The need for a computational tool and therefore a validation database is based on ... The test was conducted at dynamic pressures, q, from 10 lb/ft2 to 50 lb/ft2.
, /
J /
/ NASA
Technical
Memorandum
107419
Wind Tunnel Measured Effects on a Twin-Engine Short-Haul Transport Caused by Simulated Ice Accretions Data
Report
Andrew Reehorst, Mark Lewis Research Center Cleveland,
Brenda
Ohio
Gile
Langley
Research
Hampton,
May
Laflin
Virginia
1997
National Aeronautics and Space Administration
Center
Potapczuk,
and Thomas
Ratvasky
WIND
TUNNEL MEASURED EFFECTS ON A TWIN-ENGINE SHORT-HAUL TRANSPORT CAUSED BY SIMULATED ICE ACCRETIONS: DATA REPORT
Andrew
Reehorst
Mark Potapczuk Thomas Ratvasky NASA
Lewis
Research
Cleveland,
Center
Ohio
and Brenda NASA
Gile
Laflin
Langley Research Hampton, Virginia
Center
Abstract The purpose of this report is to release the data from the NASA Langley/Lewis 14 by 22 foot wind tunnel test that examined icing effects on a 1/8 scale twin-engine shorthaul jet transport model. Presented in this document are summary data from the major configurations tested. The entire test database in addition to ice shape and model measurements is available as a data supplement in CD-ROM form. Data measured and presented are: wing pressure distributions, model force and moment, and wing surface flow visualization.
Nomenclature b
wing
Cs
slat chord
length,
Cw
wing
element
C_
forward
Cmf
mid flap
Caf
aft flap
Cp
pressure
NASA
span,
feet
main
TM-107419
flap
feet chord
element
element element
chord
chord chord
coefficient,
length, length,
length, length,
feet feet
feet feet
(pn-patm)/q
1
CD
drag
coefficient,
CL
lift coefficient,
Cm
pitching
Parr,
atmospheric
po
pressure
q
free-stream
S
wing
(_
angle
13
sideslip
8f
flap
Drag/qS Lift/qS
moment
coefficient,
pressure, at specific
area,
dynamic
pitching
moment/qSb
Ib/_
model
tap n=1,2...,
pressure,
Ib/ft 2
Ib/ft 2
ft 2
of attack,
deg
angle,
deflection
deg angle,
deg
Introduction
Aircraft icing simulation methods are currently under development in order to provide design and certification tools for the aircraft industry. These tools include simulation methods for ice accretion, ice protection system performance, and aircraft performance degradation, and scaling methods. As in all computer simulations of physical processes, it is important to determine the quality of the prediction. This paper presents results of an experimental program designed to provide validation information for performance degradation of a commercial transport aircraft with ice accumulated on its wing and tail. It is important to understand how ice accretions can influence the aerodynamic behavior of an aircraft in order to determine the ice protection requirements and to understand the effects of an ice protection system failure. This is currently done through flight and wind tunnel tests using real or artificial ice accretions. The development of a reliable computational tool for evaluation of performance changes due to ice accretion would help to decrease the number of such tests and in turn reduce
the time and costs
of design
and certification.
The need for a computational tool and therefore a validation database is based on the desire of several aircraft manufacturers to determine the size and shape of ice accretions which are critical to aerodynamic performance. Currently, there is not a great
deal
of such
been
several
data
studies
publicly
of airfoil
available and
wing
for a complete models
with
aircraft
leading
with
edge
ice.
There
ice accretions
have 13.
These have provided information of sufficient quality to assess the accuracy of computational simulations and have helped to point out areas for improvement of such simulation methods. The data from this test program should serve a similar purpose
NASA
TM-107419
2
for the evaluation
of simulation
methods
applied
to complete
aircraft
configurations.
Presented in this document are summary data from the major configurations The entire test database in addition to ice shape and model measurements available as a data supplement in CD-ROM form. A discussion of the test available in Reference 4. Test
tested. is results is
Apparatus
The wind tunnel test was conducted in the NASA Langley 14 by 22 foot subsonic wind tunnel. The test article was a 1/8 scale twin-engine short-haul jet transport model. Several aircraft configurations were examined including various flap and slat deflections, with and without landing gear. Two separate configurations of leading edge ice contamination configuration.
Facility
were
tested
in addition
to the
uncontaminated
baseline
Description
The NASA atmospheric
Langley 14 by 22 foot Subsonic wind tunnel with a test section
Tunnel S is a closed-circuit, single return, that can be operated in a variety of
configurations: closed, slotted, partially open, and open. For this test, the test section was operated in the closed configuration. The closed test section is 14.5 feet high by 21.75 feet wide by 50 feet long.
Model
Description
The model used for this test was a 1/8 scale twin-engine subsonic transport with multielement wings e shown in figure 1. The empennage consisted of a vertical tail with rudder and a motorized horizontal stabilizer with elevator. The engines were represented and landing
Ice shape
by two flow-through configurations.
nacelles.
The
model
was tested
in cruise,
take-off,
description
Two different artificial ice shapes were used for this test. They were based upon drawings of ice shapes used by Boeing (for a mid 1960s wind tunnel test of a similar aircraftT). The two shapes represent realistically sized ice accretions for this configuration. Because of the age of the information, no clear documentation was identified stating the method of determining these shapes, however, it is conjectured that the shapes were developed using either the Boeing ice shape prediction technique 8 or the method described in the FAA icing handbook 9. The
Boeing
outlines
were
transformed
to provide
the appropriate
scale
and orientation
for production of the artificial ice shapes in the NASA Lewis Research Center's woodmodel shop. The ice shapes were manufactured for inboard and outboard wing, vertical tail and horizontal tail surfaces for both sides of the aircraft. The ice shapes
NASA TM-I07419
3
were attached to the aircraft model using mechanical fasteners and double sided adhesive tape. Figures 2 and 3 show the artificial ice shapes attached to the horizontal tail. After being attached, the joints between the aircraft model and the ice shapes were filled using modeling clay. Profiles of the ice shapes installed on the aerodynamic surfaces were measured after the test to document the ice shapes used and their alignment to the aircraft surfaces.
