Aero Engineering 315 Lesson 28 Cruise Range and Endurance.
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Transcript of Aero Engineering 315 Lesson 28 Cruise Range and Endurance.
![Page 1: Aero Engineering 315 Lesson 28 Cruise Range and Endurance.](https://reader038.fdocuments.net/reader038/viewer/2022102713/56649d365503460f94a0df6f/html5/thumbnails/1.jpg)
Aero Engineering 315
Lesson 28
Cruise Range and Endurance
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T-38 Example
Given:W = 12,000 lbsh = Sea Level
Find: MAX
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T-38 Example
Given:W = 12,000 lbsh = Sea Level
Find: ROCMAX
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T-38 Ceiling
What happens to TA - TR as we go higher?
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Ceilings
Based on maximum climb rates
Absolute Ceiling = 0 ft/min ROC
Service Ceiling = 100 ft/min ROC
Cruise Ceiling = 300 ft/min ROC
Combat Ceiling = 500 ft/min ROC
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Cruise performance overview
Thrust Specific Fuel Consumption Average Value Method
Endurance Range
Breguet Equations (conceptual only) Endurance Range
Know points to fly for max range and endurance
Find velocities for max range and endurance from T-38 charts or drag polar
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Speaking of Range and Endurance…
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0
1
2
3
4
5
6
7
8
9
10
0 1 2 3 4
Flight Mach Number
Thru
st S
peci
fic F
uel C
onsu
mpt
ion,
1/h
r
Rocket
Ramjet
Afterburning Turbofan
AfterburningTurbojet
Turbojet
Low-Bypass-Ratio Turbofan
High-Bypass-Ratio Turbofan
Turboprop
Piston Engine / Propeller
TSFC = Fuel use rate in lb/hr
Thrust output in lb
TSFC = ct = Wf
T
•
Thrust Specific Fuel Consumption
Adjust for altitude
or
SL
ALT
SL tALT t T
T c= c
ct ALT = ct SL (aALT /aSL)
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TSFC - Typical Values
Engine type TSFC (1/hr)
Recip Prop 0.25 to 0.60Turboprop 0.35 to 0.60Turbofan 0.35 to 0.60 (high bypass)
0.39 to 0.70 (medium bypass) 0.80 to 1.00 (low bypass)
Turbojet 1.00 to 1.30 1.80 to 2.50 (with afterburner)
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Low and High Bypass
FanBurner
High-PressureCompressor
High-Pressure Turbine
Low-Pressure Turbine
Afterburner
NozzleLow-Pressure Compressor
Bypass Duct
Fan
Burner
CompressorHigh-Pressure Turbine
Low-Pressure Turbine
Nozzle
Low Bypass Ratio with Afterburner High Bypass Ratio Bypass Ratio = 0.2 - 1.0 Bypass Ratio = 2.0 - 8.0TSFCDry = 0.8 - 1.3 TSFC = 0.5 - 0.7TSFCWET = 2.2 - 2.7
BPR = Mf / Mc
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T-38 Powerplant
Ratings (see Note 1)Power Setting Normal Military Maximum
Power Power PowerAugmentation None None
AfterburnerEngine Speed (Note 2) 96.4 100 100Thrust per engine - lb
No losses 2140 2455 3660Installed 1770 1935 2840
Specific fuel consumption (Note 3)Installed 1.09 1.14 2.64
Notes(1) Sea level static ICAO standard conditions with a fuel specificweight of 6.5 lb/gal.(2) Units are % RPM where 100% = 16,500 RPM.(3) Units are lb/hr per lb thrust.
Supplemental Data
17.3% loss
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Endurance—Average Value Method
How long will an airplane fly?
