Ice Accretion Test Results for Three Large-Scale Swept-Wing Models in the NASA Icing Research Tunnel

Document

www.nasa.gov

June 13-17, 2016

Washington, D.C.

Sam Lee

Brian Woodard

Vantage Partners, LLC

Boeing Commercial Airplanes

NASA Glenn Research Center

Adam Malone and Ben Paul

Andy Broeren and Mark Potapczuk

University of Illinois at Urbana-Champaign

NASA Icing Research Tunnel

ASE Conference

Ice-Accretion Test Results for Three-

Large-Scale Swept-Wing Models in the

AIAA 8

National Aeronautics and Space Administration www.nasa.gov

Outline

Introduction Objective and Approach Hybrid Model Design Experimental Methodology Aerodynamic Calibration Results Ice Accretion Results Summary Acknowledgements

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Introduction

Development and use of 3D icing simulation tools. Lack of ice accretion and aerodynamic data for large- scale, swept wing geometries. Aerodynamic understanding important for evaluating efficacy of 3D icing simulation tools. Multi-faceted research effort called SUNSET II.

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Objective and Approach

Generate a database of ice-accretion geometry for large-scale, swept wings. Select baseline large-scale, swept-wing geometry. Identify three spanwise stations of interest—Inboard, Midspan and Outboard. Design hybrid or truncated wing-section models for IRT test section. Conduct ice-accretion testing in IRT. Measure ice geometry with 3D scanning technique.

Objective • Approach • • • • •

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Common Research Model (CRM)

Commercial transport class configuration. Contemporary transonic supercritical wing design. Publically available and otherwise unrestricted for world-wide distribution. A 65% scale CRM was selected as the full-scale, reference swept-wing geometry for this research. CRM65 size airplane is comparable to Boeing 757.

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Scale Factor = 1.5

Select wing stations for hybrid model design

Outboard, 83% Semispan

Scale Factor = 2

Midspan, 64% Semispan

Iced Flight Baseline (IFB) LEWICE3D

Hybrid Model Design

Design hybrid models to generate full-scale ice accretion.

Clean Flight Baseline (CFB) OVERFLOW

Scale Factor = 2.25

• Inboard, 20% Semispan

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Outboard Model

Midspan Model

Experimental Methodology

Ice-accretion testing was conducted at NASA Icing Research Tunnel (IRT) that simulates flight through an icing cloud at pressure-altitudes near sea level. IRT test section is 6 ft high by 9 ft wide by 20 ft long. Models were installed vertically from floor-to-ceiling with small gaps to provide clearance for angle of attack and flap angle changes.

Inboard Model

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2.0 1.5

2.25 Factor

Model Scale

6.3 6.2

13.5 Chord

Length (ft)

Experimental Methodology

Streamwise

18, 36 and 54 inches above the test-section floor. Pressure instrumentation Icing

− − −

Streamwise pressure taps located at three spanwise stations Single-element, slotted flap with anti- icing heater. Two removable leading edges

Model

Section Inboard

Midspan

Outboard

Models Description • • •

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1.06 1.42 0.36

Model

Outboard

1.66 1.91 0.57

Model

Midspan

4.72 5.28 2.85

Model

Inboard

Streamwise Wrap Distance—Inches From Hilite

3.7 4.4 2.1

AoA deg.

Aerodynamic Calibration Results

Case

Flight

WB33 WB41 WB52

An aerodynamic calibration of the hybrid models was performed in order to match the attachment point location on the IRT models to the corresponding location on the CRM65, full-scale reference airplane. The model incidence and flap angles were systematically varied to track the attachment line location at the 36-inch model centerline station. The attachment line location was defined as the location of the maximum pressure coefficient.

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National Aeronautics and Space Administration www.nasa.gov Flap = 0 Flap = 5 Flap = 10 Flap = 15 WB52 WB33 WB41 7.0 6.0 5.0 4.0 (deg.)

 3.0 2.0 1.0

Aerodynamic Calibration Results

0.0 0.5 1.0 1.5 2.0 2.5 3.0 3.5 4.0 4.5 5.0 5.5 6.0 6.5 Streamwise Wrap Distance From Hilite, s (in.)

Aerodynamic calibration for Inboard Model.

•

National Aeronautics and Space Administration www.nasa.gov = 3.7 deg., Flap = 13.7 deg.

 (in.)

s 10.0 11.0 12.0 13.0 9.0 8.0 Experimental Data, CRM65 Airplane CFD Simulation WB33 Attachment Point Location (Original) WB33 Attachment Point Location (Updated) 7.0 6.0 5.0 4.0 3.0 Streamwise Wrap Distance From Hilite, 2.0 1.0

Aerodynamic Calibration Results

0.0 0.0 0.2 0.4 0.6 0.8 1.0 -1.0 -0.8 -0.6 -0.4 -0.2 p Surface pressure data near attachment point for Inboard Model.