Roughness
determination
The roughness size for the model ice shapes was calculated by scaling down experimentally measured roughness. Roughness elements have been measured in the NASA Lewis Icing Research Tunnel and have been determined to be on the order of 0.02 inches t°'11 This approximate value does not appear to vary significantly as the chord length or airfoil section changes, and is therefore considered reasonable for the full scale transport ice accretion. The next step in calculating the model ice roughness size was to determine an appropriate scaling method. Neither full scale roughness nor geometrically scaled roughness are appropriate, since neither will appropriately address the change in the flow field due to the presence of roughness. The method selected was to scale the roughness with the ratio of the model to full scale boundary layer momentum thicknesses. The momentum thickness was calculated for both the full scale and 1/8 scale ice shapes using Cebeci's IBL computer program 12,_3. The average ratio between the two momentum thickness was 0.5411. When the full scale roughness size of 0.02 inches is multiplied by the scaling ratio of 0.5411, the scale model roughness size becomes 0.011 inches. This corresponds to a roughness that falls between a #60 and #70 grit. #60 grit, with nominal 0.0117 inch diameters, was utilized for this experiment. Figure 4 is a close-up view of the grit applied to the artificial ice shape.
Test
Procedures
The test was conducted at dynamic pressures, q, from 10 Ib/ft 2 to 50 Ib/_ corresponding to Reynolds numbers of 8.2 x 10 S to 1.8 x 108 and Mach numbers 0.08 to 0.18. Data was obtained over an angle-of-attack with sideslip varying from -10 ° to 10 °. Aerodynamic forces and moments balance and wing pressures were devices from flush pressure ports. electronically corrections tunnel wall Two
were obtained obtained with Angle-of-attack
range
from
-4 ° through
of 16 °
with a six-component strain-gauge electronically scanned pressure and sideslip were measured
in the model/model support system. Wing, body and wake blockage to free stream dynamic pressure TM were applied as were corrections for interference _s.
different
flow
visualization
techniques
were
utilized
during
this test.
The
first
technique was a surface oil method that utilized motor oil with a fluorescent additive viewed under ultraviolet lighting. The oil was painted on the left wing surface in a span-wise direction. When the proper test condition was achieved an overhead photograph was quickly taken with an ultraviolet flash. Due to the restrictive nature of
NASA
TM-107419
4
this testing technique, with this technique.
only
a select
number
of model
configurations
were
examined
A less restrictive technique was utilized for almost all test conditions. This technique makes use of fluorescent mono-filament wing tufts glued to the left wing. The tufts were digitally photographed using an ultraviolet flash. The "mini-tufts" do not provide quite the image resolution of the oil flow visualization technique, but proved to be much more practical for regular use since they required little upkeep from one test condition to the next.
Data
Presentation
Figures
5 through
supplement
86 represent
a summary
of the data
available
on the data
CD-ROM.
The figures are organized such that figures 5 through 28 display the results of the testing with the intermediate temperature ice shape (Ice #2, figure 3) with the model the 8f=40 ° wing configuration. Results shown are the C L, C m, C o, C_, C n, C¥ curves, • pressure coefficient curves, oil flow visualization, and mini-tuft flow visualization
in
images. Figures 29-46 represent the results for Ice #2 with the model in the cruise wing configuration. Results shown are the C,, Cm, CD, C_, C n, C¥ curves, pressure coefficient curves, and mini-tuft flow visualization images. Figures 47-58 represent the results of testing with the low temperature ice shape (Ice #1, figure 2) with the model in the 8f=40 ° wing configuration. Results shown are the C L, C m, C D, C_, C n, C¥ curves, pressure coefficient curves, and mini-tuff flow visualization images. Figures 59-69 represent the results for Ice #1 with the model in the 5f=30 ° wing configuration. Results shown are the C L, Cr,, CD, C_, Co, C¥ curves, pressure coefficient curves, and mini-tuft flow visualization images. Figures 70-86 represent the results for Ice #1 with the model in the cruise wing configuration. Results shown are the C L, Cm, CD, C_, Co, C¥ curves, pressure coefficient curves, and mini-tuft flow visualization images.
Data
Supplement
This report and its data supplement (in the form of a CD-ROM) are available from the NASA Center for AeroSpace Information (CASI), 800 Elkridge Landing Road, Linthicum Heights, Maryland, 21090-2934 (NASA Access Help Desk (301)621-0390). On the CD-ROM, the following information is available: -Test database--the DAS program
NASA
TM-107419
database is available
is in Data Analysis System 16 (DAS) "ffsif" format from NASA Langley Research Center, Hampton,
5
(the VA)
-Model
photographs
-Model measurements--measurements of the model (made with portable laser profilometer developed -Model
measurements
notes--model
-Ice shape
measurements--detailed
-Ice shape
measurements
-Mini-tuft
images
-Mini-tuff
image
notes--ice
measurement measurements shape
with the ice shapes installed by Hovenac and Vargas 17) file
naming
of the
convention
ice shapes
measurement
file naming
convention
catalog
Acknowledgments The authors would like to thank the efforts of Mr. Mario the model measurements with his laser profilometer.
Vargas
for his help
in making
References ,
Reehorst, A., Potapczuk, M,, Ratvasky, T., and Gile Laflin, B.,"Wind Measured Effects on a Twin-Engine Short-Haul Transport Caused Accretions", AIAA-96-0871, NASA TM-107143, January, 1996.
1.
Bragg, M.B. and Spring, S.A., "An Experimental Study of the Flow Airfoil with Glaze Ice," AIAA Paper 87-0100, Jan. 1987.
