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C-17 C-17

Globemaster

Globemaster

III III

Andrew Smithey

Andrew Smithey

Ryan Wagner

Ryan Wagner

Brady White

Brady White

Image from www.fas.org

C-17 Mission

C-17 Mission

Strategic airlift for

Strategic airlift for

U.S. Air Force

U.S. Air Force

Deployment of

Deployment of

troops or cargo to troops or cargo to operating bases or operating bases or forward forward deployment areas deployment areas

Capable of

Capable of

performing theater performing theater airlift missions airlift missions

Image from www.fas.org

Basic Geometry

Basic Geometry

Length: 173.92 ft

Length: 173.92 ft

Diameter: 33.67 ft

Diameter: 33.67 ft

Wingspan: 170.75 ft

Wingspan: 170.75 ft

Wing Area: 3800 ft

Wing Area: 3800 ft

2 2

Wing Sweep: 25°

Wing Sweep: 25°

Wing Wing

Anhedral

Anhedral

: 3° : 3°

H.T. span: 65 ft

H.T. span: 65 ft

H.T. Area: 845 ft

H.T. Area: 845 ft

2 2

H.T. Sweep: 27°

H.T. Sweep: 27°

H.T. H.T.

Anhedral

Anhedral

: 3° : 3°

V.T. Area: 685 ft

V.T. Area: 685 ft

2 2

V.T. Sweep: 41 °

V.T. Sweep: 41 °

Image from www.fas.org

Winglet Geometry

Winglet Geometry

Height: 8.92 ft

Height: 8.92 ft

Sweep: 30° (aft)

Sweep: 30° (aft)

Vertical Angle: 15°

Vertical Angle: 15°

Image from www.fas.org

Cruise Conditions

Cruise Conditions

Weight: 585,000 lb (max peace-time)

Weight: 585,000 lb (max peace-time)

Mach Number: 0.76

Mach Number: 0.76

(450 (450 kts kts at 29,000 ft) at 29,000 ft)

Range: 4,741 nm (without mid-air

Range: 4,741 nm (without mid-air

refueling) refueling) C C L L : 0.578 : 0.578 C C L L : 0.11458 /° : 0.11458 /° : 5.0446° : 5.0446°

Neutral point located 73.0 ft from nose

Neutral point located 73.0 ft from nose

(65% of (65% of m.a.c m.a.c

10% static longitudinal stability

10% static longitudinal stability

Induced Drag at Cruise

Induced Drag at Cruise

Cruise C

Cruise C

L L : 0.578 : 0.578 C C Di Di : 0.0111 : 0.0111

Aspect Ratio: 7.673

Aspect Ratio: 7.673

e: 1.01 e: 1.01

Winglets give Oswald efficiency

Winglets give Oswald efficiency

factor greater than 1.0 factor greater than 1.0

Drag at Cruise

Drag at Cruise

For cruise condition:

For cruise condition:

Friction Drag:

Friction Drag:

C C Df Df =0.00510 =0.00510

Form Drag:

Form Drag:

C C Dform Dform =0.00109 =0.00109

Wave Drag:

Wave Drag:

C C Dwave Dwave =0.00169 =0.00169

Wave Drag at Cruise

Wave Drag at Cruise

Best Guess

Best Guess

airfoil given limited data airfoil given limited data

NASA Supercritical SC(2)-0412

NASA Supercritical SC(2)-0412

Design

Design

C C l l = 0.4 = 0.4

12% thick

12% thick

TSFOIL Results:

TSFOIL Results:

2D 2D C C l l = 0.872 = 0.872 C C p p = -0.841 = -0.841

Image from NASA Technical Paper 2969

00.20.40.60.81

0 0.2 0.4 0.6 0.8 1 1.2 1.4 Mach Number of Flow Around C-17 Airfoil during Cruise x/c M

Upper Surface

Lower Surface

00.20.40.60.81

-2 -1.5 -1 -0.5 0 0.5 1 1.5 2 C p x/c Pressure Coefficient Distribution for C-17 Airfoil during Cruise C p,upper C p,lower Drag Drag

Polars

Polars

00.020.040.060.080.10.120.140.160.180.2

-0.5 0 0.5 1 1.5 2

C-17 Cruise Drag Polar

C D C L

Takeoff/Landing

Takeoff/Landing

Takeoff (at sea level)

Takeoff (at sea level)

Mach Number: 0.18

Mach Number: 0.18

C C L L : 3.156 : 3.156

Landing (at sea level)

Landing (at sea level)

Mach Number: 0.13

Mach Number: 0.13

C C L L : 5.014 : 5.014

The C-17 was designed

The C-17 was designed

for STOL capabilities and for STOL capabilities and can takeoff and land in can takeoff and land in distances as short as distances as short as

3,500 ft.

3,500 ft.

A sophisticated high-lift

A sophisticated high-lift

system is needed for system is needed for both takeoff and landing. both takeoff and landing.

Image from www.fas.org

Note: Lift coefficients determined from gross

maximum takeoff weight.

High-lift System

High-lift System

Externally-blown

Externally-blown

flaps for superior flaps for superior

STOL performance

STOL performance

C C Lmax Lmax 7.2 7.2

T-tail configuration

T-tail configuration

used to avoid large used to avoid large downwash from downwash from high-lift system high-lift system

Vertical tail and

Vertical tail and

rudder sized for rudder sized for engine out engine out conditions conditions

Image from www.fas.org

F117-PW-100 Turbofan Engine

F117-PW-100 Turbofan Engine

Manufactured by Pratt

Manufactured by Pratt

& Whitney & Whitney

Military variant of

Military variant of

PW2000 used on

PW2000 used on

Boeing 757

Boeing 757

C-17 uses 4 of these

C-17 uses 4 of these

engines certified at engines certified at

40,400 lb of thrust

40,400 lb of thrust

apiece apiece

Capable of thrust

Capable of thrust

reversal reversal

Image from www.pw.utc.com

References

References

Federation of American Scientists

Federation of American Scientists

www.fas.org www.fas.org Jane Jane s 2003 Edition, Jane s 2003 Edition, Jane s Information s Information Group Group

NASA Langley Research Center

NASA Langley Research Center

NASA Technical Paper 2969: NASA

NASA Technical Paper 2969: NASA

Supercritical Airfoils, 1990.

Supercritical Airfoils, 1990.

Nicolai, Fundamentals of Aircraft Design,

Nicolai, Fundamentals of Aircraft Design,

1976
1976

Pratt & Whitney

Pratt & Whitney

www.pw.utc.com www.pw.utc.comquotesdbs_dbs7.pdfusesText_13

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