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Burst Frequency effect of DBD Plasma actuatoron the control of separated flow over an airfoil ¨®[o, xÜ, 252-5210 »z·¶¢iSyg¯Øm 3-1-1, asada@flab.isas.jaxa.jp
ÉU|È, ISAS/JAXA, 252-5210 »z·¶¢iSyg¯Øm 3-1-1, fujii@flab.isas.jaxa.jp
Kengo Asada, The University of Tokyo, 3-1-1, Yoshinodai, Chuo-ku, Sagamihara, Kanagawa,252-5210, Japan
Kozo Fujii, Institute of Space and Astronautical Science, JAXA, 3-1-1, Yoshinodai, Chuo-ku, Sagamihara,
Kanagawa, 252-5210, JapanThe flow-fields controlled by DBD plasma actuator on burst mode around the NACA0015 airfoil are simulated with
implicit large eddy simulation (ILES) using compact difference scheme, and the burst frequency effect of DBD plasma
actuator on the control of separated flow over the airfoil is discussed. The Reynolds number based on chord length isset to 6,3000 and the angle of attack is set to 14 [deg]. The DBD plasma actuator is installed at the 0 % and 5 % chord
length from the leading edge, and actuated in burst mode. For the burst mode, the nondimensional burst frequency is
set to 1 and 6. Through the present analysis, the two mechanisms of separation control are discussed. The firstmechanism enhance the vortex shedding from the separation shear layer and avoid the massive separation from theleading edge on burst mode with nondimensional burst frequency of 1. The second mechanism improves the airfoil
performance by suppressing the separation region on the burst mode with nondimensional burst frequency of 6. In
addition, it is clarified that the first mechanism is more sensitive to the location of DBD plasma actuator than thesecond mechanism and it is associated with large fluctuation of lift.
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(%$&"%  Áh&èà£³åf lÇ' Dielectric Barrier Discharge (DBD)CJ6D+29H/O8(5)(6)+GK0*{!Q°S ¸½('é CJ6D+29H/O8 Figure 1 º$ÑàX*2 à ('éRàV§çàq*'$&â} Õvf*§XÑÓ' èÚs*k'á^à %ÌÏàn ¾£§( ÑÓ('é¬rèC
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%('é

Induced flow
Exposed electrodePlasma region

Dielectric
Insulated electrode
A.C. voltage source

Figure 1 Configuration of plasma actuator.
Tbase
T

+
T=1/f


Figure 2 Burst wave image.

1

Copyright © 2010 by JSFM

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21424
force magnitude
Figure 3Force image of Suzen model.

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050
force magnitude

Figure 4Force distribution of Suzen model (DC=8).

3

Copyright © 2010 by JSFM

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S(x, y,z,t) = SSuzen (x, y,z)sin 2 (2f base t)    '&" sin2(2fbaset)'Ðc(OÅ'X&-0,'#0Ü*Û'g3Ò z'g3 Save(x,y,z)$Û'^&"eÍ Dc '^3·0$¹0$


z

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x

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1= Dc SSuzen ( x, y,z)2

Figure 5 Computational grids Whole image.

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$r¸eµ. 5 %'Z¶&Æ¶}q#Ä²3¾ Ü
Table 1. Plasma actuator parameters.

Figure 6 Computational grids near the leading edge: Zone1 (blue), Zone2(red) and model grid (green).
   '
 DI:E46<H5L;'\iY(eÍ'£(11)3
l¹&ÛAL9?3§fÔd&"fÔdh¥1$|t'   !'u&!"Ä²3¾ ÜALAL9?'{$%0sine 'u3 fbase
9?'u3f+Û$ÛAL9?¤ BR 3BR =DBD-OFFBM_5p_F6
BM_5p_F1
BM_0p_F6
BM_0p_F1

f base BR 1         =Tn

$%0Ü* f+3'&¢_j0Ü


F+ =

fbase
[Hz]

BR
[%]

f+
[Hz]

F+

N/A
5%
5%
0%
0%

N/A
6,000
6,000
6,000
6,000

N/A
10
10
10
10

N/A
600
100
600
100

N/A
6
1
6
1



32 0-.(! /$ 0-%*)1 Â'Ç3¾+&ÛfÔd3¾ "%}q'Ø$Ä²'xg]c3Figure 7&­Ü´m)¡´&-0³3­"/ÛSm)NÁ'DK=?Ø³
3­"0Üxg](Û=4°&"O×$P×$,&½
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fÔd&"ÛAL9?u$fÔdhm)Û'1}&Ó"©%ÉÈ3¾T3ª©$0+Û¥y'Â
(kc#0$Ã0ÜTbase          T