2.
Khodadoust, A. and Bragg, M.B.,"Measured Wing with a Simulated Ice Accretion," AIAA
.
.
°
Tunnel by Simulated
Field
Aerodynamic Performance Paper 90-0490, Jan. 1990.
Flemming, R.J., Britton, R.K., and Bond, Lewis Icing Research Tunnel," AGARD Dec. 1991.
T.H., "Model Rotor Icing Tests Conference Proceedings 496,
Reehorst,
A., Potapczuk,
T., and Gile
Measured Accretions",
Effects on a Twin-Engine AIAA-96-0871, NASA
M,, Ratvasky,
Short-Haul TM-107143,
Laflin,
Transport January,
B.,"Wind Caused 1996.
Gentry, Garl L. Jr., Quinto, P. Frank, Gatlin, Gregory M., and Applin, T.,"The Langley 14- by 22-Foot Subsonic Tunnel: Description, Flow and Guide for Users",NASA TP 3008, September 1990.
NASA
TM-107419
6
about
Ice
an
of a Swept
in the NASA Paper No. 9,
Tunnel by Simulated
Zachary Characteristics,
Ice
.
7. .
.
Paulson, 1/8-Scale 1977. Hill,
John P.,"Wind-Tunnel Results of the Aerodynamic Characteristics of a Model of a Twin-Engine Short-Haul Transport", NASA TM X-74011, April
Eugene
G., Personal
shapes AGARD
for evaluating aircraft handling and performance Advisory Report No. 127, September 1977. Gensemer,
Airframe Icing Technical December 1963. 10. Hansman, Accretion",
and
1992.
Ramon,
D.T.,
theoretical
November
Wilder,
Bowden,
W.,"A
communication,
A.G., Data,
R. John,"Analysis AIAA-92-0298,
experimental
and Sheen,
means
FAA Technical
Data,
FAA Technical
Generation
12.Cebeci, T. and Chang, K.C.,"Calculation of Incompressible Layer Flows",AIAA Journal, Vol. 16, No. 7, July 1978.
14. Heyson, Harry H.,"Use of Superposition Tunnel Interference Factors for Arbitrary to V/STOL 15. Rae, W.H., Inc., 1984.
Models",
NASA
Jr., and Pope,
16.Graham, A.B.,'q'he Data NASA Langley Research
February
A,Low-Speed
Wind
Analysis Center,
17. Hovenac, E.A., and Vargas, Icing Wind Tunnels", NASA
NASA TM-107419
in Aircraft
with
7
ADS-4,
Ice
Leading
Rough-Wall
Edge
Boundary-
N.D. and Lee, K.,"Airfoils with of Fluid Mechanics, Vol. 163,
pp.
WindReference
1969. Tunnel
System, System April, 1993.
M.,"A Lsser-Based TM 106936, June,
5,
of
Report
in Digital Computers to Obtain Configurations, With Particular
TR R-302,
Paper
Summary
of Surface Roughness Associated NASA TM-106459, January 1994.
13. Cebeci, T., Clark, R.W., Chang, K.C., Halsey, Separation and the Resulting Wakes",Journal 320-347, 1986.
ice accretion
characteristics",
C.A.,"Engineering
of Surface Roughness January 1992.
11 .Shin, Jaiwon,"Characteristics Ice Accretion",AIAA-94-0799,
to predict
Testing,
Description
Ice Shape 1995.
John
Wiley
and User's
Profilometer
& Sons,
Guide",
for Use in
Figure
1.--NASA
Figure
NASA TM- 107419
Langley
2.--Ice
1/8 scale twin engine
shape
#1 on the model
8
subsonic
horizontal
transport
tail.
model.
Figure 3._lce
shape
Figure 4._Grit
NASA
TM-I07419
#2 on the model
applied
9
horizontal
to ice shapes.
tail.
.2 .1
-.1 -.2 a
m
-.3
-"_%
-.4
_
R_
[] o O A
_S
-.5
Icing
323. 314. 319. 308.
TallW'_ Outbmrd All Oea_
-.6 3.0 2.5 2.0 1.5 CL 1.0
/
.5 0 ".__,
u., de_
C0
Figure 5.--Effects of Ice #2 on longitudinal aerodynamic characteristics of the model in the 8_=40° configuration.
NASA TM-107419
10
o
314.
O_ltboe.rd Wing
[]
323.
Tail
0
319.
All
A
308.
Cle_n
.06
.03
C/
0 -.03
-.06
.06
.03
c.
o
L_
-.03
-.06 : .4
.2
Cy
0
.m.
_
T
v
v
''_r
-.2
I
I
I
I
I
I
I
I
I
I
I
I.ll
I
I..I
I
I_
Figure 6.-Effects of Ice #2 and sideslip on the lateral characteristics of the model in the 8f=40 ° configuration.
NASA
TM-I07419
11
aerodynamic
O []
Run
king
314, 308.
Outbo_ Wing Clean
["+" inside symbols indicates
-13
lower sarfac_ pressures]
y = gO.561n
-13 -11 • y = 37.4gin. Cp "7" -5
-1.
-13 • -11 • ._
•
"7
"
y = 28.20ia.
Cp.5 ;Ju
-13
-9
y = 16.0gin.
Cp -7 -5 -3 .1 1 .v./cw
x/_ _=6
_.
Figure 7.--Effect of Ice #2 on the wing pressure distributionfor the model in the 5_=40° configuration.
NASA
TM-107419
12
Run 0
314.
Outbc_d W'mg
[]
308.
Clean
r' +" inaido aymbola
-13
1_ing
indicaX_ lower
su_ffac_ pream_res]
-If -9
y = 63.00 in.
-7
%._ -3 1, -13 -II .9
Y = 58.92 in
-7
Cp._ -1
-13 -11 -9
y = 49,56
in.
