Flight Vehicle Design Project 2

1508 Words Mar 27th, 2013 7 Pages
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
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In this case I used the values 1.8, 2, 2.2, 2.4, 2.6, 2.8, 3, 3.2 and described in the table below. (W/S)TO Calculations | CLmaxL | (W/S)L | (W/S)TO | 1.8 | 89.996 | 112.495 | 2 | 99.995 | 124.994 | 2.2 | 109.995 | 137.494 | 2.4 | 119.994 | 149.993 | 2.6 | 129.994 | 162.492 | 2.8 | 139.994 | 174.992 | 3 | 149.993 | 187.491 | 3.2 | 159.993 | 199.991 |
Step 6:
The plane must now be sized to the FAR25 climb requirements. On page 144 we can find the climb requirements for a two engine jet transport. From equations 3.21 and 3.22 we can derive the polar drag data and create a table.
Eqn 3.21 log10f = a + blog10Swet
Eqn 3.22 log10Swet = c + dlog10WTO
Values for a,b,c and d can be found on page 122 in table 3.4 using 0.003 for the equivalent skin friction coefficient and table 3.5 for