A flight investigation of internally balanced sealed ailerons in the presence of a balanced split flap

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Material Information

Title:
A flight investigation of internally balanced sealed ailerons in the presence of a balanced split flap
Series Title:
NACA WR
Alternate Title:
NACA wartime reports
Physical Description:
4 p., 7 leaves : ill. ; 28 cm.
Language:
English
Creator:
Williams, W. C
Langley Aeronautical Laboratory
United States -- National Advisory Committee for Aeronautics
Publisher:
Langley Memorial Aeronautical Laboratory
Place of Publication:
Langley Field, VA
Publication Date:

Subjects

Subjects / Keywords:
Ailerons   ( lcsh )
Aerodynamics -- Research   ( lcsh )
Genre:
federal government publication   ( marcgt )
bibliography   ( marcgt )
technical report   ( marcgt )
non-fiction   ( marcgt )

Notes

Summary:
Summary: Flight tests were made with a modified Ryan ST airplane to determine the effect on aileron characteristics of various arrangements of balanced split flaps covering that portion of the wing span occupied by the ailerons. NACA recording instruments were used to determine aileron effectiveness. With the flaps fully extended, the aileron effectiveness was reduced by approximately 18 percent of the effectiveness measured with ailerons alone. For the partly retracted positions of the flap, the corresponding reduction was of the order of 60 percent.
Bibliography:
Includes bibliographic reference (p. 4).
Statement of Responsibility:
by W.C. Williams.
General Note:
"Originally issued May 1942 Advance Restricted Report."
General Note:
"NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution."

Record Information

Source Institution:
University of Florida
Rights Management:
All applicable rights reserved by the source institution and holding location.
Resource Identifier:
aleph - 003805102
oclc - 123907148
System ID:
AA00009462:00001


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I NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS


' I...



'i l WiARTIME REPOiRT
,,. ORIGINALLY ISSUED
:... May 1912 as
Advance Restricted Report


A FLIGHT DIVESTIGATICH OF INTER ALLY

BALANCED SEALED AILERCS IN THE PRES CE


OF A BALANCED SPLIT FLAP

By W. C. Williams


Langley Memorial Aeronautical Laboratory
Langley Field, Va.


WASHINGTON


ICA WARTEME REPORTS are reprints of papers originally issued to provide rapid distribution of
dLice research results to an authorized group requiring them for the war effort. They were pre-
igily tield under a security status but are now unclassified. Some of these reports were not tech-
telAy edited. Al have been reproduced without change in order to expedite general distribution.
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NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS


ADVANCED RESTRICTED REPORT


A FLIGHT INVESTIGATION OF INTERNALLY

BALANCED SEALED AILERONS IN THE PRESENCE

OF A BALANCED SPLIT FLAP

By W. C. Williams


SUMMARY


Flight tests were made with a modified Ryan ST
airplane to determine the effect on aileron character-
istics of various arrangements of balanced split flaps
covering that portion of the wing span occupied by the
ailerons. NACA recording instruments were used to
determine aileron effectiveness.

With the flaps fully extended, the aileron ef-
fectiveness was reduced by approximately 18 percent
of the effectiveness measured with ailerons alone.
For the partly retracted positions of the flap, the
corresponding reduction was of the order of 60 percent.


INTRODUCTION


Results are presented herein for part of an ex-
tensive investigation conducted by the NACA to develop
a satisfactory lateral control device for use with full-
span flaps. In the full-span flap arrangement, with
which this paper is concerned, balanced split flaps
are located over that portion of the wing span covered
by the ailerons, the inboard portion of the span pre-
sumably being fitted with slotted or Fowler type flaps.
The investigation consisted of flight tests in which
the full-span-flap lateral control arrangement was
simulated by locating a flap of the balanced split
type under that portion of the wing span covered by
the ailerons. The tests were confined to measure-
ments of the effectiveness of the lateral controls.

These flight tests were conducted by the NACA at
Langley Field, Va.












SYMBOLS


p rolling velocity, radians per second

V true airspeed, feet per second

Vi indicated airspeed, miles per hour

b wing span, feet

c, wing chord

8f flap deflection


APPARATUS


The Rysn ST airplane with internally sealed and
balanced ailerons is described in reference 1. For
the present investigation, balanced split flaps were
mounted or fi ed bralkots over the outboard portion
of the span, s shown. in figures 1 and 2. Th3 flaps
covered 38 pe':cer.t of the wing span and had a chord
of 20 rercenc of the win9 chord.

The eirpiane was tested with several arrangements
of flap deflection, fore-and-aft positions, and of the
gap becKa-n -'te flip and the lower -urface of tUe wing.
Theq.. aLs-rnj:rlients are 'l.3.ustrited in figures 3 to 6.
Stanv.a-i IACA rocori1ng instru-n en's wsr'e -.lied to measure
air .j.ct., con.tcl positi.-n, control force, and rolling
velocity.