Cp -7 -5
x/c 5
x/c_
x/_
x,'en:
*/c 4
0_= 6%
Figure 7 (concluded).--Effect of Ice #2 on the wing pressure distribution for the model in the 5f=40° configuration.
NASA
TM-107419
13
Run
Icing
©
314.
Olltboazd W'n_
[]
308.
Clean
g' +" inside _mbols
-13
imliemes
lower sar_ee
pregstres]
-11 y = 't0.56ia.
-9 -'7
Cp._ -3
-1! iI
mm__J
-13 -11 y = 37.44
-9 -71
Cp.5 .3_r -t-
l
w,,.
-13 -11
m
.g .
y = 28._) in.
E
¢p-7
-1 1,
_d_ "13r " C
• -119I
y = 16.08 in.
-7 io .51
"I [
_,
d
._c_
x/_a=
xk_
_c_
If}".
Figure 8.--Effect of Ice #2 on the wing pressure distribution for the model in the 5,=40 ° configuration.
NASA
TM-I07419
14
Run 0
314.
[]
308.
Icing Outboa_-dW'mg Clean
["+"ir_idcwmbols indicates lower surfaceprc_m_es]
-13 -11 -
y = 63.00 in. -7-
_._ -3-
.I
-13
.
y = 58._ in
C P.5-7 I
-13 -11 ,y = 49.56 in. Cp -7
.1 1
o
1
2
3
A
3
_
7
8
_ 10
Me w
x/c_
z,/Sy
x/e_:
¢x= 10%
Figure
8 (concluded).--Effect
for the model
NASA
TM-107419
in the
_=40
of Ice #2 on the ° configuration.
15
wing
pressure
distribution
© []
Run
]zing
314, 30E
OutIEw_mIw_ Wing Clean
["+" inside symbols indicat_
-13
lowar aarfa_
pr_sutas]
-II y = 40.56 in.
-9 -7
Cp._
i
-3 .| [ -13 -11 .9 q
y =37A4
in
-7
Cp.5 -3 1 -13 -11 y = 28.20in
-9
Cp -7
i.
-3,
x../c"I3F .
y = 16,0g in_
U
,1
.2
.3
.;5
.4
,B
.7
.i,I
,_1 1,0
x/c. = 13 °.
Figure the
NASA
9.--Effect
of Ice #2 on the wing
pressure
8,=40 ° configuration.
TM-107419
16
distribution
for the
model
in
RUB
r'+-
0
314.
[]
308.
L-sid_ _ymbol_
Icing Outboard
W'm 8
Clean
ladicmt_
lc_wct sur_ac_ pr_gut_]
y = 63.00 in_
"if 1 -13 -11 y = 5g,_2 in
-9 -7
Cp.s °_
-1 _" 1 _..._ -13 -11 y = 49.56 in-
-9 -7
Cp.5
l
.1
.2
,3
.4
.5
,6
,7
,_1
,_
l,O
O_
x/c_ _=
13 °.
Figure 9 (concluded).--Effect of Ice #2 on the wing pressure distribution for the model in the 8f=40 ° configuration.
NASA
TM-107419
17
0 D
F'+" i_ido
-13
Run
_ing
314. 308.
OutboardWing Clean
_mbolB
iaadi_
lowar s_
_o_roJ]
-11 y = 40.56 in
-9 -7
Cp._ -3 -1 1 -13 -11 y = 37.44in.
-9 -7
Cp._ -3 -1 1 -13 -11 -9 •
Y = 2E20 in
"i
_
_.
7_
_ p
-,,_cs - 13 -II -9
y = 16.08 in.
_.
Cp -7 -5 .3 .1 1 x_ w
:_ o¢=15 °.
Figure lO.mEffect of Ice #2 on the wing pressure distribution for the model in the 8f=40 ° configuration.
NASA
TM-107419
18
F+"
-13
R_a
Icing
0
314.
_tboal_ W'mg
[]
30g.
Clean
ir_ide m/mbola
tlodieates
1ow_ s_
_r_l
-II y= 63.00_n
.9
-5 -3 -1 1 -13 -11 y=58._in
-9 -7
¢P.5 -3 -1 1 -13 -11 y = 4956 _n
-9 -7
Cp.s -3
I
x/c s
x/%
r,/_-
rJe_
x/c_
a_= 15°.
Figure 10 (concluded).--Effect of Ice #2 on the wing pressure distribution for the model in the 5f=40 ° configuration.
NASA
TM-107419
19
Figure
NASA
11 .--Wing
TM-107419
mini-tuft
flow visualization
for outboard
20
ice #2, (5f=40 °, (_=4 °, run 314condition.
Figure
12.--Wing
NASA
TM-107419
mini-tuff
flow visualization
for outboard
21
ice #2, _f=40 °, e_=lO°, run 314 condition.
Figure
13.--Wing
NASA
TM-107419
mini-tuff flow visualization
for outboard
22
ice #2, _=40 °, _=14 °, run 314 condition.
Figure
14.--Wing
NASA TM-107419
mini-tuft
flow visualization
for no ice, 5f=40 °, _=4 °, run 314 condition.
23
Figure
15.--Wing
NASA TM-107419
mini-tuft
flow visualization
for no ice, 5f=40 °, _=10 °, run 314 condition.
24
Figure
16.--Wing
NASA TM-107419
mini-tuft
flow visualization
for no ice, 5f=40 °, _=14 °, run 314 condition.
25
Figure17.--Mainwingflow visualization forice#2, 5f=40
Figure
NASA TM-107419
18.--Main
wing flow visualization
26
°, tz=0 ° condition.
for ice #2, 5f=40 °, et=8 ° condition.
Figure
19.--Main
Figure 20.--Main
NASA TM-107419
wing flow visualization
for ice #2, _=40 °, o_=10° condition.
wing flow visualization
for ice #2, _=40 °, (z=12 ° condition.
