This viewgraph presentation discusses turbulence modeling requirements, development philosophy, and approach; two major areas of concentration (high speed and low speed turbulence modeling); high speed turbulence modeling; compressibility effects; turbulence models adapted to USA code; M = 9.2 flat plate flow; Mach 7.05 flow over axisymmetric flare; Mach 8.6 flow over cold wall edge; low speed turbulence modeling; turbulence models being assessed; turbulence model deck structure and integration with Navier-Stokes solver; nonlinear algebraic-stress model; rotation modified k-epsilon model; and Reynolds stress model

Hadid, A. H.

Lynch, E. D.

Sindir, Munir M.

German

NASA Technical Reports Server

OVERVIEWOFTURBULENCEMODELDEVELOPMENTAND
APPLICATIONSAT ROCKETDYNE
A.H.Hadid,E.D.Lynch,andM.M. Sindir
RocketdyneDivision
RockwellInternational
CanogaPark,California
N95- 27891
TURBULENCE MODELING REQUIREMENTS,
DEVELOPMENT PHILOSOPHY AND APPROACH
REQUIREMENTS
• TURBULENCE MODELING IS A KEY ENABLING TECHNOLOGY
FOR ALL PROPULSION RELATED CFD ACTIVITIES
• FACTORS TO CONSIDER INCLUDE ACCURACY, CONSISTENCY,
COMPUTATIONAL COST, AND EASE OF USE
• TURBULENCE MODELS THAT CAN NOT BE INCLUDED tN
PRODUCTION GRADE CFO CODES ARE OF LIMITED VALUE
TO INDUSTRY
PHILOSOPHY
• BASIC MODEL DEVELOPMENT IS BEST LEFT TO SPECIALIZED
"CENTERS OF EXCELLENCE"
• VARIOUS CLASSES OF MODELS NEED TO BE SUPPORTED SINCE
NO SINGLE UNIVERSAL MODEL IS SHOWN TO EXIST
• ESTABLISHING THE RANGE OF APPLICABILITY, ACCURACY, AND
THE COMPUTATIONAL COST OF THE MODELS IS ESSENTIAL
. TURBULENCE MODELING REQUIREMENTS,
DEVELOPMENT PHILOSOPHY AND APPROACH (Cont.)
• APPROACH
• IDENTIFY KEY "CENTERS OF EXCELLENCE' AND ESTABLISH
COLLABORATIVE RELATIONSHIP
° ACQUIRE MODELS AND ASSESS PERFORMANCE FOR THE
INTENDED CLASS OF APPLICATIONS
• DELINEATE MODEL DEFICIENCIES AND INITIATE EFFORT TO
REDUCE THEM
• DEVELOP MODELS INTO STANDALONE MODULES
• INCLUDE MODULES IN PRODUCTION CODES AND ESTABLISH
BASELINE FOR APPLICATIONS
107
i_CEDING PAGE BLANK NEll FILMED
https://ntrs.nasa.gov/search.jsp?R=19950021470 2020-06-16T08:03:47+00:00Z
TWO MAJOR AREAS OF CONCENTRATION
• HIGH SPEED TURBULENCE MODELING (LEAD DR. DOUG LYNCH)
• FOCUSED ON HIGH SPEED (M>I) PROPULSION (ROCKET
AND AIRBREATHING) AND AERODYNAMICS
• EMPHASIS ON 2-EQUATION PHENOMENOLOGICAL MODELS
WITH NASA ARC AND LARC AS KEY TECHNOLOGY PARTNERS
• LES WORK IN PLANNING STAGES WITH CTR
• LOW SPEED TURBULENCE MODELING (LEAD DR. ALl HADID)
• FOCUSED ON LOW SPEED (M<I) AND ROTATING FLOW
APPLICATIONS
• EMPHASIS ON REYNOLDS STRESS PHENOMENOLOGICAL
MODELS IN COLLABORATION WITH UMIST, ICOMP, CTR, AND UAH
• LES WORK INITIATED WITH CTR
HIGH SPEED TURBULENCE MODELING
EMPHASIS IS ON THE DEVELOPMENT OF ENGINEERING
TURBULENCE MODELS FOR
