CIAM, Sukhoi NCT and Irkut Contribution to HiLiftPW-2 · CIAM, Sukhoi NCT and Irkut Contribution to...

CIAM, Sukhoi NCT and Irkut Contribution to

HiLiftPW-2

Vladimir Makarov at all

Central Institute of Aviation Motors (CIAM), Moscow, Russia

32nd AIAA Applied Aerodynamics Conference, 2nd High Lift Prediction Workshop Special Session APA-21,

June 16-20 2014, Atlanta

2

The DLR-F11’s configuration considered:

Configuration 2

Configuration 4

Mean aerodynamic chord (MAC) Semispan (b/2) Wing aspect ration

0.34709 m 1.4 m 9.353

3

Problem statement:

External bounds Internal bounds

External region: 12 blocks

Configuration 2: 335 blocks Configuration 4: 480 blocks

External bounds of internal region

symmetry

plane

symmetry

plane symmetry

plane

Different mesh topology

Red lines: topology

block’s bounds

4

Mesh generation (base principles and details):

Case Mesh No. of cells

(million)

First cell

heights (m)

Case 1 Coarse 5 756 600 0.00055

Medium 13 773 390 0.00037

Fine 43 346 620 0.00024

Case 2 Medium 47 252 565 0.00037

All meshes were block-structured and were constructed by the ICEM-CFD

Details of the meshes used

5

Mesh generation (Case 1 illustration):

wing-fuselage junction

cut view at wing root

zoom near wing nose

zoom near wing trailing edge

Coarse Medium Fine

flap stack fairings

Mesh generation (Case 2 illustration):

wing-fuselage junction cut view at wing root

zoom near wing nose zoom near wing

trailing edge

zoom near slat

stack junctions

zoom near flap stack fairing junctions

Details of the numerical method and software:

Numerical method:

• 2D/3D Euler/RANS/URANS solver

• Finite volume

• Explicit/implicit time integration

• Second order spatial/time discretization

• Dual time approach for unsteady problems

• Cartesian coordinate system

• Multi-block structured fixed/moving mesh

• Parallel capability shared/distributed

memory

Typical performance:

• Courant number up to 1000 (in implicit

mode)

• Up to 5, 000, 000 mesh cells for 1 Gb RAM

• Near linear parallel computation speed-up

factor

Flow capabilities:

• Inviscid

• Laminar

• Turbulent

• Real/perfect gases

• Turbulent models:

o Spalart-Allmaras

o k-

o SST (high and low Reynolds)

• Standart/extended wall function

• Perforated walls

• Particles tracking with wall interaction

• Stationary and/or Rotating frame of

reference

Computer platforms:

• Linux (32/64 bit)

• Windows XP/7 64 bit 7

Results (Case 1):

8

0.6

1.0

1.4

1.8

2.2

2.6

3.0

3.4

3.8

4.2

0 100 200 300 400 500 600 700 800

Lif

t C

oe

ffic

ien

t

Iterations/Pseudo-time steps

Cobra (Fine SA): AoA= 7.0 degree

Cobra (Fine SA): AoA=16.0 degree

Iteration/pseudo-time convergence of lift coefficient for Case 1

Configuration: configuration 2 of DLR-F11

Free stream Mach number: 0.175

Angle of attack (AoA): 7 and 16

Meshes: coarse, medium, fine

Reynolds number: 15.1 million

Results (Case 1 mesh convergence):

9

1.82

1.84

1.86

1.88

1.90

1.92

1.94

1.96

1.98

0.40 0.80 1.20 1.60 2.00 2.40 2.80 3.20

Lif

t C

oe

ffic

ien

t

Mesh parameter1e-5

Simulation: AoA= 7.0 deg., Cobra(SA)

Experiment: AoA=7.039 deg., Re=15.1e+6

0.160

0.162

0.164

0.166

0.168

0.170

0.40 0.80 1.20 1.60 2.00 2.40 2.80 3.20

Dra

g C

oe

ffic

ien

t

Mesh parameter1e-5



Lift coefficient Drag coefficient

Mesh convergence for AoA = 7

1.82

1.84

1.86

1.88

1.90

1.92

1.94

1.96

1.98

0.40 0.80 1.20 1.60 2.00 2.40 2.80 3.20

Lif

t C

oe

ffic

ien

t

Mesh parameter1e-5



0.160

0.162

0.164

0.166

0.168

0.170

0.40 0.80 1.20 1.60 2.00 2.40 2.80 3.20

Dra

g C

oe

ffic

ien

t

Mesh parameter1e-5




Mesh convergence for AoA = 7

Results (Case 1 pressure coefficient distribution at AoA=7):

10

Z=0.150

Z=0.449

Z=0.891

Slat Wing Flap

z

Results (Case 1 Summary):

11

1.00

1.50

2.00

2.50

3.00

3.50

0 5 10 15 20 25 30

Lift

Coeffie

nt

Angle of Attack, deg.