27
Figure
21 .--Main
Figure 22.qMain
NASA
TM-107419
wing flow visualization
for ice #2,
_f=40 °, _=13 ° condition.
wing flow visualization
for ice #2,
_f=40 °, c_=15° condition.
28
Figure 23.--Main
wing flow visualization
for no ice, 5f=40 °, o_=0° condition.
Figure
wing flow visualization
for no ice,
NASA TM-107419
24.--Main
29
5f=40 °, o_-8 ° condition.
Figure 25.--Main
wing flow visualization
for no ice,
Figure 26.--Main
wing flow visualization
for no ice, 5f=40 °, a=12 ° condition.
NASA TM-107419
30
5f=40 °, o_-10 ° condition.
Figure 27.--Main
wing flow visualization
for no ice, _=40 °, c_=13° condition.
Figure 28.--Main
wing flow visualization
for no ice,
NASA TM-107419
31
5f=40 °, o_=15° condition.
.2
'\\0 -.1
Cm
-.2
]C'll_
RIlII -.3
o [] A r_
-.4
-°5
512. 500. 495. 516. 431.
Vectioal Tail Tail All Inboard Wing Clean
-.6
© 3.0 2.5 2.0 1.5 CL 1.0
5
°/
f.
• ,de8
Figure 29.--Effects of Ice #2 on longitudinal model in the cruise configuration.
NASA TM-107419
CD
aerodynamic
32
characteristics
of the
o
512.
[]
500.
Vt_dr,,al Ta.i,l Tail
495. A
516.
r,,
431.
All InboardW'mg Clean
,06
.03
Cl
0 -,03
-,06
,06
,03
c.,
L
o
_
_
i
i
i
--_
_m_
-,03
-,06
.4
,2
C¥
0
-°2
-,4-
Figure 30.--Effects characteristics
NASA
TM-107419
i
i
i
of Ice #2 and sideslip on the lateral of the model in the cruise configuration.
33
aerodynamic
Run ©
516.
[]
495.
_,
431.
I_in_ _W'I_ All Clean
r' +" inside symbols in_eslee lower _urface pr_zsuces]
-13 -ll
y = _.36
-9
in.
Cp.7
m i
i
m
n
-13 -11
y = 37,44 in.
-9 -7
cp._ -3 /
1 -13 -11
y =28.2D_
.9 .7
Cp._ -3 -I ,"t_
_ _|---|
m
i
||||
_O -13 x/c s oil y = 16.08 in.
og
Cp -7 -5 -3 -1 • .1
| .2
.3|
A|
| .:5 .b|
.7
.8
._
1.0
!{
I ,._
| | | .50 J31.UO
x/c_ N=_.
Figure 31 .mEffect of Ice #2 on the wing pressure distribution for the model in the cruise configuration.
NASA
TM- 1074 t9
34
Ran
]ci_
o
516.
[]
#95.
0
431.
Int_oa'aWir_
r'+" ir_ide _tmbols
-13
i._lie/e8
lower s_filee
p_sltes]
-11 yffi 63,00 in.
-9
%-:'
-5 .31
-13 -ll y _58,92in
Cp._
m-
,
i
,
,
i
i
i
1
-13 -11 y ffi49.56 i_
-9 -7
Cp.s -3 -1' _
-
-
i___
x,,ew
i
r/e_¢
.r/_
x/tag
a= 6 °.
Figure model
NASA
TM-107419
31 (concluded).--Effect in the
cruise
of Ice #2 on the
configuration.
35
wing
pressure
distribution
for the
Run 0
516.
D
495.
AH
0
431.
Clma
r' ÷" i_id_
-13
Icing _W'mg
_rmboli
i_licAt_
lower surf_
presume]
-11 y --40.56 in.
-9 .?
Cp._ -3
l
I
I
I
m i
i
1
,
-13 . -11 . y= 37.44 in. Cp "7' °_ W
1 -13
I
-11 -g .7 Cp._
k,
-I
/ ||a| .
.
.,._..-.TI-
r
.
,
%
-T
vV-_-,---,
-13 -11 y = 16.08in.
.g
,.
Cp -7 b-
-1 l
., . . .,.-.-:-7:.-!
N
, .._ ._o .4_l.bo x/e_
_.0 y-/¢_¢
Oc= 10 °. Figure in the
NASA
TM-107419
32.--Effect cruise
of Ice #2 on the
wing
pressure
configuration.
36
distribution
for the model
]dng
Ran 0
516,
[]
495,
["+" ]naid_
-13
Wing
In_ All
aymbola
indicaa_
lower
sutrf_ce
_mlsca]
-11 y= 63.00
.9
in.
-7
q, °3q -|| 1
till/
-13 -ll
y= 5B.92in
-9 Cp
-7 -5
E
.3 __
-13 -II
y = 4g.56 in.
.g -7
Cp._ -3 oll ¢--e,,b..4MMNmm ,I ,2
x/c s
3
,5
A
x/c w
Figure 32 (concluded).--Effect for the model in the cruise
NASA
TM-107419
.0
.7
._
,9 1,0
a= 10_.
r./elF
z,_-
of Ice #2 on the wing pressure configuration.
37
x/c_t"
distribution
Run
-13
o
516.
[]
495.
A
5O0.
[_'+" inlide
_mbols
]eiag Inbotrd Wing All
Tail
8ttrf.aex; pr_are_]
indicateslower
-11
y = 4-0.56 flo.
-9 -7
Cp.s -3 -1 m
1
nail
-13 -11 y = 37.44
.9
in.
Cp -7 .5 .3 .1
_m m
1
......I......J
-13 -11
y -- ._8._) _-
-9 -7
Cp._ .3 -1
.-r-r.
1
iommi |
I
|
|
-13 xA:4r
-11 -9
y --16.08 in.
Cp -7 -5 -3' -1
_o • .-_ .- -. _,-..._.: x/c,,,
_'.o rdc_
= 13°. Figure 33.--Effect of Ice #2 on the wing pressure in the cruise configuration.