• HIGH SPEED AIRBREATHING PROPULSION SYSTEMS
• THRUST CHAMBERS
• VEHICLE AERODYNAMICS
APPROACH TAKEN IS BASED ON 2-EQUATION MODELS
• DIFFERENT CLASSES OF 2-EQUATION MODELS STUDIED
• koS
• k-o
• POINTWISE Rt
• :COMPRESSIBILITY EFFECTS AND TURBULENCE-CHEMISTRY
INTERACTIONS MAJOR MODEL UPGRADE THRUSTS
• COMPRESSIBILITY MODIFICATIONS FROM ARC
• TURBULENCE-CHEMISTRY INTERACTION MODELS FROM LARC
• USA AND GASP SERVE AS NUMERICAL PLATFORM
• GASP - CHIEN, LAM-BREMHORST k-s, k-o_
• USA - VARIETY OF k-s, k-co
108
COMPRESSIBILITY EFFECTS
• MIXING LAYER SPREADING REDUCED AT HIGH MACH NUMBERS
• INCREASE DISSIPATION RATE OF k
• DEFINE Ck2AS A FUNCTION OF TURBULENT MACH NUMBER_
• ZEMAN MODIFICATION (1990)
• SARKAR (1990, 1991) AND WILCOX (199,1)PROPOSALS
• MODIFICATIONS OF ZEMAN AND SARKAR NOT RECOMMENDED
• HEAT TRANSFER OVER PREDICTED NEAR SHOCK WAVES
Ky )
• SEPARATION UNDERPREDICTED IN RAPID COMPRESSION OR
STRAIN REGIONS
• INCREASE a _OR cco)UNDER RAPID COMPRESSION (VUONG AND
COAKLEY)
• HEAT TRANSFER OVER PREDICTED FOR VERY COLD WALLS
T Wff aw<O.1 (COAKLEY)
• CEBECI-SMITH ~ 60%, k-_ ~ 40%, q-_ ~ 10%, k-_ ~ 30%
TURBULENCE MODELS ADAPTED TO USA CODE
TP,_NsrnoN MODEL COMPRESSIBILITY EFFECTS
DAMPING BOUNDARY HIGH ORDER MIXING LAYER SE PARAllON REATrACHMENT
WALL LOCAL _ _ ARNAL _ EXTI_IT HEATTRANSFER
Baldwln-Lomax X 3 Version= X X
k.,t 1. S_lmr (lggl) 4. Yuong & S. Vuong &
I. Myong-IOl_lgl X X k=0 ;(
¢ = _tlSy 2 2. ZJrnan (1990) Coakley Coakley
3. WUCOX (1991) (1987) (1987)
2. ChZInO"2) X . X __'_ X _2. a. 4. S.
3. Jo41es-Lagndllr X X k=O X 1_ 2., 3. 4. S.
(1972} z=0
1,2,3. 4. S,
4. LJlundef-Sharma X X ks0 X
{1974)
k=O 1,2,3. &. S.
s, x=n_pco=k_,y x x e. 2,_h_ x(1_
k=O 1.2,3. 4. 5.
s spom_-sc-zha.g x x =- _k_t= X
(1_1
k=O 1_2, 3. 4. S.
7. Larn-Bn=mborst X X cy. 0 X
(1_)
8. High Re X X Will Ftm_k_l X
_ Hug.R. w,cox _==olo_ x "_2, 3 4. 5
0991a)
k=O
2. Low Re Wilcox = = 7.2_1/y2 X 1.2., 3. 4. 5.
(1991b)
k=O X
Coakley (1987) _f = 0
Onl_Equallon (Goldberg. - k = 0
Two-Time Scale 1992}
Onl_Equltlon R T X d(_) = d(_lRt) =0 X
(Gok:lberg 1993,1994) dy ely
109
M = 9.2 FLAT PLATE FLOW
CHIEN k-_ MODEL WITH RAPID COMPRESSION AND LENGTH SCALE
COMPRESSIBILITY MODIFICATIONS
VELOCITY PROFILE
f0.1
O,4
O.,2
- 0.!
0.0
U.0 0.5 1.0
yldl|ta
TURBULENT VISCOSITY
lO = ,
lO' (
lO = |
lO' I
+" .," ; =.
lO" • l,
10,J - ." ..... .m.,m,
I
.-' : -¢- t++5mmmm
10"'< _m
"%.. ,o., ,o. ,;-.. ,o. .,o. _,o.
ylmu=
lO'
REF: G.T. COLEMAN AND J.L. STOLLERY, JFM 56: 741, "HEAT.TRANSFER FROM A
HYPERSONIC TURBULENT FLOW AT A WEDGE COMPRESSION CORNER"
MACH 7.05 FLOW OVER AXISYMMETRIC FLARE
CHIEN k-o) MODEL WiTH RAPID COMPRESSION AND LENGTH SCALE
COMPRESSIBILITY MODIFICATIONS
AXISYMMETRIC FLARE WALL PRESSURE FOR AXISYMMETRIC FLARE
5 = 2 cm e = 35 °
M = 7.0_
I !
1 39 cm
50
