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…show more content…
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
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