NASA
TM-107419
38
distribution
for the model
Icing O
516.
[]
495.
Inboard ",N_mg All
A
500.
Tail
["+" ir_id_ _ymbol_ iadieal_
-13
low_e surfae_ pre_ute_]
y = 63,00 in
1
i
I
i
l
i
-13 -11 y = 58,_.Ln -7
-
Cp.S -3j
-13 -11 y = 4.9.56 in.
.g
Cp -7 -5 -3 -11 i
i
L
i
i ,_ ._o .75 l.UO
¢_= 13 °. Figure
33 (concluded).--Effect
for the
NASA
TM-107419
model
in the
cruise
of Ice #2 on the configuration.
39
wing
pressure
distribution
[] A
495. All 5O0. Tail
["+" ir_id_ r/mbol_
-13
indic_t_
lower surfAc_ pr_]
[
-11 y = _0,56 in_
-9 -7
r
Cp.5 .3 Im_mm fill
l
,
-13 -11 • y --37.4A in.
Cp.5 -1 _ t
A u
-13 • -11 • y = 28,29 ia.
..
-7.
t _-r_.o
i
-
|
|
|
.......A--.--J
-13 x/c,
-11 -9
y = 16.08 in.
Cp -7 -5 .3' -1 llulmg41..ImIBa
1' _0 q
x_ w
_
_c_
I
x/c_
¢_= 15",
Figure 34.--Effect of Ice #2 on the wing pressure distribution for the model in the cruise configuration.
NASA
TM-107419
40
[]
@5.
All
500.
Tml
F+" L-mid__mbo_
-13
mdir._
low_ sm'fa_ !m_mmm_]
-11 y= 63.00_
-9 -7
-3
-13 y =58._in
-13 -II y = 49.56 in.
-9
c_-7 -5 -3
1
,0 z./e_:
X/¢a a= 15°.
Figure 34 (concluded).--Effect of Ice #2 on the wing pressure distribution for the model in the cruise configuration.
NASA
TM-107419
41
Figure 35.--Wing mini-tuff run 495 condition.
NASA
TM-107419
flow visualization
for all wing ice #2, cruise configuration,
42
a=4 °,
Figure 36.roWing mini-tuff flow visualization run 495 condition.
NASA TM-107419
for all wing ice #2, cruise
43
configuration,
o_=10°,
Figure 37.--Wing mini-tuft run 495 condition.
NASA TM-107419
flow visualization
for all wing ice #2, cruise
44
configuration,
o_=14 °,
Figure 38.--Wing mini-tuft run 486 condition.
NASA TM-107419
flow visualization
for outboard
45
ice #2, cruise configuration,
(z =4 °,
Figure 39.BWing mini-tuft flow visualization run 486 condition.
NASA
TM-107419
for outboard
46
ice #2, cruise configuration,
o_=10 °,
Figure 40.--Wing mini-tuff run 486 condition.
NASA TM-107419
flow visualization
for outboard
47
ice #2, cruise
configuration,
o_=14°,
Figure 41 .--Wing mini-tuff run 516 condition.
NASA TM-107419
flow visualization
for inboard
48
ice #2, cruise
configuration,
(z =4 °,
Figure 42.--Wing mini-tuft run 516 condition.
NASA TM-107419
flow visualization
for inboard
49
ice #2, cruise configuration,
(z =10 °,
Figure 43.nWing mini-tuft run 516 condition.
NASA TM-107419
flow visualization
for inboard ice #2, cruise configuration,
50
o_=14 °,
Figure 44.--Wing condition.
NASA
TM-107419
mini-tuft
flow visualization
for no ice,cruise
51
configuration,
(_ =4 °, run 500
Figure 45.--Wing condition.
NASA
TM-107419
mini-tuft flow visualization
for no ice, cruise configuration,
52
e_=10 °, run 500
Figure 46.--Wing condition.
NASA TM-107419
mini-tuff
flow visualization
for no ice, cruise configuration,
53
(z =14 °, run 500
.2 .l
-,1
C m
-.2 R_n _x,,, __"_>_t>
I_iag
o
299. V_'lical Tadl
_ O a
280. 263. 197.
-,4
_
-.5
ID
Tail All Clean
-.6 3.0 2.5 2.0
r
1.5 CL l.O .5 0
-°_:
D
q
o_ d_
CD
Figure 47.--Effects of Ice #1 on longitudinal of the model in the 6--40 ° configuration.
NASA
TM-107419
54
aerodynamic
characteristics
Rum
Icing
o
_9.
[]
280.
VetticaITail
C,
263.
All
:,
197.
Clean
Tail
.06
.03
C-1
0
-.03
-.06
.06
.03
c,,
0
-.06
A
.2
cy
0
-,2
-,4,
-
i
i
i
i
i
i
z
i
i
I
I
I
i
i
l.ml
I
i._l
i
iz
)
a, aeg #=-5o Figure 48,--Effects characteristics
NASA
TM-
107419
of Ice #1 and sideslip on the lateral of the model in the 5f=40 ° configuration,
55
aerodynamic
Run
Icing
0
263.
All
[]
197.
Clean
-13 -ll -9
y .-. 40,56 in
Cp -7 -5 -3 -1
11 -13 -11 y = 37,44 in
-9
Cp -7 -5
.3 _ 1 -13 -ll y = 28.20i-
-9 -7
Cp._ -3 -11
11 -13 .c/c a
-11 -9
y = 16.08in
Cp -7 -5 -3 .1| 1
x/cw
z/_ g=6 ° ,0=-5 °.
x/c_
x/c_
Figure 49.--Effect of Ice #1 on the wing pressure distributions for the model in the 6=40 ° configuration.
NASA
TM-107419
56
Ran ©
263.
