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NATIONAL FULL-SCALE AERODYNAMICS COMPLEX

The National Full-Scale Aerodynamics Complex wind tunnel facility located at NASA Ames Research Center in Moffett Field, Calif., is operated by the U.S. Air Force's Arnold Engineering Development Complex.  In 2006, the Air Force signed a lease with NASA to reopen NFAC after the facility closed in 2003 due to budget pressures.  Full operational capability occurred in early 2008.  

NFAC is a unique facility primarily used for determining aerodynamic characteristics of large-scale and full-scale rotorcraft and powered-lift V/STOL aircraft, as well as tesing of wind turbines, parachutes, trucks, and other non-traditional types of testing.  The facility is composed of two large test sections and a common, six-fan drive system.  The 40-by-80 foot wind tunnel circuit is capable of providing test velocities up to 300 knots. The 80-by-120 foot test section is the world's largest wind tunnel and is capable of testing a full size Boeing 737 at velocities up to 100 knots.  A system of moveable vanes can be positioned so that air either drawn through the 80-by-120 foot test section and exhausted into the atmosphere, or driven around the closed circuit through the 40-by-80 foot test section.  A passive air exchange systems is utilized in the 40-by-80 circuit to keep air temperatures below 125 degrees Fahrenheit.  A wide range of available model support systems combine with this unique facility to allow successful completion of aerodynamic and acoustic experiments that cannot be achieved anywhere else.

The 40-by-80 foot wind tunnel was built in 1944.  In 1987, it became NFAC after the 80-by-120 foot test section was added and the fan drive system was replaced.  The new fan drive system is composed of six variable-pitch fans, each 40 feet in diameter arranged in two rows of three. Each fan has 15 laminated wood blades and is powered by a 22,500 horsepower electric motor. The six fans rotate together at 180 rpm drawing 106 megawatts of electricity at full power while moving more than 60 tons of air per second.

Unique, test specific requirements are explored with each customer to guide the experiment design and new systems are integrated into the facility as needed. Utility support systems that have been used for testing powered vehicles and components include variable frequency electrical power, hydraulic power units, cooling water, 150 and 400 Hz electrical power and jet fuel systems. Rotor test beds incorporating electric motors and rotor balance systems are available for testing complete rotor and hub systems independent of the flight vehicle.


Data Systems
The NFAC Data Acquisition System is a distributed computing system connected by both a real-time network using reflective memory, and a switched Ethernet and Local Area Network within the NFAC control room. Major Components consist of the Basic DAS, Dynamic DAS, Safety of Flight DAS, Real-Time Processor and Post-Point Processor.

Additional features include: 
     -- Calibrations traceable to National Institute of Standards and Technology standards.
     -- Support for dynamic acquisition of analog inputs. Basic DAS and Dynamic DAS data are acquired synchronous to rotor position for rotorcraft testing or by a common clock for non-rotor testing.
     -- Real-time calculations and engineering unit conversions with results instantly available to the user for review and diagnostics.
     -- Standard equations library available in the Real-Time Processor and Post-Point Processor to meet most aerodynamic test computational requirements. Full support of test dependent equations to meet unique customer requirements.
     -- Multiple, continuous near real-time displays for monitoring measured and computed parameters in table and plot format.
     -- Post-point data reduction, analysis, and plotting.

LANDING GEAR TEST FACILITY

Overview

The Landing Gear Test Facility (LGTF) has been a cornerstone of aerospace testing at Wright-Patterson Air Force Base since 1942, dedicated to ensuring the reliability and performance of aircraft landing gear systems.

Throughout its history, the LGTF has supported the warfighter by providing critical data to enhance the safety and effectiveness of landing gear, wheels, tires, and brakes, directly contributing to the mission of the United States Department of Defense. In addition to its military focus, the LGTF offers comprehensive testing services to commercial entities, employing world-unique test machines capable of simulating real-life conditions with unparalleled accuracy.

Guided by the core values of Integrity, Service, and Excellence, the LGTF consistently delivers precise and dependable data to both military and commercial partners.

Test Machine Capabilities

Overall System Specifications:

Max Speed: 250 mph
Max Acceleration: 21 ft/s2
Inertial Equivalent: 2,445 - 20,063 lbs.
Max Kinetic Energy: 41,750,000 ft-lbs.
 

South Carriage Specifications:

Max Load: 40,000 lbs.
Max Torque: 375,000 in-lbs.
Max Tire Size: 64 in
 

North Carriage Specifications:

Max Load: 25,000 lbs.
Max Torque: 72,000 in-lbs.
Max Tire Size: 48 in

Overall System Specifications:

Max Speed: 200 mph
Max Acceleration: 2 ft/s2
Inertial Equivalent: 10,147 - 162,987 lbs.
Max Kinetic Energy: 205,000,000 ft-lbs.

South Carriage Specifications:

Max Load: 301,500 lbs.
Max Brake Torque: 5,800,000 in-lbs.

Overall System Specifications:

Max Speed: 350 mph
Max Acceleration: 24 ft/s2

South Carriage Specifications:

Max Load: 150,000 lbs.
Max Yaw: ± 20°
Max Camber: ± 20°

North Carriage Specifications:

Max Load: 100,000 lbs.

Overall System Specifications:

Max Speed: 250 mph
Max Acceleration: 16 ft/s2
Max Vertical Load: 150,000 lbs.
Max Yaw: ± 20°
Max Camber: ± 10°

Overall System Specifications:

Max Compressive Load: 3,000,000 lbs.
Max Tension Load: 1,000,000 lbs.
Max Stroke: 60 in
Max Height: 28 ft
Max Width: 10 ft
Platen Size: 60.5 x 96 in

Overall System Specifications:

Max Vertical Load: 75,000 lbs.
Max Side Load: 30,000 lbs.
Max Yaw: ± 90°
Max Camber: ± 10°
Max Tire Size: 56 in.
Table Length: 20 ft.
Max Travel Speed: 3 in/s
Roll Distance: 217 in

Overall System Specifications:

Below-grade safety enclosure
Dimensions: 72 x 120 x 126 in.
Water Pressure Limit: 5,000 psi
Rate of Inflation: 10 psi/min

Drop Tower #1

Load Range: 750 - 3,600 lbs.
Wing Lift: 200 - 3,600 lbs.
 

Drop Tower #2

Load Range: 2,000 - 10,300 lbs.
Wing Lift: 200 - 10,300 lbs.
 

Drop Tower #3

Load Range: 6,500 - 50,000 lbs.
Wing Lift: 200 - 35,000 lbs.
 

Drop Tower #4

Load Range: 35,000 - 150,000 lbs.
Wing Lift: 200 - 150,000 lbs.

Load frame that accommodates multiple hydraulic cylinders to provide controlled forcing and operational stresses to test objects in all 6 axes.

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CONTACT US

704 TG/OL-ACL
Landing Gear Test Facility
Area B, Bldg. 31
Wright-Patterson AFB, OH 45433
(937) 255-9216
704.tg.olac@us.af.mil

WHERE TO FIND US