C

•

National Aeronautics and Space Administration www.nasa.gov = 18 in. = 36 in. = 54 in.

y y y

n.)

i

(

x

-20 -40 -60

Aerodynamic Calibration Results

-80 0.0 0.5 1.0 -4.0 -3.5 -3.0 -2.5 -2.0 -1.5 -1.0 -0.5 p

C

Surface pressure data for Inboard Model.

•

National Aeronautics and Space Administration 45 45 min.

www.nasa.gov Exp. Time 0.36 g/m 0.51 LWC 0.17 to 0.55 m 20 20 20 μ MVD -13.0 deg. C Static Temp -10.0 to -3.0 -4.1 deg. C -6.0 to 1.1 Total Temp -18.4 to 1.1 -25.0 to -6.0 230 220 260 TAS Knots

Ice Accretion Results

(ft) 5,000 5,000 10,000 Altitude Conditions were scaled to IRT test speed (130 knots for most cases). Effects of velocity scaling were investigated for Midspan and Outboard models.

3.7 4.4 2.1 AoA deg.

− −

Generate range of ice accretion. Hold and descent for CRM65 airplane in App. C. Large range of temperatures, limited variations in MVD and LWC. Large model size limited maximum speed in IRT.

Icing Test Matrix Development • • • • Baseline Flight Reference Conditions Case

WB33 WB41 WB52 National Aeronautics and Space Administration www.nasa.gov

Ice Accretion Results

Ice accretion was documented with photographs and 3D scans. 3D scan data were post-processed to provide the Maximum Combined Cross Section (MCCS).

• •

National Aeronautics and Space Administration min.

www.nasa.gov Exp. Time 1.0 g/m LWC m μ MVD -8.5 deg. C Static Temp -6.3 deg. C Total Temp

Ice Accretion Results

TAS Knots 3.7 AoA deg.

Run TG2450

Time lapse video—Midspan Model

National Aeronautics and Space Administration 29 29 29 min.

www.nasa.gov Exp. Time 1.0 1.0 1.0 g/m LWC

Total Temp = -23.8 deg. C

m 25 25 25 μ MVD -6.0 -11.0 -25.0 deg. C Static Temp

Total Temp = -8.7 deg. C

-3.8 -8.7 -23.8 deg. C Total Temp 130 130 130 TAS Knots

Ice Accretion Results

3.7 3.7 3.7 AoA deg.

Run TG2421 TG2402 TG2415

Total Temp = -3.8 deg. C

Inboard Model—Effect of Temperature

National Aeronautics and Space Administration C C C    0.06 min.

www.nasa.gov 0.04 = -11.2 = -15.0 = -23.8 0 0 0 Exp. Time T T T FS 0.02 x/c 0.00 1.0 g/m LWC -0.02 0.00 0.02 0.04 FS -0.04 -0.02 z/c m μ C  MVD C C 0.06   0.04 = -6.3 = -8.7 = -11.2 0 0 0 T T T FS 0.02 x/c deg. C Static Temp -3.6 to -25.0 0.00 -0.02 0.00 0.02 0.04 FS -0.04 -0.02 z/c deg. C Total Temp C C C -1.4 to -23.8    0.06 = -1.4 = -3.8 = -6.3 0.04 0 0 0 130 T T T TAS Knots

Ice Accretion Results

FS 0.02 x/c 3.7 AoA deg.

0.00 - -0.02 Run 0.00 0.02 0.04 FS -0.04 -0.02 z/c

Inboard Model—Effect of Temperature

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C

˚

29 29 29 min.

www.nasa.gov Exp. Time

Outboard

1.0 1.0 1.0 g/m LWC m 25 25 25 μ MVD

Midspan

-6.0 -6.0 -6.0 deg. C Static Temp -3.8 -3.8 -3.8 deg. C Total Temp

Ice Accretion Results

130 130 130 TAS Knots

Inboard

3.7 3.7 3.7 AoA deg.

Run TI2462 TG2421 TH2438

Identical Condition Run on Each Model—Total Temperature = -3.8

National Aeronautics and Space Administration 0.08

C

˚

29 29 29 min.

www.nasa.gov 0.04 Exp. Time FS x/c 0.00

Outboard

1.0 1.0 1.0 g/m LWC -0.04 0.00 0.02 0.04 0.06 0.08 FS -0.06 -0.04 -0.02 z/c m 25 25 25 μ MVD 0.08 0.04 FS x/c -8.5 -8.5 -8.5 deg. C

Midspan

0.00 Static Temp -0.04 0.00 0.02 0.04 0.06 FS -0.06 -0.04 -0.02 z/c -3.8 -3.8 -3.8 deg. C Total Temp 0.06

Ice Accretion Results

0.04 130 130 130 TAS Knots FS 0.02 x/c 3.7 3.7 3.7 AoA deg.