40
c 30
o,.
a.
20
10
0'
-20
RO PREDICTIONS
• ARC PREDICTIONS
TEST 0ATA _e
J
-10 0 10 2O
x(In)
REF: M.I. KUSSOY AND C.C. HORSTMAN, "DOCUMENTATION OF TWO- AND
THREE-DIMENSIONAL HYPERSONIC SHOCK-WAVE TURBULENT
BOUNDARY LAYER INTERACTION FLOW," NASA TM 1-01075.
110
MACH 7.05 FLOW OVER AXISYMMETRIC FLARE
CHIEN k-_ MODEL WITH RAPID COMPRESSION AND LENGTH SCALE
COMPRESSIBILITY MODIFICATIONS
WALL HEAT TRANSFER FOR AXISYMMETRIC FLARE
40"
PREDICTIONS
• TEST DATA
30
._c
QO
o" 20" e•
10
0
-20 -10 0 10 20
x (in)
MACH 8.6 FLOW OVER COLD WALL WEDGE
M=8.6
Tw/Taw = 0.065
THREE STUDIES
1. CHIEN k-e MODEL WITH RAPID COMPRESSION AND LENGTH SCALE
CORRECTIONS AND WITH AND WITHOUT MIXING LAYER TREATMENT
2. HIGH-Re k-e MODEL WITH VARIOUS AIR CHEMISTRY MODELS
3. BALDWlN-LOMAX TURBULENCE MODEL USING WALL AND LOCAL
DAMPING
III
MACH 8.6 FLOW OVER COLD WALL WEDGE
CHIEN k-E MODEL WITH AND WITHOUT MIXING LAYER TREATMENT
o"
4"
3
HEAT FLUX CALCULATIONS
..._°
WITHOUT MIXING LAYER MODIFICATIONS
WITH MIXING LAYER MODIFICATIONS !SARKAR)
TEST DATA
• • • • • •'*--'*--'_'"';'_";"--_ ......._..... _ ......._ ..........
• • • •
0
u.0 0.2 0.4 0.6 0,8 1.0
x/L
MACH 8.6 FLOW OVER COLD WALL WEDGE
HIGH-Re k-o,)MODEL WITH VARIOUS AIR CHEMISTRY MODELS
HEAT FLUX CALCULATIONS
4_ --""-- NONEQUILIBRIUM AIR KINETICS (KANG & DUNN)
'E 2 _
PERFECT GAS
• TEST DATA
OoO°" "_ ,i,._._.,° m. °o..°,_..,°._..,.,-q.w, ........... .,- ..-. ..... i.° ..... °,°,...,. n ..
U.0 0.2 0.4 0.6 0.8 1.0
x/L
112
MACH 8.6 FLOW OVER COLD WALL WEDGE
BALDWIN LOMAX, k-E, k-co MODEL COMPARISONS
"E
4 _
HEAT FLUX CALCULATIONS
.... b_- BALDWIN-LOMAX WALL DAMPING
..... O-- BALDWIN-LOMAX LOCAL DAMPING
;_ _ k-_a (NONEQUILIBRIUM)
. °,,..p..
3 f_ .-, (EQUILIBRIUM}
i _ ° ,_sT DAT,
q" "Q""'$" "q-_ -_ _""A'_'A ...... A........ _ .............
g
U.0 0.2 0.4 0.6 0.8 1.0
x/L
LOW SPEED TURBULENCE MODELING
• EMPHASIS IS ON THE DEVELOPMENT OF ENGINEERING
TURBULENCE MODELS FOR
• ROTATING MACHINERY
• FLOW IN DUCTS AND MANIFOLDS
• REACTING FLOWS
• APPROACH TAKEN IS TO
1. SYSTEMATICALLY ASSESS EXISTING PHENOMENOLOGICAL
MODELS USING COMMON NAVIER-STOKES SOLVER
2. IDENTIFY, DEVELOP AND VALIDATE MODEL UPGRADES
COMMENSURATE WITH OBSERVED FLOWPHYSICS
3. DEVELOP SELF-CONTAINED TURBULENCE MODEL DECKS
(MODULES) THAT CAN BEINTEGRATED WITH NAVtER-STOKES
SOLVERS
4. PROVIDE GUIDANCE TO EXPERIMENTAL AND THEORETICAL
RESEARCH IN TURBULENCE MODELING FOR ENGINEERING
APPLICATIONS
113
TURBULENCE MODELS BEING ASSESSED
I PHENOMENOLOGICAL SINGLE POINT CLOSURE MODELS I
SINGLE-SCALE MULTI-SCALE
I I
2-EQUATION MODELS ALGEBRAIC REYNOLDS
K- _ (SKEM) STRESS MODELS STRESS MODELS
(ASM) (RSM)
2-EQUATION MODELS
K- • (MKEM)
NEAR-WALL TREATMENTS INCLUDE (WHERE APPROPRIATE) WALL
FUNCTIONS, MULTILAYER MODELS, AND LOW-REYNOLDS NUMBER
APPROXIMATIONS
