Joe Syler, Aerospace Testing Alliance outside machinist, makes an adjustment to the Ares I first stage booster model in the center’s von Karman Facility’s Tunnel B prior to the resumption of heat transfer testing. (Photo by David Housch)
A model of the X-15 rocket shown in AEDC’s von Karman Gas Dynamics Facility wind tunnel A. The X-15 underwent air worthiness and stability testing in the late 1950s. AEDC played a major role in the development of the X-15 and continues to provide instrumental aeronautical tests for U.S. military, NASA, and commercial air and space craft.
The Terminal High Altitude Area Defense (THAAD) missile is designed to intercept and destroy ballistic missiles inside or outside the atmosphere while they are in their final, or terminal, phase of flight. The THAAD model shown here was tested at AEDC’s Hypervelocity Wind Tunnel 9 facility in White Oak, Md., to collect high-accuracy static stability and drag data. Once demonstrated, the same test model and instrumentation were used in a test in the von Karman Facility to confirm complementary test capabilities exist between the two AEDC facilities. (U.S. Air Force photo)
The von Karman Gas Dynamics Facility, located at Arnold Engineering Development Complex, Arnold AFB, Tenn., is the nation's largest aerospace ground test facility complex.
The von Karman Gas Dynamics Facility
(Hypersonic Wind Tunnels A/B/C) The von Karman Gas Dynamics Facility has three continuous-flow units, Tunnels A, B and C. The tunnels are used extensively to obtain large aerodynamic and aerothermodynamic databases that are used to develop supersonic and hypersonic flight vehicles. Virtually every high-speed flight vehicle has required testing in Tunnels A/B/C, from reentry and tactical vehicles and space capsules, to the X-planes and winged vehicles.
Since the early 1970s, for example, various models of the space shuttle have been tested in these tunnels to determine the aerodynamic relationship between its main components--the orbiter, the external tanks and the two solid rocket boosters.
VKF Wind Tunnel Operation
Air is the working medium used in all VKF tunnels. They may be operated for hours at a time using air supplied by a nine-stage compressor system that is an eighth of a mile long and is driven by electric motors providing up to 92,500 horsepower. Air is stored in two reservoirs with a combined capacity of approximately 542,000 pounds. This air is used to simulate jet flows from the models and provides high-pressure air for the power ejectors in all facilities at AEDC.
Tunnel A is a 40-inch squared, continuous, closed-circuit, variable density, supersonic wind tunnel with a Mach number range of 1.5 to 5.5.
Devoted primarily to explorations of aerodynamic design, Tunnel A's unique feature is its computer controlled continuous-curvature nozzle that can vary the tunnels Mach number. Tunnel A can obtain a maximum temperature of 290 degrees Fahrenheit.
Tunnel B is a 50-inch, closed-circuit hypersonic tunnel with continuous-flow capability with a Mach number capability of 6 and 8. Provided with air heated to a maximum of 900 degrees Fahrenheit with natural gas-fired heaters. Tunnel B is also primarily explores aerodynamic design.
Tunnel C is the third continuous-flow tunnel in the VKF facility with a Mach number capability of 4, 6, and 10. It offers an aerothermal environment for testing materials proposed for use on space vehicles and aircraft. The one-of-a-kind wind tunnel makes it possible to subject flight hardware to a combination aerodynamic and thermodynamic--or heating--effects up to 1,440 degrees Fahrenheit so engineers can study how aerospace vehicles and materials respond to the combined effects of external heating, internal heat conduction and pressure loading.
Special photographic techniques are used in the tunnels to visualize shock waves and heating patterns.
Captive Trajectory Support Testing The Captive Trajectory Support systems for AEDC wind tunnels allow computer-controlled, six-degrees-of-freedom positioning of a missile, bomb, or any other store in close proximity to the aircraft (parent) model. Operational CTS systems exist in Tunnels A, B, and C. Applications in the PWT transonic and supersonic test units consist of store separation and flow-field mapping.
History The origin of AEDC's VKF may be traced back to the end of World War II, when General of the Air Force H.H. "Hap" Arnold -- then Army Air Forces commander and the man for whom the center was named -- sought to determine how the Germans had made such rapid progress in developing high-performance jet aircraft and rocket-powered missiles. He enlisted the help of Dr. Theodore von Karman, one of history's great aeronautical scientists, to conduct a survey of the German facilities as the war was ending.
Dr. von Karman's subsequent report recommended the Air Force create a center with "...wind tunnel facilities to attain speeds up to three times the velocity of sound, with large enough test sections to accommodate models of reasonable size, including jet propulsion units, and one ultrasonic wind tunnel for exploration of the upper frontier of the supersonic speed range. Ample facilities for the study of combustion and other characteristics of propulsion systems at very high altitudes should be provided..."
The decision to proceed with a gas dynamic facility was made in 1950 at a Washington, D.C., meeting by representatives of the Air Force, Navy, NACA (forerunner of NASA), the government's Research Development Board and the aircraft industry.
The Actual directive to the Corps of Engineers to proceed with construction did not come until almost two years later. In 1959, two years after completion of the two large continuous-flow tunnels, the facility was renamed after Dr. von Karman, then chief scientific advisor to the
Air Force and an enthusiastic participant helping AEDC.