The Aerodynamic Characteristics of Flaps

*° \
CUT--OUT
4°O
/0-~ COT-0U1, 0"4 ! CUT-OUT
/ /
K==
3.0 ,' ,, ,
~ ,.. O~ CUT--OUT/
3.0
~\ .
\\0-1 CUT-I/
o~/\
C~
2.o
'
ET
co,.=:~ ( ,+~. ~\ \ \ O'4NE.~ 1 \ NE~' o . 4 ,
-- m tJ " / --
Z
C. t-
~
~.
SPAN/~ /
O'~ NET ;
1.0 TT A L k, cL,a ~ ..)( FLAP sPAr9," ,.
\\
(2. o ~ ~ CI. FOR INI::INITE FLAP /
~SPANW1NEr=-GrAPPRO~ < %"/3PA~"~vt
ACk~.~L.IFT COEFFICIENT INCREMENT N-~'~/
OF FLAP ~ 0*8
FLAP SPAN//
Ck----- LIFT COEFFICIENT OF "~ "
J WIN~ ~ FLAP/
o '0.Z o'.;+ O'~ O.S I-O
OVIERAI,,k F[.AP ,SPAN/ WIN~ 5PAN.
FIG. 19. Factor K for calculating induced drag of an
elliptic wing with part-span flaps and cut-out. A/a o -~ 1.0.
I°0
\"....\." / \SPAN"~/ 1/
• . / ,, /
CD:'='C..~L= (l+j;~ ~ ~ ~/ O.G NET /
=cj h+KP=Jl\ \ / \ ,
• ='-
j i ~
-L ~/I
L-,
%- ~ "\ . \ >,. / , , ,
"2"-o~ WING: 6, APPROX.\ _~/ 0;S
DUE TO FLAR ~
EL.= LIFT COEFFiE!ENT OF
~VIN~ -v FLAP
0 0,~ 0"4 O-G Or8 1,0
OVERALL, FLAP 5PAN / WING 5PAN.
FIG. 20. Factor /t7 for calculating induced drag of all
elliptic wing with part-span flaps and cut-out. A/a o ---- 2.0.