TURBULENCE MODEL DECK STRUCTURE AND
INTEGRATION WITH NAVIER-STOKES SOLVER
PREPROCESSOR
1. GRID
2. BOUNDARY CONDITION FLAGS
3. FLOW PROPERTIES
4. INmAL CONDmONS
i
NAV1ER-STOKES
SOLVER
INPUT TO
TURBULENCE
DECK
------I1,=
MEAN VELOCITY
UI
ITERA'nON LOOP
TURBULENCE MODEL DECK
SELF-CONTAINED DECK
WITH BUILT-IN SOLVER
_'_,_2LEVELS OF MODELING_
_\\'_ _\\\\\\\\\\\\\\\'_
I EDOY VISCOSITY MODELS
k, P I 1. S;<EM1, j 2. MKEM
_U__j.I REYNOLDSTRESSMODELSI. ASM
2. RSM
114
PROJECT WELL UNDERWAY
• TEAM
• MODELS PROVIDED BY UMIST, LERC/ICOMP, ARC/CTR
• MODULE DEVELOPMENT BY ROCKETDYNE
• MODULE TESTING BY ROCKETDYNE (REACT, USA) AND
UAH (MAST)
• MODEL UPGRADES BY ROCKETDYNE, UMIST, ARC/CTR
• APPLICATION BY ROCKETDYNE TO TURBOPUMP
COMPONENT (E.G. IMPELLER) ANALYSIS
• 2-D MODULES COMPLETED, TESTED, AND RELEASED
• SINGLE SCALE k-_
• MULTI SCALE k-_
• ASM
• RSM
• 3-D MODULE DEVELOPMENT IN PROGRESS
NONLINEAR ALGEBRAIC-STRESS MODEL
VORTEX SHEDDING FROM RECTANGULAR CYLINDERS (DURAO, et al)
PARTICLE STREAKLINES
°'J f _:-*%_-
,,,._-_E]',/,_._ _ _,_,
"':'_"_':"" _!
G.o. o o' _ _.,
MEAN AXIAL VELOCITY ALONG CENTERUNE
o '" /."
o.3 o.i
x
MEAN KINETIC ENERGY ALONG CENTERLINE
. -..
I _.1 • • \' "*/
\,
• , .' / '_% .........
.L, -LI ,, ,, t, _l ,t L, ,, ,,
115
ROTATION MODIFIED k-_ MODEL
BACKWARD FACING STEP (DRIVER AND SEEGMILLER)
STREAMUNE CONTOURS
MEAN AXIAL VELOCITY AT X/M=4
ALGEBRAIC STRESS MODEL
CONFINED COAXIAL SWIRLING JET FLOW (ROBACK AND JOHNSON)
=:
GEOMETRY
I
$.0,lle
DECAY OF MEAN AXIAL CENTERLINE VELOCITY
STREAMLINE CONTOURS
0,0 O1 02 0.3 04 05
x(m)
RADIAL PROFILES OF _'_
25 mm
_¢;'1-
_-
...1
_o .
O5 Q
0.0 0,4 0'.8
I16
REYNOLDS STRESS MODEL (LRR - MODEL)
BACKWARD FACING STEP (DRIVER AND SEEGMILLER)
STREAMLI NE CONTOU RS
o.13o ._
o.oo o.= o:o4 o.,= o:,= -o'._o
MEAN AXIAL VELOCrTY AT X/H--4
!t -
"I __.
AXIAL TURBULENT INTENSITY AT XJH=4
CONCLUDING REMARKS
• PROGRAMS (BOTH COMMERCIAL AND GOVERNMENT) EMPLOY
NEW TECHNOLOGY ONLY WHEN IT PROVIDES "ADDED VALUE"
• REDUCED DEVELOPMENT COST
• INCREASED RELIABILITY AND PERFORMANCE
• ENHANCED MANUFACTURABILITY
• THE NE3N TECHNOLOGY WE OFFER IS THE COMPUTATIONAL
ENGINEERING TOOLS FOR PRODUCT DESIGN AND ANALYSIS
• THESE TOOLS ARE THE END PRODUCT FOR ALL ENABLING
TECHNOLOGY DEVELOPMENT
• PRE- AND POST PROCESSING
• ALGORITHMS AND NUMERICAL PLATFORMS
• PHYSICAL MODELS (E.G. TURBULENCE AND CHEMISTRY)
• FAILURE OF ANY ENABLING TECHNOLOGY JEOPARDIZES THE
PERFORMANCE (VALUE) OF THE TOOL
NOW MORE THAN EVER, THERE IS A NEED FOR CLOSER
COLLABORATION AND COOPERATION BETWEEN GOVERNMENT,
INDUSTRY, AND RESEARCH INSTITUTIONS TO ENSURE
MAINTENANCE OF COUNTRY'S TECHNOLOGY BASE
117



Overview of turbulence model development and applications at Rocketdyne

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