Numerical studies of real-gas effects on two-dimensional hypersonic shock-wave/boundary-layer interaction Gregory H. Furumoto, a) Xiaolin Zhong, and John C. Skiba Department of Mechanical and Aerospace
INTERNATIONAL JOURNAL OF ADVANCED RESEARCH IN ENGINEERING AND TECHNOLOGY (IJARET) HYPERSONIC SIMILITUDE FOR PLANAR WEDGES. Asha Crasta 1, S. A.
INTERNATIONAL JOURNAL OF ADVANCED RESEARCH IN ENGINEERING AND TECHNOLOGY (IJARET) International Journal of Advanced Research in Engineering and Technology (IJARET), ISSN 0976 ISSN 0976-6480 (Print) ISSN
Numerical Investigation of Shock wave Turbulent Boundary Layer Interaction over a 2D Compression Ramp
Advances in Aerospace Science and Applications. ISSN 2277-3223 Volume 4, Number 1 (2014), pp. 25-32 Research India Publications http://www.ripublication.com/aasa.htm Numerical Investigation of Shock wave
12. SHOCK WAVE PROPAGATION THROUGH NON- EQUILIBRIUM CLUSTER PLASMA
12. SHOCK WAVE PROPAGATION THROUGH NON- EQUILIBRIUM CLUSTER PLASMA Klimov A., Bityurin V., Charitonov A., Fokeev V., Sakharov A., Vystavkin N., Kuznetsov A. Institute for High Temperature RAS Moscow, Izhorskaya
MEASUREMENT OF THE CROSS-COUPLING DERIVATIVES DUE TO PITCHING IN THE HIGH REYNOLDS NUMBER BLOWDOWN WIND TUNNEL
MEASUREMENT OF THE CROSS-COUPLING DERIVATIVES DUE TO PITCHING IN THE HIGH REYNOLDS NUMBER BLOWDOWN WIND TUNNEL Marija Samardžić*, Zoran Anastasijević*, Dragan Marinkovski* and Jovan Isaković** *Military
6-DOF simulation and the vulnerable area of the Air-to-Air missile to develop an End-game simulator
DOI: 1.139/EUCASS217-33 7 TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) 6-DOF simulation and the vulnerable area of the Air-to-Air missile to develop an End-game simulator Eui-Gyu
Introduction to Aircraft Flight. Mechanics
Introduction to Aircraft Flight. Mechanics i Performance, Static Stability, Dynamic Stability, Classical Feedback Control, and State-Space Foundations Second Edition Thomas R. Yechout with contributions
Dynamic Response of an Aircraft to Atmospheric Turbulence Cissy Thomas Civil Engineering Dept, M.G university
Dynamic Response of an Aircraft to Atmospheric Turbulence Cissy Thomas Civil Engineering Dept, M.G university cissyvp@gmail.com Jancy Rose K Scientist/Engineer,VSSC, Thiruvananthapuram, India R Neetha
Active Flutter Control using an Adjoint Method
44th AIAA Aerospace Sciences Meeting and Exhibit 9-12 January 26, Reno, Nevada AIAA 26-844 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, 9 12 Jan, 26. Active Flutter Control using an
ASSESSMENT OF AEROTHERMAL HEATING AUGMENTATION ATTRIBUTED TO SURFACE CATALYSIS IN HIGH ENTHALPY SHOCK TUNNEL FLOWS
ASSESSMENT OF AEROTHERMAL HEATING AUGMENTATION ATTRIBUTED TO SURFACE CATALYSIS IN HIGH ENTHALPY SHOCK TUNNEL FLOWS Matthew MacLean (1) and Michael Holden (2) (1)CUBRC, Inc.; 4455 Genesee St., Buffalo,
An Efficient Low Memory Implicit DG Algorithm for Time Dependent Problems
An Efficient Low Memory Implicit DG Algorithm for Time Dependent Problems P.-O. Persson and J. Peraire Massachusetts Institute of Technology 2006 AIAA Aerospace Sciences Meeting, Reno, Nevada January 9,
Overview of Boundary-Layer Transition Research at AEDC Tunnel 9
Arnold Engineering Development Complex Overview of Boundary-Layer Transition Research at AEDC Tunnel 9 Eric Marineau AEDC White Oak June 29 2016 AEDC Hypervelocity Wind Tunnel No. 9 Unique hypersonic blowdown
Coupled Fluid and Heat Flow Analysis Around NACA Aerofoil Profiles at Various Mach Numbers
