design lab present a ion
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A Amith Reddy (AE09B032) Ch Deepak (AE09b034) S Hari Prasad (AE09B036) Jackson Joseph (AE09b037) Yogesh Jethani (AE09B038)
GROUP 6 :
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MISSION AND FIRST WEIGHT ESTIMATE
MISSION Design a strategic bomber conceptually.
PRIMARY DESIGN CRITERIA Important parameters :
Range (8000 Kms β 10000 Kms) Service ceiling (8000 m) Maximum speed (1000 kms)
FIRST WEIGHT ESTIMATE Approach : First weight estimate based on historical data
ππ = πππππ€ + ππππ¦ππππ
+ πππ’ππ + πππππ‘π¦
ππ = πππππ€ + ππππ¦ππππ + (ππ/ππ)ππ + (ππ/ππ)ππ
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Graphs plotted from historical data
a) ππ/ππ π£π ππ b) ππ/ππ
π£π ππ c) π ππππ π£π ππ d) ππππ£πππ πππππππ π£π ππ e) πππ₯πππ’π πππππ π£π π0
Analytical optimization process gives π0. Using above π0 and graphs βaβ and βbβ we can get ππ and ππ . Calculated values :
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MISSION PROFILE AND SECOND WEIGHT ESTIMATE
MISSION PROFILE
(30 mins)
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Weight loss due to bomb dropping is excluded, because bombs should be carried back if not used.
EMPTY WEIGHT FRACTION β’ Empty weight fraction can be estimated Using curve fit
equation given below
β’ πΎπ
πΎπ= π¨πΎπ
π π²ππ --------------(1)
β’ Kvs is variable sweep constant which in this case is 1 as we didnβt opt for any variable sweep.
β’ For a bomber aircraft ,A and C values are 0.93 and - 0.07 respectively.
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FUEL FRACTION ESTIMATION
ENGINE SPECIFICATIONS : Since the aircraft is subsonic high bypass turbofan is selected for its high efficiency in this velocity range.
Specific fuel consumption : Cruise:0.5 Loiter:0.4
TAKEOFF, CLIMB AND LANDING : Weight fractions of Takeoff, climb and landing are independent of the type of aircraft Historical mission segment weight fractions:
Warm up and takeoff 0.970
Climb 0.985
Landing 0.995
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CRUISE : The cruise mission segment can be found out from the range equation which is
ππ
ππβ1= exp β
π πΆ
π(πΏ
π·)
LOITER : The loitering weight ratios are found out using the
endurance equation
ππ
ππβ1= exp β
πΈπΆ
(πΏ
π·)
From historical data wetted aspect ratio is 1.2, with wetted aspect ratio (L/D)max=15.4 and (L/D) = 0.866*(L/D)max . CRUISE SPEED : Cruise speed is found using historical data Plotted graphs from historical data
a. cruise speed vs. range b. cruise speed vs. service ceiling c. cruise speed vs. total take-off weight
with optimization similar to the previous one, cruise speed is found to be about 600 kmph.
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SECOND WEIGHT ESTIMATE
Using calculated values for (L/D)max and C, we get π3
π2 and
π4
π3 .
Taking the aircraft weight at the end as W6, we have
π6
π0=
π6
π4
π4
π3
π3
π2
π2
π1
π1
π0 and
ππ
π0= 1.06 β 1 β
π6
π0 .
Now iteration is performed using the relation π0 =πππππ€+ππππ¦ππππ
1β ππ
π0 β
πππ0
and equation ππ/π0 = 0.93π0
β 0.07 From the iterative processes
πΎπππππ 37200
πΎπ(second estimate) 88880