Las Vegas, July 2006
Fluid Qualification Testing
Arlene Beisswenger
Las Vegas, July 2006
1
De / Anti-icing Fluids
Type I
Type II
Type III
Type IV
Main use:
De-ice
Anti-ice
Anti-ice
Anti-ice
Behavior:
Newtonian
Non-Newtonian
Non-Newtonian
Non-Newtonian
Specification:
AMS1424
AMS1428
AMS1428
AMS1428
Aircraft:
Icing
Protection:
Both
Large
WSET = 3 min WSET = 30 min
Commuter
WSET = 20 min
Las Vegas, July 2006
Large
WSET = 80 min
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Fluid Qualification (AMS 1424/1428)
Performed at Ø Effect on aircraft materials
AMIL
Ø Environment
Ø Fluid Performance
ØAnti-icing Endurance
ØAerodynamic Acceptance
Ø Physical Properties
Ø Fluid Stability
Las Vegas, July 2006
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Types of Qualification
Ø Pre-production
v 1st time
v All tests
v High and low viscosity samples representing
production range (anti-icing)
Ø Periodic
v Every 2 years
(4 years now for Type I in 2nd requalification)
v Only performance tests
v Production sample
Ø Multiple location
v Fluid is produced at a different site
v Aerodynamic acceptance + 1 WSET
v Production sample
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Performance Standards
Anti-icing Endurance
WSET
HHET
→ determines the fluid type
WAS: Annex A of AMS1424 and 1428
NOW: AS5901
Aerodynamic Acceptance
FPET
→ determines (along with freeze point) the LOUT
Aerodynamic Performance:
WAS: Annex B and C of AMS1424 and 1428
NOW: AS 5900
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Performance Standards = Better Fluids
Anti-icing Endurance Time (min)
120
Type I
100
Type II
80
Type IV
60
IV
40
II
II
20
MIL
I
I
0
In the
beginning
1993
AMS1424
AMS1428
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1996
AMS1424A
AMS1428A
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Performance Standards = Better Fluids
TYPE IV
High speed ramp tests
100
90
PERCENTAGE OF ELIMINATION (%)
80
70
60
74 % elimination requirement
50
1995
1996
1997
1999
2000
2001
2002
40
30
20
10
0
-35
-30
-25
-20
-15
-10
-5
0
5
FLUID TEMPERATURE (°C)
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Anti-icing Endurance Performance
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Water Spray Endurance Test
WSET:
• usually first test performed
• simulates a freezing fog condition
Procedure :
• (dilution with hardwater)
• shearing
• evaluation in cold chamber
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WSET – dilution with hard water
Hard water:
ü 1 L ASTM D1193 Type IV (demineralized) water
ü 400 mg ± 5 Ca(C2H3O2)2.2H2O
ü 280 mg ± 5 MgSO4.7H2O
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WSET – shear stability
Calibration:
Type I:
7500 rpm
10 min
Type IV:
3000 rpm
5 min
Ø Test run 20 min to 2 hrs following
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WSET
Air temperature: -5ºC (23°F)
Plate temperature: -5ºC
Intensity: 5 g/dm²/h (0.5 mm/h)
Plate angle:
10º from horizontal
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WSET – fluid failure
Fluid failure =
ice front at 25mm line,
5 mm in from the sides
Requirements:
Type I = 3 min
Type II = 30 min
Type III = 20 min
Type IV = 80 min
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WSET – Chamber
OSCILLATING NOZZLE ±30°
ASTM D1193 TYPE IV WATER
COMPRESSED AIR
60°
130cm
REFRIGERATED SUPPORT
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HHET
Simulates frost
Air temperature: 0ºC
Plate temperature: -5ºC
Horizontal air velocity: 0.2 m/s
Ice catch: 0.3 g/dm²/h (0.03 mm/h)
Relative humidity: 96% Rh
Requirements:
Type I = 20 min
Type II = 4 hours
Type III = 2 hours
Type IV = 8 hours
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Aerodynamic Performance
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Aerodynamic Acceptance – before anything
For Type II and IV:
Check viscosity (0ºC at 6 and 30 rpm)
before and after shearing,
If ? by > 15% ? shear fluid before testing
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Aerodynamic Acceptance – dilution preparation
Dilutions prepared using
ASTM D1193 Type IV
(demineralized) water
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Aerodynamic Acceptance – dilution preparation
Fluid dilutions and
reference fluid
measured into
1 L bottles
Fluids are stored in
freezers at
-17°C, -27°C, (-45°C)
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Aerodynamic Acceptance – Wind Tunnel
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Aerodynamic Acceptance – FPET –pouring and leveling
Fluid poured from
1 L bottle
Fluid leveled to a 2 mm thickness
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Aerodynamic Acceptance – test section insert
P1
(P1 − P2)

δ *ave = 1 
c  (P1 − P2)+(P2 −P3) 
Convergent cone
1.5 meter
P2
( )
2

2
S
2 
V = (P1 − P2)/ 1−
 S1 
ρ
Test section
Divergent cone
Insulation
Ta
P3
Tf
P1,P2,P3 - Static pressure gauges
Ta- Air temperature thermocouple
Tf- Fluid temperature thermocouple
S2 , P2
Tunnel wall
S3 , P3