Inboard

0.00 -0.02 Run 0.00 0.02 0.04 FS TI2462 -0.04 -0.02 TG2421 TH2438 z/c

Identical Condition Run on Each Model—Total Temperature = -3.8

National Aeronautics and Space Administration

C

˚

29 29 29 min.

www.nasa.gov Exp. Time 1.0 1.0 1.0 g/m LWC

Outboard

m 25 25 25 μ MVD -8.5 -8.5 -8.5 deg. C Static Temp

Midspan

-6.3 -6.3 -6.3 deg. C Total Temp

Ice Accretion Results

130 130 130 TAS Knots 3.7 3.7 3.7 AoA deg.

Inboard

Run TI2479 TG2411 TH2452

Identical Condition Run on Each Model—Total Temperature = -6.3

National Aeronautics and Space Administration 0.08

C

˚

29 29 29 min.

www.nasa.gov 0.04 Exp. Time FS x/c 0.00

Outboard

1.0 1.0 1.0 g/m LWC -0.04 0.00 0.02 0.04 0.06 0.08 FS -0.06 -0.04 -0.02 z/c m 25 25 25 μ 0.08 MVD 0.04 FS x/c -8.5 -8.5 -8.5 deg. C 0.00

Midspan

Static Temp -0.04 0.00 0.02 0.04 0.06 FS -0.06 -0.04 -0.02 z/c -6.3 -6.3 -6.3 deg. C Total Temp 0.06

Ice Accretion Results

0.04 130 130 130 TAS Knots FS 0.02 x/c 3.7 3.7 3.7 AoA deg.

Inboard

0.00 -0.02 Run 0.00 0.02 0.04 FS -0.04 -0.02 TI2479 z/c TG2411 TH2452

Identical Condition Run on Each Model—Total Temperature = -6.3

National Aeronautics and Space Administration 29 45 min.

www.nasa.gov Exp. Time

TH2514

1.0 0.91 g/m LWC m 25 27 μ MVD

TH2452

-8.5 -5.3 deg. C Static Temp -6.3 -3.1 deg. C Total Temp 0.08 TH2452 TH2514

Ice Accretion Results

130 130 TAS 0.04 Knots FS x/c 3.7 3.7 0.00 AoA deg.

-0.04 Run 0.00 0.02 0.04 0.06 FS TH2452 TH2514 -0.06 -0.04 -0.02 z/c

Maximum Scallop vs. App. C Scaled Conditions on Midspan Model

National Aeronautics and Space Administration 32 32 min.

www.nasa.gov Exp. Time

TH2444

0.91 0.65 LWC g/m m 27 24 μ MVD

TH2445

-5.3 -6.0 deg. C Static Temp -3.1 -2.0 deg. C Total Temp 0.08

Ice Accretion Results

TH2445 TH2544 130 180 TAS Knots 0.04 FS x/c 3.7 3.7 AoA deg.

0.00 -0.04 Run TH2445 TH2444 0.00 0.02 0.04 0.06 FS -0.06 -0.04 -0.02 z/c

Effect of Velocity on Ice Accretion on Midspan Model

National Aeronautics and Space Administration min.

www.nasa.gov 25.3 Exp. Time

TI2494

0.60 0.30 LWC g/m m 25 20 μ MVD

TI2465

-20.1 -18.3 deg. C Static Temp -11.2 -17.9 deg. C 0.08 Total Temp TI2465 TI2494

Ice Accretion Results

0.04 130 232 TAS FS Knots x/c 0.00 3.7 3.7 AoA deg.

-0.04 0.00 0.02 0.04 0.06 Run FS -0.06 -0.04 -0.02 z/c TI2465 TI2494

Effect of Velocity on Ice Accretion on Outboard Model

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Summary

A large database of ice accretion geometry was generated for three sections of the CRM65 large-scale, swept wing. Hybrid models with full-scale leading-edges were used to obtain full- scale ice accretion at the Inboard (20%), Midspan (64%) and Outboard (83%) stations. The ice accretion database consists of the 3D ice accretion geometry along with surface pressure measurements on the clean hybrid models at corresponding aerodynamic conditions. For most cases, each model was subjected to identical icing conditions which limited the speed to 130 knots because of the large size of the Inboard model. The Appendix C-based icing conditions were scaled from flight reference values to account for the difference in velocity. A limited number of higher-velocity cases were run on the Midspan and Outboard models—results were limited by ice shedding.

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National Aeronautics and Space Administration www.nasa.gov :

Acknowledgements

NASA—Advanced Air Transport Technology Project FAA ONERA Boeing University of Illinois University of Virginia University of Washington

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