International Journal of Engineering Research and Technology. ISSN 0974-3154 Volume 6, Number 2 (2013), pp. 249-258 International Research Publication House http://www.irphouse.com Coupled Fluid and Heat
EXPERIMENTS OF CLOSED-LOOP FLOW CONTROL FOR LAMINAR BOUNDARY LAYERS
Fourth International Symposium on Physics of Fluids (ISPF4) International Journal of Modern Physics: Conference Series Vol. 19 (212) 242 249 World Scientific Publishing Company DOI: 1.1142/S211945128811
STUDY ON THE IMPROVED KRIGING-BASED OPTIMIZATION DESIGN METHOD
7 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES STUDY ON THE IMPROVED KRIGING-BASED OPTIMIZATION DESIGN METHOD Song Wenping, Xu Ruifei, Han Zhonghua (National Key Laboratory of Science and Technology
THE ROLE OF LOCALIZED ROUGHNESS ON THE LAMINAR-TURBULENT TRANSITION ON THE OBLIQUE WING
THE ROLE OF LOCALIZED ROUGHNESS ON THE LAMINAR-TURBULENT TRANSITION ON THE OBLIQUE WING S.N. Tolkachev*, V.N. Gorev*, V.V. Kozlov* *Khristianovich Institute of Theoretical and Applied Mechanics SB RAS
General Geology - GEOL 1113 Section 005
General Geology - GEOL 1113 Section 005 Instructor: Dr. Glen S. Mattioli, Professor Office: Ozark Hall 27B Office Hours: MW 10:30-12:00 & TR 11:00-12:00 Office Phone: 575-7295 Class Web Page http://comp.uark.edu/~mattioli/geol_1113.html
THEORETICAL AND EXPERIMENTAL INVESTIGATIONS ON CHOKING PHENOMENA OF AXISYMMETRIC CONVERGENT NOZZLE FLOW
8 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES THEORETICAL AND EXPERIMENTAL INVESTIGATIONS ON CHOKING PHENOMENA OF AXISYMMETRIC CONVERGENT NOZZLE FLOW Ryuta ISOZUMI*, Kazunori KUBO*, Daisuke
Laser Absorption Spectroscopy in Inductive Plasma Generator Flows
nd AIAA Aerospace Sciences Meeting and Exhibit -8 January, Reno, Nevada AIAA - AIAA - Laser Absorption Spectroscopy in Inductive Plasma Generator Flows Makoto Matsui, Georg Herdrich, Monika Auweter-Kurtz,
Section 4.1 Polynomial Functions and Models. Copyright 2013 Pearson Education, Inc. All rights reserved
Section 4.1 Polynomial Functions and Models Copyright 2013 Pearson Education, Inc. All rights reserved 3 8 ( ) = + (a) f x 3x 4x x (b) ( ) g x 2 x + 3 = x 1 (a) f is a polynomial of degree 8. (b) g is
The Gamma Variate with Random Shape Parameter and Some Applications
ITSUBISHI ELECTRIC RESEARCH LABORATORIES http://www.merl.com The Gamma Variate with Random Shape Parameter and Some Applications aaref, A.: Annavajjala, R. TR211-7 December 21 Abstract This letter provides
SIMULATION OF GAS FLOW OVER MICRO-SCALE AIRFOILS USING A HYBRID CONTINUUM-PARTICLE APPROACH
33rd AIAA Fluid Dynamics Conference and Exhibit 3-6 June 3, Orlando, Florida AIAA 3-44 33 rd AIAA Fluid Dynamics Conference and Exhibit / Orlando, Florida / 3-6 Jun 3 SIMULATION OF GAS FLOW OVER MICRO-SCALE
THERMODYNAMIC ANALYSIS OF COMBUSTION PROCESSES FOR PROPULSION SYSTEMS
2nd AIAA Aerospace Sciences Paper 2-33 Meeting and Exhibit January -8, 2, Reno, NV THERMODYNAMIC ANALYSIS OF COMBUSTION PROCESSES FOR PROPULSION SYSTEMS E. Wintenberger and J. E. Shepherd Graduate Aeronautical
CFD Analysis of Micro-Ramps for Hypersonic Flows Mogrekar Ashish 1, a, Sivakumar, R. 2, b
Applied Mechanics and Materials Submitted: 2014-04-25 ISSN: 1662-7482, Vols. 592-594, pp 1962-1966 Revised: 2014-05-07 doi:10.4028/www.scientific.net/amm.592-594.1962 Accepted: 2014-05-16 2014 Trans Tech
Journal of Astronautics , ; 2. : (2007) Navier2Stokes, T = T w + ( T aw - T w ) guπu e rgu 2 ΠCp 1.