[]
197,
Clcm,
_mbol8
indicates
["+" inside
-13
I_ All
lower
sttrfaee
preasures]
-11 -9
y = 63,00
in
q-7 -5 -3 -1
-13
y = 58,9_ in
-13 -11 -9
y = 49,56
]n.
-7
Cp._ -3 -1 1
Figure 49 (concluded).--Effect of Ice #1 on the wing pressure for the model in the 6=40 ° configuration.
NASA
TM-107419
57
distributions
Run
Icing
0
263.
All
[]
197.
Clean
-13
7
-11 -9
y =,_.56
in.
y = 37A4
in.
y = 28.20
Ln.
.7
Cp.5 -3 -1 1 -13 -11 -9 .7
Cp.5
-13 -11 .9 -7
Cp.5 -3q ol _
11 -13 x/c# -If -9
y = 16.08 in
cp -? -5 -3 .[ L
x/c w
x/c_
x,'c_
_c_
a= io_ p= -_o. Figure 50.--Effect of Ice #1 on the wing pressure distributions for the model in the _=40 ° configuration.
NASA
TM-107419
58
Ran
-13
Icing
O
263,
All
E]
197.
Clcm
F'+" Lrmidesymbols
badica_es lowar suthee
pre_glrm]
-11 -9
y = 63.00 in.
-7
-3
-13 -II -9
y = 58.92in
Cp -7 -5
1
x/eme
x/c_
Figure 50 (concluded).--Effect of Ice #1 on the wing pressure distributions for the model in the 6=40 ° configuration.
NASA
TM-107419
59
Run O
263.
_x
299.
["+"
-L3
imide
_mboli
I_ All Ver_irad
iadicaaee
Tail
Lower 8ttrf_ee
pressurm]
-LI _
-9
y = 4,0.56 in.
Cp -7 -5 -3
F
-1 !
_
_dNMi,O¢" I
-L3 -11
y = 37,4_ in.
"°i -7 CP.5
"
_P .l
!e_o,ao,o_b
-13
•
-ll
• y--
28,_0
in.
-7
0 -13 x/_s -11 .9
y : 16.08 in.
-7
-3q -1 1
x/c w
x/e# a= ]3° p= -5°.
Figure 51 .--Effect of Ice #1 on the wing pressure distributions for the model in the c5f=40° configuration.
NASA TM-107419
60
Run 0
Icing
263.
All
299.
V_tical
Tail
F'+" ir_ide eymbol_ tudicmes lower surface pressures]
-13 -11 -
y= 63,00 in. Cp "7-5
-13. -11 ,y=58._in .7
cp .s[
-13 -11 y = 49,56 in-
-9 -7
CP.S -3 -1 1 0
x/c a
I
2
]
,4
3
Ib
7
81
x.,/cw a=
13"
9
ll_
x/_#=-5 o.
x/e.f
x/c#
Figure 51 (concluded).--Effect of Ice #1 on the wing pressure distributions for the model in the 8f=40° configuration.
NASA
TM-107419
61
©
263.
ALl
_
299.
VerticalTRil
F'+" ir_ide symbols imiicmtes1_
-13
s_'f_
l_=s_]
-I1 .g .7
CP.S -3 .11 1: -13 -1| y : 37,44 im -7
Cp.5 -3 -1 1 -13 -ll y = 2E_Oin.
-9 -7 CP.5 -3
-13 x/'¢_ -II y:
-9
q,
16.08 _-
.7
l
3
A
5
6
7
B
910
.....
a= 15° #= _5o. Figure 52.--Effect of Ice #1 on the wing pressure in the 8,=40 ° configuration.
NASA
TM-107419
62
distributions
for the model
Ran O
]¢_.g
263.
All
299.
-13 -
Vc_i_ITa_
F_+'' _micl_ symbols
indi_s
low_
su__ce
_s]
-1! y = 63.00 in.
o1'
I' -13, -11. .9 _
Y = 5g.92 in
Cp -7 .s[
1 -I_ -ll -9
y = 49.56i_.
Cp -7 -5 -3 .1 1
_ _ 3 A _ :o _ ._1.o
......
o._._o:,_._o
r,/_
z/e_
x/% a= 15°
x/c_
/_ =-5 °.
Figure 52 (concluded).--Effect of Ice #1 on the wing pressure distributions for the model in the &=40 ° configuration.
NASA
TM-107419
63
Figure 53.--Wing condition.
mini-tuff
flow visualization
for outboard
ice #1,5f=40
Figure 54.--Wing condition.
mini-tuff
flow visualization
for outboard
ice #1, _f=40 °, (z =10 °, 13=-5 °, run 263
NASA TM-107419
64
°, (z=4 °, 13=-5°, run 263
Figure 55.--Wing condition.
Figure 56.--Wing
NASA TM-107419
mini-tuft flow visualization
mini-tuff flow visualization
for outboard ice #1,5f=40
°, ¢z=14 °, _ =-5 °, run 263
for no ice, _f--40 °, e_=4 °, _ =-5 °, run 280 condition.
65
Figure
57.--Wing
mini-tuff
Figure
58.--Wing
mini-tuft flow visualization
NASA TM-107419
flow visualization
for no ice, 8f--40 °, cc =10 °, 13=-5 °, run 280 condition.
for no ice, 8f--40 °, ¢x =14 °, 13=-5 °, run 280 condition.
66
.2 ,1
-.1 _L -,2 _1_ C
m
-.3
Rum
'_
3_9. V_-tiealTail 339. Tail 334. All 355, (_aa
o [] ¢> ix
-,4 -.5
Izh_g
-.6 3,0 2.5 2.0 1.5 CL
._
¢
,,"_
/
P 1.0
,41
[g
"
-,,,
J .5 0 -.5
CD
de_
Figure 59.--Effects of Ice #1 on longitudinal aerodynamic characteristics of the model in the (_=30° configuration.