Test section:
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Aerodynamic Acceptance – BLDT
5 min @ 5 m/s
25 s acceleration from 5 m/s to 65 m/s
→ 2.5 m/s²
30 s of 65 m/s
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Aerodynamic Acceptance – FPET – video
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Aerodynamic Acceptance – Ramps
80
65 m/s ± 5
High Speed Ramp:
Large transport type jet aircraft
Take off speeds >100 knots
AIR VELOCITY (m/s)
70
60
50
40
30
25 s ± 2
20
10
0
0
10
20
40
50
60
40
50
60
TIME (s)
80
70
AIR VELOCITY (m/s)
Low Speed Ramp:
Commuter-type aircraft
With no compensating measures
Take-off speeds > 60 knots
30
60
50
35 m/s ± 3
40
30
17 s ± 1
20
10
0
0
10
20
30
TIME (s)
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Aerodynamic Acceptance – FPET – test order
Test order:
Measurements:
Dry
MIL
MIL
Dry
Fluid
Fluid
Dry
Fluid
MIL
Dry
Test run #
Air Temperature
Fluid Temperature
Relative Humidity
Speed
Fluid thickness: before and after
Sample # for RI
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Aerodynamic Acceptance – %age elimination
Fluid thickness is remeasured
following test to calculate
%age elimination
Requirement:
Type I: none
Type II and IV > 74%
Type III > 57%
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Aerodynamic Acceptance – acceptance criteria
15
14
13
12
11
Dry (without fluid)
BLDT = 2.7 mm ±0.05
5 % lift loss
BLDT (mm)
10
9
8
7
Acceptance Criteria
6
Reference Fluid
DRY
linear regression
5
4
3
2
1
0
-40 -35 -30 -25 -20 -15 -10 -5
FLUID TEMPERATURE (°C)
0
5
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Aerodynamic Acceptance – FPET – Candidate fluid
15
100/0
75/25
50/50
DRY
Acceptance Criteria
14
13
12
For fluid:
« fluid is acceptable if none
of the independent BLDT
measurements is greater
than the acceptance criteria
…the average of the three
lowest temperatures of the
acceptable data points »
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BLDT (mm)
10
9
8
7
6
5
4
3
2
1
0
-35
-30
-25 -20 -15 -10 -5
FLUID TEMPERATURE (°C)
0
5
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Fluid Characterization - Viscosity
Viscosity is measured on everything tested:
WSET: sheared and HW dilutions at 0 ºC, and 20 ºC
Aero acceptance: from 0 ºC down to lowest temp at 10 ºC intervals
All at 0.3, 6 and 30 rpm with appropriate spindle
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Fluid Characterization – Refractive Index
1.44
Of all dilutions tested
As well as water change curve
to calculate water change from
aerodynamics
1.43
REFRACTIVE INDEX
1.42
1.41
1.40
1.39
1.38
1.37
1.36
60
70
80
90
100
110
FLUID CONCENTRATION %(W/W)
M028
C861
C862
M028 : RI = 0.000801 %(w/w) + 1.348040
C861 : RI = 0.000679 %(w/w) + 1.336560
C862 : RI = 0.000533 %(w/w) + 1.332320
BASIS : 100%(w/w) corresponds to NEAT product
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Fluid Characterization – pH
For all dilutions tested
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Fluid Characterization – Surface Tension
For all dilutions tested
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Fluid Stability
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Fluid Stability
Simulating fluid dry-out:
• On leading edge
• On aircraft including
aerodynamic quiet areas
• Heated storage
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AMIL
Main Focus:
Qualification of aircraft de/anti-icing fluids
for aerodynamic acceptance and anti-icing endurance
according to AMS specifications
2nd:
Research for the aviation community on fluid related
issues
Support the SAE G-12 on fluid testing issues
3rd:
Apply our icing simulation expertise to look into icing
and new deicing techniques for other structures
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AMIL - Installations
• Two icing wind tunnels
which can simulate aircraft take-off
• Four climatic chambers where:
freezing rain, freezing drizzle,
freezing fog, frost, snow,
and ice pellets are simulated
• Fluid characterization lab: viscosity (down to –30°C),
refractive index, surface tension, freezing point, specific mass
heat capacity, water diffusion…
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Other Fluid Research
• Non-glycol fluids
• Gel residues
• Aerodynamic acceptance reference fluid replacement
• Ice pellets simulation and aerodynamic flow-off
• Snow pellet simulation
• Freezing precipitation simulation
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Other Icing Research Topics
• Icephobic coatings
• Helicopter icing and deicing
• Over head cable icing and deicing
• Wind turbine icing and deicing
• Refrigeration system icing and deicing
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Q
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More Information
Consult our website at:
www.amil.chicoutimi.qc.ca
List of Qualified Fluids:
follow the ‘qualification/qualified’ links
from the AMIL home page
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