| . |
**Data for each of these
characteristics can be
obtained by contacting
the EICO
Aviation Specialist
at the NAVFAC Criteria
Office.
|
 The
F-22’s combination of stealth, supercruise, maneuverability, and integrated
avionics, coupled with improved supportability, represents an exponential
leap in warfighting capabilities and allows for the full realization
of operational concepts that are vital to the 21st century Air Force.
The F-22 is a critical component of the Global Strike Task Force that
is designed to project air dominance, rapidly and at great distances,
to counter and defeat threats that will attempt to deny access to our
forces. The F-22 cannot be matched by any known or projected adversary
fighter aircraft.
A combination of improved sensor capability, integrated avionics, improved
situational awareness, and improved weapons provides first-kill opportunity
against the threat. The F-22 possesses a sophisticated sensor suite
that allows the pilot to track, identify, shoot and kill the threat
before it detects the F-22. Significant advances in cockpit design and
avionics fusion improve the pilot's situational awareness. Advanced
avionic technologies allow the F-22 sensors to gather, integrate and
display essential information in the most useful format to the pilot.
|
|
Aircraft Type |
Fighter
|
|
Aircraft Manufacturer
|
Boeing
and Lockheed Martin
Corp.
|
Engine Manufacturer |
Pratt
& Whitney
|
Engine Number |
F119-PW-100
|
Type of Landing Gear |
Single Tricycle
|
Design Gear Load |
|
Design Tire Pressure |
|
Pass/Cov Ratio Channelized |
|
|
Pass/Cov Ratio Unchannelized
|
|
|
|
Wingspan |
44 ft 6 in
|
Length (Overall) |
62 ft 1 in
|
Height (Overall) |
16 ft 5 in
|
Wheelbase |
|
Nose to centerline of main gear |
|
|
Wheel track (tread) Main
|
10 ft 6 in
|
|
Wheel track (tread) Nose
|
|
Vertical clearance of wingtip at
maximum weight |
|
Centerline of fuselage to
approximate pivot point based on maximum
steering angle or locked wheels |
|
Height of jet engine on
centerline of fuselage |
|
|
|
Minimum turning radius |
|
Engine operating danger areas -
idle |
|
Ground clearance |
**
|
Electrical Service |
• Maximum kVa by aircraft
for 400Hz distribution |
|
Mechanical Service |
• Air starting system |
|
• Preconditioned air |
|
• Environmental control air |
|
|
|
Min takeoff weight |
40,000 lbs
|
Min takeoff distance with min
takeoff weight |
|
Min takeoff distance with min
takeoff weight with abort distance |
**
|
Max takeoff weight at peace-time |
60,000 lbs
|
Max takeoff weight at war-time |
|
Min takeoff distance with max
takeoff weight |
|
Min landing weight |
|
Max landing weight |
|
|
Peace-time weight used for pavement evaluation
|
|
• Min landing distance at min landing
weight
|
|
|
• Min landing distance at max landing
weight
|
|
View / Sort aircraft on Spreadsheet.
|