NASA TM-107419
67
.06
Run
IcL_
o
349.
Vortical Tail
[]
339.
Tail
334.
All
355.
Clean
l i
.03 _
l
-,03
-,06
.03
t
o -.03 -,06
.4
.2
Cy
0
-,2
-.4
I l I J
Figure
60.--Effects
characteristics
NASA
TM-107419
of Ice #1 and characteristics
sideslip
on the lateral
of the model
68
aerodynamic
in the &=30 ° configuration.
Run ©
334.
All
[]
355.
Clean
F'+" imid_ _/mbols
-13 -
]c_.g
indic_tm
lower sttrface pressures]
-ii y = 40,56 i_
.9_
Cp "7-5 -3
! .11
l
-13 -11 _y = 37.44 m. -7
-1 1 -13, y = 28._0in-
Cp -7
1
_cs
-13 - I1 -9
y = 16,08 in.
Cp -7 .5 -3 .1
x/c_
z/e_
z/e M
x/c_
of=6 _.
Figure 61 .--Effect of Ice #1 on the wing pressure distributions for the model in the 6=30 ° configuration.
NASA
TM-107419
69
©
["+" inaido
-13
Ran
l_tag
334,
All
aymbola
italic.rote8
lowez
aurface
preasttrea]
-II y = 63.00
-g
in
.7
%.2 -3 .1 r
I
I
r-
I
I
I
I
I
I
-13
'-;f
y= 58.92 _"
-13 -11 -9 -
Y = 4g.56
in.
Cp "7" .5 -3-
:i -_-'- .'_-._ .?_:.,._.7._._,.o x/c_
x/c_
r./e_
.2_ ._u .w ].uO z/e_
0 x/cat
CX=6 °.
Figure 61 (concluded).--Effect of Ice #1 on the wing pressure for the model in the _=30 ° configuration.
NASA
TM-107419
70
distribution
Ru.n
-13
Icing
O
334.
All
[]
355.
CI_an
r'+" i_mid_ _mbols
imdic_cs
ow= surfac_ pr_sures]
-II y = 40•56i_
-9
Cp -7 -5
-13 -II y = 37•44 in.
-g -7
i i
__---_
1 -13 -II y = _B•20 in.
-9 -7
Cp._ "3 I
_p
-1
-13 x/¢ s
-11 -9
y = 16.08 in.
Cp "7 .5 -3 .1 I
1
" .V::5 I-._ ._ ._ ._
_'.o
xk w a=
10%
Figure 62.--Effect of Ice #1 on the wing pressure distribution for the model in the (3f=30° configuration•
NASA
TM-107419
71
R_
-13
I_
0
334.
All
[]
35!
Clelm
F'+" i_i_
_mbol8
bt_o__t_
low_
s_cc
_m,Ltm]
-ll y = 63.00 in.
-9 _-7 .5 -) -II lq -13-II-
y = 58.9'2 in
°9Cp "7" .5
.3. II_C., -13-Ii.g.
y = 49,56_n_
-5 -3 .ti_ile,_i _ '
.r,/(: s S= l(r. Figure
62 (concluded).--Effect
for the
NASA
TM-107419
model
in the
of Ice #1 on the
&=30 ° configuration.
72
wing
pressure
distribution
Run ©
334.
All
[]
355.
Clean
F'-v" L,_id_ _mboLs
-13
Icing
ixKli_a_s lower su_fa_
lacc_au_s]
-11 ), = ¢0.56 in.
-9
Cp -7 -5 -I
_
-u
-I3
P -5_
"I
-
-13 -11 y = 7.8,_0 in.
-9 -7
CP.S .3 I .l'
222
t ._..o x/c
"13l" y = 16,08 in.
C
-7 P -SL
U
.1
.2
.3
A
.5
.0
.7
.8
,_
1.0
,
x/c_ a -- 13".
Figure 63.--Effect of Ice #1 on the wing pressure distribution for the model in the 6=30 ° configuration.
NASA
TM-107419
73
Ran 0
334,
[]
355.
["+" ir_ide symbols
-13
[ciz_
CleJm
indiPJle8 lower s,,J.rfaccpresma'ee]
-11 .9
y = 63.00in.
-7
-3 _
-I
-13
m
I I
-[3 -11 .9
Cp -7 -5 -3 .11
Figure 63 (concluded).--Effect of Ice #1 on the wing pressure distribution for the model in the (_=30° configuration.
NASA
TM-
1074 i 9
74
Figure
NASA
64.--Wing
TM-107419
mini-tuff
flow visualization
for outboard
75
ice #1, 5f=30 °, (_=4°, run 334 condition.
Figure 65.--Wing condition.
NASA TM-107419
mini-tuft flow visualization for outboard
76
ice #1,5f=30
°, c_=10 °, run 334
Figure 66.--Wing condition.
NASA TM-107419
mini-tuft flow visualization
for outboard ice #1,5f=30
77
°, _ =14 °, run 334
Figure
67.--Wing
NASA TM-107419
mini-tuft flow visualization
for no ice, 8f=30 °, _ =4 °, run 349 condition.
78
Figure 68.--Wing
NASA TM-107419
mini-tuff
flow visualization
for no ice, 6f=30 °, _ =10 °, run 349 condition.
79
Figure
69.--Wing
NASA TM-107419
mini-tuft
flow visualization
for no ice, _f=30 °, _ =14 °, run 349 condition.
80
'3
.1
0
C m Rilll
\
-,3
-.4
-.5
o []
450. 459. 464.
Veaieai Tail Tail All
a t_
481. 431.
Inboard Wing CI_a
-.6
3,0 2.5 2.0 1,5 CL 1.0
,5 k
0
CD
deg
Figure 70.--Effects of Ice #1 on longitudinal of the model in the cruise configuration.
NASA
TM-107419
81
aerodynamic
characteristics
o
450.
Vertical Tail
r_
459.
Tail