28 3 2007 5 Journal of Astronautics Vol. 28 No. 3 May 2007 1 2 2 1 (1. 100083 ; 2. 100074) : Π : ; Π ; : V211 : A : 100021328 (2007) 0320598205 0 1 Π 1. 1 Π Π [1-5 ] Navier2Stokes Roe FDS B2L Chien k2
Thomas E. Schwartzentruber Assistant Professor
Thomas E. Schwartzentruber Assistant Professor Department of Aerospace Engineering & Mechanics, University of Minnesota #222 Akerman Hall, 110 Union St. SE Minneapolis, MN 55455 Tel: 612-625-6027 schwartz@aem.umn.edu
CFD ANALYSIS OF AERODYNAMIC HEATING FOR HYFLEX HIGH ENTHALPY FLOW TESTS AND FLIGHT CONDITIONS
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES CFD ANALYSIS OF AERODYNAMIC HEATING FOR HYFLEX HIGH ENTHALPY FLOW TESTS AND FLIGHT CONDITIONS Keiichi Murakami*, Yukimitsu Yamamoto*, Olivier Rouzand**
Theoretical and Computational Studies of Stability, Transition and Flow Control in High-Speed Flows. Principal Investigator: A.
Theoretical and Computational Studies of Stability, Transition and Flow Control in High-Speed Flows Principal Investigator: A. Tumin February 22, 2011 Report Documentation Page Form Approved OMB No. 0704-0188
Improvements to the Linear Standard Stability Prediction Program (SSP) Propulsion Conference and Exhibit July 2004 Fort Lauderdale, FL
AIAA 2004-4181 Improvements to the Linear Standard Stability Prediction Program (SSP) J. C. French Software and Engineering Associates Carson City, NV 89701 Propulsion Conference and Exhibit 11 14 July
APPLICATION OF SPACE-TIME MAPPING ANALYSIS METHOD TO UNSTEADY NONLINEAR GUST-AIRFOIL INTERACTION PROBLEM
AIAA 2003-3693 APPLICATION OF SPACE-TIME MAPPING ANALYSIS METHOD TO UNSTEADY NONLINEAR GUST-AIRFOIL INTERACTION PROBLEM Vladimir V. Golubev* and Axel Rohde Embry-Riddle Aeronautical University Daytona
Exponential Box-Schemes for Boundary-Layer Flows with Blowing
JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER Vol. 10, No. 1, January-March 1996 Exponential Box-Schemes for Boundary-Layer Flows with Blowing Vladimir V. Riabov* Worcester Polytechnic Institute, Worcester,
AIAA Sensing Aircraft Effects by Flap Hinge Moment Measurement
AIAA 99-349 Sensing Aircraft Effects by Flap Hinge Moment Measurement Holly M. Gurbacki and Michael B. Bragg University of Illinois at Urbana-Champaign Urbana, IL 7th Applied Aerodynamics Conference June