Endurance = Total fuel used in lb
Fuel use rate in lb/hr
E =Wf
• Wf
ct TR
Wf=
ct D
Wf= for SLUF
ct Davg
WfE =
But weight changes cause drag changes, so use the average drag over the segment
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Using our average endurance equation:
Maximum Endurance
ct Davg
WfE =
To maximize endurance…
Wf and ct are constant for a
mission segment and altitude
…minimize drag
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Example:T-38
Given:W = 11,000 lbhT = 20,000 ftCt = 1.09 (sea level)Fuel burned = 2,000 lb
Find:E for M=.7EMAX
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Breguet Equations:Endurance
1
0ln
1
W
W
C
C
cE
D
L
t
where W0=initial weight and W1=final weight
Max E?
For a complete endurance solution, integrate over weight changes
E = Dc
dW
t
1
0
W
W
L/D)max
ct min
(high altitude)
Wfuel max
For our drag polar this means?
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Range—Average Value Method
Starting with Endurance
For our average situation
Max Range?
R = EV
ct Davg
Wf VavgR =
Range = Endurance x Velocity
ct (D /V ) avg
WfR =or
Minimize drag/velocity
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V
TTR
TA (DRY)
TA (WET)
Range
For a given velocity,say V1
Slope =(D/V1)
= D for (D/V1)
ct (D /V1 )
WfR =
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V
TTR
TA (DRY)
TA (WET)
Max Range
Slope= (D/V)MIN, avg
= D for (D/V)MIN, avg
= V for (D/V)MIN, avg
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Example:T-38 again
Given:W = 11,000 lbh = 20,000 ftFuel Wt = 2,000 lb
Find: RMAX
Slope tangent at Mavg = 0.63 Davg = 960
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Breguet Equations:Range
Dc
dWV
t
R = Vdt = 1
0
W
W
2/11
2/10
D
2/1L
tWW
C
C
c
1
S
22R
For a complete range solution, integrate over weight changes
where W0=initial weight and W1=final weight
Max R?
ct min & min
(High altitude)
W fuel max
)max
CL1/2
CD
Dc
VdW
t
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Maximum Range using the Drag Polar
Parasite Drag = Drag due to Lift
so: CD = CD,0 + CD,i = 4 CD,0 /3 = 4 kCL2
solving for CL:
CD,0 = 3CD,i or CD,0= 3k CL2
CL = (CD,0 /3k)1/2
3x
)max
CL1/2
CDoccurs when:
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2LDo
MaxD
L
kCC
C
C
Range and Endurance -Aerodynamic Summary
MAX ENDURANCE: MAX RANGE:
2
2/1
3 LDo
MaxD
L
kCC
C
C
Minimum ofThrust Curve
Tangent toThrust Curve
Graphical
Analytical
CL = (CD,0 /3k)1/2CL = (CD,0 /k)1/2
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Performance Summary(text p. 173)
*for typical non-afterburning turbojet aircraft
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Performance SummaryRelationship Best Case Relation between
Induced and Parasite Drag for best case
Graphical relation for best case
Max Climb Angle CDo = kCL2 - Minimum from TR curve
- Tangent point on a line from origin to PR curve
Max Climb Rate No set relation - Draw a line parallel to PA curve, and move it down till it is tangent to PR curve
Breguet (5.28) or Avg Value (5.27)
Max Jet Powered Range
CDo = 3kCL2 - Tangent point on a line
from origin to TR curve
Breguet (5.26) or Avg Value (5.24)
Max Jet Powered Endurance
CDo = kCL2 - Minimum from TR curve
- Tangent point on a line from origin to PR curve
R = h (L/D)Best Glide Range (angle)
CDo = kCL2 - Minimum from TR curve
- Tangent point on a line from origin to PR curve
Best Glide Endurance (min sink)
3CDo = kCL2 - Minimum from the PR curve
)arcsin(W
DT
W
P
W
DTVCOR x
)(...
W
P
W
VDDOR R...
Climbing
Cruise
Glides
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4 5 3 7 6 8 2 1 7 7
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Next Lesson (T29)… Prior to class
Read text 5.10 Complete problems #32, 33 and 34 Complete FDP parts a, b, c, d, e, f, i, j, k,
l, r In class
Discuss takeoffs and landings