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Flight Vehicle Design Project 2

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FLIGHT VEHICLE DESIGN PROJECT 2

Professor: Dr. Steven Lu
Written By: Joey Haripersaud

Design Specifications for a Particular Jet Transport

Payload: 304 Passengers
Crew: Two pilots and three cabin attendants
Range: 4200 nm following by ¾ hour loiter
Altitude: 35,000 ft
Cruise speed: M = 0.84 at 35,000 ft
Climb: Direct climb to 35,000 ft at maximum take-off weight WTO
Take-off and landing: FAR 25 fieldlength 9,800 ft at an altitude of 5,300 ft and 98°F day.
Landing performance at WL = 0.8WTO
Engines: Four turbofans
Certification base: FAR 25

Specification Project 1

WTO= 357,100
WF used= 106,722
WOE TENT=188,008
WE TENT=185,197
WE= 185,240

Procedure
Step 1:
The Temperature ratio (φ) has to be found so that σ can be determined. The pressure ratio (δ) is found using the atmospheric table with an altitude of 1500 ft.
T= 98 °F
Stofl: 5300 ft
Temperature Ratio (φ): (T + 459.7)/518.7 = 1.0752
Pressure ratio (σ)= δ/φ = .822/1.075=0.765

Step 2:
From observing Table 3.1 a range of values for CLmaxTO for the take-off flaps are found to be 1.6 to 2.8. In this case the values 1.6, 2.0, 2.4, 2.8 are going to be used.
Using equation 3.8: STOFL: [37.5 (W/S)TO] / [σ * (T/W)TO] which is simplified and rearranged to (T/W)TO= [ 0.014997 (W/S)TO] / CLMAXTO
Step 3:
This table was composed with the information given in step 2. T/W TABLE | | CLmaxTO | | At 5300 ft and 98 °F | At Sea Level | W/S | 1.6 | 2 | 2.4 | 2.8 | 1.6 | 2 | 2.4 | 2.8 | 60 | 0.188 | 0.150 | 0.125 | 0.107 | 0.220 | 0.176 | 0.146 | 0.125 | 80 | 0.250 | 0.200 | 0.167 | 0.143 | 0.293 | 0.234 | 0.195 | 0.167 | 100 | 0.313 | 0.250 | 0.209 | 0.179 | 0.366 | 0.293 | 0.244 | 0.209 | 120 | 0.375 | 0.300 | 0.250 | 0.215 | 0.439 | 0.351 | 0.293 | 0.251 | 140 | 0.438 | 0.350 | 0.292 | 0.250 | 0.512 | 0.410 | 0.342 | 0.293 | 160 | 0.501 | 0.400 |

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