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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



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