Study of the Boeing C17 Globemaster III structure and reproduction
The present project consists on the structural study of the Boeing C-17. Globemaster III in order to create a 1:50 scale model. The main research.
The roles and the responsibilities of registering MAA for a multi
• three (3) Boeing C-17A Globemaster III. heavy transport aircraft was acquired by the member states;. • the SAC organizations were established in order to
Barriers to Force Projection: The Impact of Climate Change on Aerial
17. Boeing “C-17 Globemaster III
C-17 HEAVY AIR LIFT INFRASTRUCTURE
In March 2006 the Minister for Defence announced the Australian Defence Force's acquisition of four Boeing C-17 Globemaster III aircraft and associated
C-17A Globemaster III
The Boeing C-17A Globemaster III is a high-wing four-engine
C-17 Globemaster III
The flexible. McDonnell Douglas (and then Boeing) airplane carries out strategic airlift tactical airlift
Military Airlift: C-17 Aircraft Program
5. jun. 2007 The Air Force's C-17 Globemaster III is a long-range cargo/transport aircraft manufactured by Boeing (since its acquisition of McDonnell Douglas ...
Backgrounder
Description and Purpose: The Boeing C-17 Globemaster III is designed to fulfill military and humanitarian airlift needs well into the 21st century.
Military Airlift: C-17 Aircraft Program
5. jun. 2007 The Air Force's C-17 Globemaster III is a long-range cargo/transport aircraft manufactured by Boeing (since its acquisition of McDonnell Douglas ...
3.1 Acquisition and operation of C-17 Globemaster III aircraft
The aircraft produced by M/s Boeing of USA is a long range heavy transport aircraft with in-flight refueling capabilities and range of 4200 kms with maximum
C?17.
08-May-2009 The C?17 Globemaster III. • Manufactured by Boeing. Integrated Defense Systems. • Developed from McDonnell. Douglas YC?15.
Study of the Boeing C17 Globemaster III structure and reproduction
The present project consists on the structural study of the Boeing C-17. Globemaster III in order to create a 1:50 scale model. The main research.
C-17 Globemaster III
C-17 Globemaster III. Andrew Smithey Mach Number of Flow Around C-17 Airfoil during Cruise. M. Upper Surface ... Boeing 757. ? C-17 uses 4 of these.
C-17 Globemaster III
incorporated into the military's newest jet transport – the Boeing (previously. McDonnell Douglas) C-17 Globemaster III. Both the Air Force and industry.
Boeing C-17 Transport
Boeing C-17 Globemaster III is a high-wing four-engine
U.S. Air Force C-17 Aircraft Supply Chain Impact Assessment Final
The C-17 Globemaster III is the most flexible cargo aircraft to enter If Boeing and the USAF was not a customer since 2012 and the respondent's ...
The Magic is in the People
C-17 Globemaster III Program
in the UK
trainer aircraft in 1938 to this year's reorganization of Boeing's UK de- fense businesses under the umbrella sixth C-17 Globemaster III on June 11. The.
Globemaster
Globemaster
III IIIAndrew 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 areasCapable of
Capable of
performing theater performing theater airlift missions airlift missionsImage 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 2Wing Sweep: 25°
Wing Sweep: 25°
Wing WingAnhedral
Anhedral
: 3° : 3°H.T. span: 65 ft
H.T. span: 65 ft
H.T. Area: 845 ft
H.T. Area: 845 ft
2 2H.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 2V.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.c10% 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 : 0.0111Aspect Ratio: 7.673
Aspect Ratio: 7.673
e: 1.01 e: 1.01Winglets give Oswald efficiency
Winglets give Oswald efficiency
factor greater than 1.0 factor greater than 1.0Drag at Cruise
Drag at Cruise
For cruise condition:
For cruise condition:
Friction Drag:
Friction Drag:
C C Df Df =0.00510 =0.00510Form Drag:
Form Drag:
C C Dform Dform =0.00109 =0.00109Wave Drag:
Wave Drag:
C C Dwave Dwave =0.00169 =0.00169Wave Drag at Cruise
Wave Drag at Cruise
Best Guess
Best Guess
airfoil given limited data airfoil given limited dataNASA Supercritical SC(2)-0412
NASA Supercritical SC(2)-0412
Design
Design
C C l l = 0.4 = 0.412% thick
12% thick
TSFOIL Results:
TSFOIL Results:
2D 2D C C l l = 0.872 = 0.872 C C p p = -0.841 = -0.841Image 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 MUpper 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 DragPolars
Polars
00.020.040.060.080.10.120.140.160.180.2
-0.5 0 0.5 1 1.5 2C-17 Cruise Drag Polar
C D C LTakeoff/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 : 3.156Landing (at sea level)
Landing (at sea level)
Mach Number: 0.13
Mach Number: 0.13
C C L L : 5.014 : 5.014The 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 as3,500 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 superiorSTOL performance
STOL performance
C C Lmax Lmax 7.2 7.2T-tail configuration
T-tail configuration
used to avoid large used to avoid large downwash from downwash from high-lift system high-lift systemVertical tail and
Vertical tail and
rudder sized for rudder sized for engine out engine out conditions conditionsImage from www.fas.org
F117-PW-100 Turbofan Engine
F117-PW-100 Turbofan Engine
Manufactured by Pratt
Manufactured by Pratt
& Whitney & WhitneyMilitary 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 at40,400 lb of thrust
40,400 lb of thrust
apiece apieceCapable of thrust
Capable of thrust
reversal reversalImage 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 GroupNASA 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,
19761976
Pratt & Whitney
Pratt & Whitney
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