China Aerodynamics Research_SA-officialPenn State University_SA -officialEcole Polytechnique de Montreal_SA -officialIntelligent Light_SACessna Aircraft Company_SABombardier_kwNASA Langley_CFL3D -SANASA Langley_FUN3D -SATATA_SAJAXA_SA -officialDLR_RSMNASA -Boeing_SAOnera_SAWTTCIAM ( Medium SA)CIAM ( Medium SST+wf)

Summary CL plots from different HiLift PW-2 for Case 1 for medium

mesh

Results (Case 2):

12

Configuration: configuration 4 of DLR-F11

Free stream Mach number: 0.175

Angle of attack (AoA): 0, 7, 12, 16, 18.5, 19, 20 and 21

Meshes: medium

Reynolds numbers: low Reynolds 1.35 million (Case 2a) high Reynolds 15.1 million (Case 2b)

Results (Case 2a aerodynamic characteristics):

13

1.00

1.20

1.40

1.60

1.80

2.00

2.20

2.40

2.60

2.80

3.00

0 2 4 6 8 10 12 14 16 18 20 22

Lif

t C

oe

ffic

ien

t

Angle of Attack, degree

Experiment: Re=1.35e+6

Cobra(Medium SA LR)

Cobra(Medium SA LR reset)

0.00

0.10

0.20

0.30

0.40

0.50

0.60

0 2 4 6 8 10 12 14 16 18 20 22

Dra

g C

oe

ffic

ien

t



Cobra(Medium SA LR)


1.00

1.20

1.40

1.60

1.80

2.00

2.20

2.40

2.60

2.80

3.00

0 0.04 0.08 0.12 0.16 0.2 0.24 0.28 0.32 0.36 0.4 0.44 0.48 0.52 0.56 0.6

Lif

t C

oe

ffic

ien

t

Drag Coefficient


Cobra(Medium SA LR)


-0.60

-0.50

-0.40

-0.30

-0.20

-0.10

0.00

0.10

0 2 4 6 8 10 12 14 16 18 20 22

Mo

me

nt

Co

eff

icie

nt



Cobra(Medium SA LR)


Drag polar Pitching moment


Results (Case 2a Surface stream lines and oil flow):

14

AoA=7

AoA=18.5

AoA=20

Results (Case 2b aerodynamic characteristics):

15Drag polar Pitching moment


1.00

1.20

1.40

1.60

1.80

2.00

2.20

2.40

2.60

2.80

3.00

3.20

3.40

0 2 4 6 8 10 12 14 16 18 20 22 24 26

Lif

t C

oe

ffic

ien

t



Cobra(Medium SA Case 2b)

Cobra(Fine SA Case 2b)

0.00

0.10

0.20

0.30

0.40

0.50

0.60

0 2 4 6 8 10 12 14 16 18 20 22 24 26

Dra

g C

oe

ffic

ien

t





1.00

1.20

1.40

1.60

1.80

2.00

2.20

2.40

2.60

2.80

3.00

3.20

3.40

0.00 0.04 0.08 0.12 0.16 0.20 0.24 0.28 0.32 0.36 0.40 0.44 0.48 0.52 0.56 0.60

Lif

t C

oe

ffic

ien

t

Drag Coefficient




-0.60

-0.50

-0.40

-0.30

-0.20

-0.10

0.00

0.10

0 2 4 6 8 10 12 14 16 18 20 22 24 26

Mo

me

nt

Co

eff

icie

nt





Results (Case 2b Summary):

16Summary CL plots from different HiLift PW-2 for Case 2b

1.00

1.50

2.00

2.50

3.00

3.50

0 5 10 15 20 25 30

Lif

t C

oe

ffic

ien

t

Angle of Attack, deg.

chen_China Aerodynamics Research

coder_Penn State University

holman_Next Limit

langlois_Bombardier

leerausch_NASA Langley_FUN3D

moitra_TATA

rudnik_DLR

sclafani_NASA-Boeing

WTT

CIAM ( Medium SA)

Conclusions:

17

• Results of the calculations have different degree of convergence with WTT-data

for different parameters

• The general tendency is good coordination of CL and dCL/d with experiment for

Case 1 and Case 2b in a linear range and over prediction of CLmax nearly

identical for all meshes

• For the Case 2a the best coordination of CLmax as the good coordination of

dCL/d takes place, but CL in a linear range is however worse predicted

• Values of CD were predicted satisfactory within the limits of the given problem

for all cases considered

• The results received for the Case 2a have shown a capability of a hysteresis of

aerodynamic characteristics during calculations that demands additional study of

the reasons of this phenomenon and its physical adequacy in the problem

considered

• The comparative analysis of the results received by various participants of the

HiLiftPW-2 project for calculation of CL vs curves for various DLR-F11’s

configurations, has shown, that CIAM’s in-house Cobra code is among of the

majority of the CFD software used in the project

Acknowledgments:

18

This work is the results of several fruitful collaborations and we gratefully acknowledge to

the Sarov's Institute of Experimental Physics which have provided supercomputer and

information resources and to Sukhoi Aircraft Company which have ensured of a great many

of works for the Cobra preliminary validation

I would like to express special gratitude to Chris Rumsey (NASA) for its persistence and

goodwill by publication and report preparation

19

Thank you for attention…

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