$0Ü#ÛBR=100%(Î'U `g3v0ÜAL9?MuR'3 n $0$


f+ =

DBD
locationf +c       U &1.'BIFL;3§"DI:E46<H5L;3\i'[¯g'Ò~i&!"j0ÜÎÛD:
E46<H5L;3U Õx&-/\i}qÛU Mu
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Û.&Qº$,Û 1sÙÖbÕ.ÀÕ'sÚ&r''[¯g¨¦"0$X0Üa[©&(Ò~i0[¯g3 S(x,y,z,t)Û
Ò z Suzen .'G>J
3 SSuzen(x,y,z)#¿$'&¿10Ü
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LES alp4
LES alp14
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Exp. alp14



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x-vorticity

10

0
u/a
0.3
Figure 9 Iso-surfaces of 2nd invariant of the velocity gradient tensors andchord direction velocity distributions(iso-surface is colored by x-vorticity).

x
Figure 7Cp distributions of the computations and experiments
at = 4, 14 deg.     ¦Ì(-ußË?TA(,lùjp¨,©Ü;%2"3+ ußË?TA,¯ê;Ùk+~¦)*8lùj;Ù$'¡õ|²9+%'äã8ā²9-AJSx+4|*v,²9+%'í.'ālùj;Ù:*v
'8ā<>EO=TD;_¹'8?TA+ö'-iþ  ÿ,ëÝ (,¡õ|²9; Figure 8 +Åā¥Þ6MPBN<>EO=TD;_¹ßË;Ù$"ā
û7-@TIôx,ï;Ú'7Ā²Ð)f+Å'
Figure 10 +ußË?TA,@TIxþx xÿï)²Ð;Å
8ā*Ā²9-AJSx+4|'8ā¦ÂÇ(-kā9,?TA4
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'8,:8āFigure 9 +lùj;Ù$'*v,Á*$'8,-BM_0p_F1, BM_5p_F6, BM_0p_F6,?TA(õ²9;ÅāÖ¢,û7-@TIôxþx éxÿ,ïkÑ\ì)Ñ\ì(:+lù'8,;,!'/0Ô;ÚĀÊaû-ïrñGSCQ,É 2 Xò+@TIô
û+°$"²9)*$'8āBM_5p_F1 ,?TA(-kÑ6x,³(ÀØ'8āïrñGSCQ,É 2 Xò,®,, *lù-´4,,Ôûìc(,î²ý}þúý}ÿ
a-³ªð;Å'7Ā³-¡ßz7çØ)*$'8ā¿È#ĀÔÑ(,î²ý}4[,?TA+¯.' ā
²9-ÔkÑ6lùĀm;Ā 6AJSx
 Figure 11 +ußË?TA(,{n`h;Åāç,Ð-j+é;%³;g'8,:8ā,³-W²+²98
*,?TAþDBD-OFFÿ;Āú- F+=6 ,?TAĀÏ- F+=1+%9ĀW²(-Ûø*³ªð;8ā1",²9,?TA;Å'8ā1"ĀÐ4,-<>EO=TD; 5 %,n,a-U«²)@TIô+d&´­dy±( 0.6 ~               ,^Ó+t7\"v;                  
0.8 Æ(q'8,Äá9"ā               +t7\"vĀÍÃÐÅ'8āDBD-OFF ,?TA-kÌ(í."«+kÑ6lù'7ĀÔ, 5 %,"76LPFH*h;Å'
8ā1"ĀÔÑ, Cp ,a4  6æ{b+9'7ĀkÑlù;¸"²9µ¤, Cp h;)$'8āU Burst mode,?TA+%'-kí,²9(4í."«+BM_5p_F1 ,?
TA;÷'p¨¾+lùjÙ'7ĀÔkÑ(oï9"²9+57_698æ{,KT>- *a;)$'8āµ+ F+=6 ,?TA- 0 %, 5 %,9,^Ó+Ó'4ókÑ,æ{,KT>;#ĀÔ¦§,×;g'8)Õ698āBM_5p_F1 ,?TA+ö'-ÔkÑ,æ{,KT>-Î('84,,Ñ(-kÑ6lù"²9, CP h+]'8ā,«+ BM_5p_F1 ,?TA-p¨¾+lùj('8v)lùj'*v),Yõ¾*²9+*$0.3
0'8Ā,¶º-­Ì(â 8āu/a Figure 12 -ußË?TA,»ïh;Å'8āïFigure 8 Time averaged chord direction velocity distributions and streamh-U«²(´­ds'7Ā¬é+ïĀÒé+û6lines at = 14 deg.
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Copyright © 2010 by JSFM 24 ,9-¢BM_5p_F6, BM_0p_F6£dn^E>,9-u^ $¥(b) 5 %B ,9-w $¤(c)"(e)  BM_0p_F6, BM_5p_F6,
BM_0p_F1, BM_5p_F1 tE'$!#H? $¥z F+=6 ,9-(+05*9/B  0 %, 5 %%[T H?m Oq~MKh$&$¥¤(+05*9/Q#? B  391v'}$[T¤F+=1 ,9-(+05*9/ B f'R _ L[TMKhOq"%¥ =k{(14) F+=1 '}[TMKhOq"%=a:$¥ ngS,9- $7)26.iNJc
$¥Figure 13 S,9-7)26.iN-u’w’
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Figure 11 Cp distributions of the No-control case, Normal mode case andBurst mode case at = 14 deg.

yn(a) 0 %u/U(b) 5 %(c) 10 %(d) 15 %u/U(e) 20 %(f) 40 %(a) BM_0p_F1(b) BM_5p_F1

(c) BM_0p_F6yn(d) BM_5p_F6

0.3
u/a
Figure 10 Time averaged chord direction velocity distributions and streamlines at = 14 deg.
0

Figure 12 Velocity profiles at the upper airfoil surface.

