A380 Presentation

Trevor StephensSteve TodtenhagenBilly Oehlschlager

Doug Morton

Aircraft Specs

Dimensions:

Length = 238 ft. 8 in.Wing Span = 261 ft. 10 in.Height = 79 ft.Area = 8934 ft^2Sweep = 33.5°AR = 7.67

Weights:Empty 610,700lbTOGW 1,234,600lb

Power Plant:

Ranges from68,000lb/engine to84,000lb/engine RR Trent900 or

81,500lb/engine

Engine Alliance GP-7200

Performance:

Long range cruising speedM 0.85.

Range 8,000nm

Service ceiling 43.000ft

Cdo, Parasite Drag (Friction)

8488H-Tail

84734TOTAL

3532V-Tail

19250Wing

3010 x 4Engine x 4

41422Fuselage

Swet (ft^2)Component At M=.85

CDF (FrictionDrag) = 0.00729

CDForm (formdrag) = 0.0062

L/Dmax =sqrt(!*Cdo*AR*e) =

0.422

6% Thickness SC Airfoil

For the weight and airspeed of A380 the required Cl is 0.79. TSFoildetermined that at cruise condition, Cl = 0.74 and Cm = -0.24

NASA SC(2)-0406

-0.5

-0.4

-0.3

-0.2

-0.1

0

0.1

0.2

0.3

0.4

0.5

0 0.2 0.4 0.6 0.8 1

x/c

t/c

Pressure t/c = 6%

-1

-0.8

-0.6

-0.4

-0.2

0

0.2

0.4

0.6

0.8

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

x/c

t/c

10% Thickness SC Airfoil

Pressure for x/c = 10%

-1.5

-1

-0.5

0

0.5

1

1.5

0 0.2 0.4 0.6 0.8 1

x/c

Cp

TSFoil determined that at cruise condition, Cl = 0.68 and Cm = -0.29.

When AoA was increased to represent twist of 5, Cl = -.17

NASA SC(2)-0610

-0.5

-0.4

-0.3

-0.2

-0.1

0

0.1

0.2

0.3

0.4

0.5

0 0.2 0.4 0.6 0.8 1

x/c

t/c

12% Thickness SC Airfoil

Pressure t/c = 12%

-1.5

-1

-0.5

0

0.5

1

1.5

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

x/c

Cp

NASA SC(2)-0412

-0.5

-0.4

-0.3

-0.2

-0.1

0

0.1

0.2

0.3

0.4

0.5

0 0.2 0.4 0.6 0.8 1

x/c t/

c

TSFoil determined that at cruise condition, Cl = 0.503 and Cm = -0.27.

When AoA was increased to represent twist of 7, Cl = -.25

LAMDES – min drag due to liftMinimum Drag Due to Lift as a Function of CG Location

0.02600

0.02700

0.02800

0.02900

0.03000

0.03100

0.03200

20 22 24 26 28 30 32 34 36 38 40

CG Location (meters from nose)

Ind

uce

d D

rag

Co

effi

cien

t

Minimum Drag Due to Lift

Estimated CG Location

NP determined to be 36.2 m, Static Margin is 2%MAC from predicted CG fromLanding gears. If CG of 30m for min drag, SM is 58%MAC. This creates largertrim drag to cause the required moments for control.

Linear Theory Twist Distribution

-2

0

2

4

6

8

10

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

y/(b/2)

Tw

ist

(deg

rees

)

Planform 1

Planform 2

Root & Tip Camber Lines

0

0.005

0.01

0.015

0.02

0.025

0.03

0.035

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

x/c

Cam

ber

Lin

e

Tip camber line, y/(b/2)=0.975

Root camber line, y/(b/2)=0.0177

Cl Distribution

0

0.2

0.4

0.6

0.8

1

1.2

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

y/(b/2)

Cl

Planform 1

Planform 2

80 m Gate Box Requirement

Larger span loading on the A380 is the result of the 80meter gate box. If the span were allowed to be bigger,the aspect ratio would increase thus decreasing the spanload on the aircraft. This would allow for less structure inthe wing, making it thinner which would decrease thedrag and increase fuel economy.

AR -A380 = 7.67A340 = 9.15

W/b -A380 = 4714.55 lb/ftA340 = 3865 lb/ft

W/S -A380 = 138 lb/ft^2A340 = 170 lb/ft^2