TESTS AND RESULTS


The flig-ht-tet procedure to dete--,ire .ilernn ef-
ffecti ". ,t \.aE th;e sa-ce as the o-r ,: t tlescrih bd in
re" ".'.* '. .. ..r "ere r.e..i.e at. anr .c3 aa 3.y I: ard
85 L i. .i If r.h'-r. The r.crrepp i.1ing vaYnes of air-
pl a e lit c o ':- Jii entt we.re app rc-. 1 rt ately 1.4 and.0.56,
re.--e elE. ebe 'detoi3ed 'esuJ u of "the flieg t tfe ts
a-; i'.-: n' t d in Tfi Jr- : 7 t3 11 n wJ ichti a.ll]:-on
e', :. -r ..:-.;< i'-. r ,- / v is pn tted as a f'.rc .I c
o/ i.. r,. :,-. ~: .al il." r ? .. .'ur'.ialr of the
reculta Is p-escuued. in the follo;.ng table:













Aileron effective-I Aileron effective-
ness (maximum 2x ) ness (percent of
Flap arrangement 2V effectiveness with
I ailerons alone)
Right roll Left rol ailerons alone)


Ailerons alone 0.061 0.078 100

Flap deflection, .051 .063 82
400; gap, 0.02cw;
leading edge
under aileron
hinge line

Flap deflection, .05 .064 82
400; gap, O.04cw;
leading edge
under hinge line

Flap deflection, a.022 a.0295 37
140; gap, 0.02cw;
leading edge
0.0325cw ahead
of hinge line
a
Flap deflection, .0263 a.0323 42
80; gap, O.Glcw
sealed; leading
edge 0.07cw
ahead of hinge
line


aAverage value



The low aileron effectiveness obtained with the
partly deflected flaps confirms unpublished wind-tunnel
data for a similar arrangement and additional wind-
tunnel tests are now under way in an attempt to determine
a more favorable flap operating path. It is possible,
however, that this low aileron effectiveness at partial
flap deflections is not, in reality, a serious drawback,
because a two-position flap arrangement may be used in
which the flap passes quickly through the region of low
aileron effectiveness. The balanced split flap is
intended for use in the duplex arrangement wherein a












Fowler or a slotted flap is used over the inboard
portions of the wing; therefore, partial flap deflec-
tions might very well be confined to movement of these
inboard portions.


Langley Memorial Aeronautical Laboratory,
National Advisory Committee for Aeronautics,
Langley Field, Va.




REFERENCE


1. Williams, W. C., and Kleekner, H. F.: A Flight
Investigation of Internally Balanced Sealed
Ailerons. NACA AR.R., Dec. 1941.






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Fig. 1


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2. Three-view drawing of the Ryan ST airplane with fixed
balanced split flap.


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hACA


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Figure 5. SkeLch oL IntLerrtlly balan&cea aileron ana ri-.!-ceia-splli-i lIp arrangement as usea on
afln 5' airplane; rully extended position ,tr, 2-percert gap.


_____ r.F~ /l
N' ____


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Figure 4. Sketch of ailron ana balanced-splIL-rlap arrangement as used on Fyan ST airplane;
rully extended position with 4-percent gap.









Figu. 5,6


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Figure 5. Sketch of aileron ano Dalanced-split-f'lap srrsrgement
partly retracted position with 2-percent gap.


as used on tyan ST airplane;


Plgure 6. Sketch of aileron and balanced split flap as used on 3yan ST airplane; partly
retracted position alth sealed gap.


BACA


Y .-L.'.FroL







Figs. 7,8


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v

o 60
0o 105

L 130 0 a



Left ht
35) 2 10 10 20 30
Change in tatl leon eagle, deg






OB


Figure 7.- Variation of helix angle pb/2V with change In aileron
deflection. Ryan ST airplane with internally balanced ailerons alone.



.08


So 57







30 20 10 0 10 20 50
C range in total aile on angle, deg


--- -- -- ^ -- -- ^------- ---- ---- ---- ----
l04




.08

Figure 8.- Variation of helix angle pb/2V with change In total aileron
angle. Ryan ST airplane with Internally balanced ailerons In the
presence of the 0.20c, balanced split flap. 6f = 400; gap =0.02cw;
leading edge of flap directly under aileron hinge line.


&CA







NACA


Figs. 9,10

-- --- -- -- -___--- -- --- --- -- ---



_____ ___ __l 0 ___
.08




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Left 0/ Rig t
50 20 10 10 20 50
Change in total aileron argle, deg








.08


Figure 9.- Variation of helix angle pb/2V with change in aileron
deflection. Ryan ST airplane with internally balanced ailerons
in the presence of the O.20c balanced split flap. bf = 400;
gap =0.04cw; leading edge of flap directly under aileron hinge line.



.08


g 57
-.4


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Left --_ __ Right
35 20 10 O10 20 50
change in total -ailern angle, leg








.081 1 11 __
Figure 10.- Variation of helix angle pb/2V with change in aileron
deflection. Ryan ST airplane with internally balanced ailerons in the
presence of the0.20c, balanced split flap. bf = 140; gap =0.02c,;
leading edge of flap0.0525cw ahead of aileron hinge line.







UaCA Fig. 11










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i i

"r4 01385 I_ _
---------------04---
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_-.- r- _.C)


Left i___ I ht
30 20 10 .-- 10 20 30
__ Change_ in total aileron angle, deg___
8 I






I _______ I---.. ~ I ___ I_ .


Figure 11.- Variation of helix angle pb/2V with change in aileron deflection.
Ryan ST airplane with internally balanced ailerons in the presence
of the 0.20c, balanced split flap. 6f = 8 ; gap = 0.01cw sealed; leading edge
of flap 0.07c ahead of aileron hinge line.














































































































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UNIVERSITY OF FLORIDA

2 08I06i4825


UNIVERSITY OF FLORIDA
DOCUMENTS DEPARTMENT
120 MARSTON SCIENCE UBRARY
.O. BOX 117011
"-AINE.\'ILL E. FL 32611-7011 USA


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