6

Copyright © 2010 by JSFM

% 24 (a) BM_0p_F1(b) BM_5p_F1(c) BM_0p_F6(d) BM_5p_F6

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¯ä )Â'*)èJç (b) BM_5p_F1
Ýs¤*v_¾^,Å¤*v`à^d¤*vL«,%ç *_¾`àP±,Üo¿(Ò$(çFigure 14 (b)_¾'`à çZP± ¤*v,´ )èFigure 15 
BM_5p_F1 bTåCLæÝ¡,´ )çFigure 14(b)q 250000 step ¤*v,´ (ç_¾'`à&b¨¦~ )+)è
 ¹"Á_¾-18D/I7,ÙÀ ç?I4;£,­vl F+=1, 6 *vl%d¯`à^Å)O\ç ¹?I4;o£`à^C0=5B
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0.004
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Figure 13Reynolds stress distributions of No-control case, Normal modecase and Burst mode case at =14 deg.
0(a) BM_0p_F1

Figure 15CL history of BM_0p_F1.

(b) BM_5p_F1

 "'! ¹«`à^dÇ'*2I4çm-1
8D/I7ÊÀQÀBM_0p_F1, BM_0p_F6 2 2I4¢Ð ç?I4;o£`à^C0=5BÞTÎÍ)èFigure 16  BM_0p_F1, BM_0p_F6 k2I4
 CL ¡-18D/I7S([Rµbâçsin2(2fbaset)V¡, Force fluctuation  ´ )èÏ
(a) BM_0p_F1 i(b) BM_0p_F6 *2I4%m
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7?I4;o !moxe )+)è
Jç(b) BM_0p_F6 2I4¢Ð¯ CL xe~ ?I4;o£Ý³ÞT#'*è *'Ö,&(ËºÎÍ)$Figure 17 i Figure
18 k time step  CL \åWæÁ_¾PÑ3I<ÜnÓ u \,·ä½åjWæY´èç CL \¯Áác+)b,bn\\È çJ¤mrÁáµª Xg %)èCL \Ã Cp \,Ú´ çCL, Cp %4@Hns )èu \·ä½ß")Ø\_¾'`à a,Æ )èFigure 17  BM_0p_F1 2I4(a)375000 step  Figure 16 -18D/I7Se {$)°
_(çÁ_¾z`àãt,S(çãtØ\Nzb,)\)è$bxe)oM%zbV,)è(b)©-18
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"ç §®¬&(çÁ'× aÁÆ(c) BM_0p_F6-10(d) BM_5p_F6
x-vorticity

10

0
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Figure 14 Iso-surfaces of 2nd invariant of the velocity gradient tensors andchord direction velocity distributions(iso-surface is colored with x-vorticity).
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7

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Figure 16 CL and force magnitude histories on BM_0p_F1 and BM_0p_F6.




8

Copyright © 2010 by JSFM 24 

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Figure 17 Local CL distributions and Cp distributions of BM_0p_F1

Figure 18 Local CL distributions and Cp distributions of BM_0p_F6






9

Copyright © 2010 by JSFM 24 

(21)


(1) Seifert, A., Darabi, A. and Wygnanski, I., “Delay of Airfoil Stall by
Periodic Excitation,” Journal of Aircraft, Vol.33 No.4 pp.691-698,
1996.
'$(2) :N, X), 9^g
-aJ b PRg
S 21 7?,J+18'!
#]Ldg(2007).
(3) :NgX)g9^, ' M J W3.=b PR -6I?2F-g
S
22 7?,J+18'!#\@dg(2008).
(4) Okada, K., Oyama, A., Fujii, K. and Miyaji, K., “Computational
Study on Effect of Synthetic Jet Design Parameters,” International
Journal of Aerospace Engineering (2010).
(5) Post, M. L. and Corke, T. C., “Separation Control on High Angleof Attack Airfoil Using Plasma Actuators,” AIAA Journal, Vol.42
No.11 pp.2177-2184, 2004.
(6) Corke, T. C., Lon Enloe, C. L. and Wilkinson, S. P., “Dielectric
Barrier Discharge Plasma Actuators for Flow Control,” Annual
Review of Fluid Mechanics, Vol. 42, pp. 505-529, 2010.
(7) Mccormick, B. W., Jr., “Aerodynamics of V/STOL Flight,”
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