Transonic Wind Tunnels
Lockheed Martin Missiles and Fire Control - Dallas
High Speed Wind Tunnel
Celebrating 40 Years of Service
Description
| Operational Status | Test Section Size |
Active |
4 x 4 x 5 ft |
| Speed Range | Temp. Range | Reynolds No. | Dynamic Pres. | Stagnation Pres. |
| Mach 0.4 - 4.8 | 540 - 620oR | 4 to 34 (per ft X 106) | 150 - 5,000 psf | 19.8 - 367.5 psia |
The High Speed Wind Tunnel is a blowdown-to-atmosphere, transonic-supersonic, adjustable-Mach-number facility.
Testing Capabilities
Equipped for force and moment, pressure, inlet performance, flutter, buffet, dynamic stability, jet effects (hot and cold), captive trajectory, and free-drop store separation testing of aircraft and missile configurations. Computer control or tunnel pressure programs, constant Reynolds number (pressure as function of temperature), model roll/pitch support system, inlet test systems, and CTS system. Auxiliary air at pressures up to 500 psi for flow rates to 18 lb/sec (to 130 in/sec flow rate at lowest pressure).
Data Acquisition
110-channel data (individual amplifier) acquisition and processing system, with on-site, on-line computer, and plotting system. Up to 110 individual pressure transducers are used for inlet testing and similar pressure measurement requirements. Scanivalve and electronically scanned module-type pressure equipment are also used. Analog (FM) tape recorders, ocsillographsm high-speed movie cameras, and video recorder are used.
Current Programs
Planned Improvements
Local Informational Contact
Carl Ziegler
Manager, Wind Tunnel Laboratories
Lockheed Martin Vought Systems
P.O. Box 650003
Mail Stop LJS-05
Dallas, Tx 75265-0003
Phone - (972) 946-2751
Fax -
email - carl.ziegler@lmco.com
Information Current as of August 7, 1999
Transonic Wind Tunnels
Lockheed - Martin
Marietta, GA
Compressible Flow Wind Tunnel
(CFWT)
Description
Blowdown, 600 psi to atmosphere; variable porosity test section walls (0-10% open area)
| Operational Status | Test Section Size |
Closed |
20 x 28 x 72 in |
| Speed Range | Temp. Range | Reynolds No. | Dynamic Pres. | Stagnation Pres. |
| Mach 0.2 - 1.3 ( ft/sec) |
Ambient | 5 - 55 (per ft X 106) |
80 - 10,760 psf | 20 - 175 psia |
Testing Capabilities
Multiple test section options including: (1) two-dimensional solid sidewalls and variable porosity top and bottom test section walls, models typically 20-in span and 7-in chord; (2) semispan floor - mounted semispan models on solid floor with boundary layer removal upstream of model, models typically 17-in semispan; and (3) full span - computer controlled sting system, models typically 15-in span. Wall mounted pressure rails available for all test section configurations to measure pressures near the test section walls. These rail pressures may be used to evaluate wall boundary conditions.
Data Acquisition
Data acquisition and reduction on site.
Current Programs
Planned Improvements
Local Information Contact
Gerald A Pounds
Group Engineer
Wind Tunnels Test GroupPhone - (404) 424-4158
Fax -
Email -
Information Current as of Jan-1985
Transonic Wind Tunnels
Lockheed Martin
California Company
Free-Jet Propulsion Tunnel
Description
| Operational Status | Test Section Size |
Closed |
6 x 7 x 20 ft |
| Speed Range | Temp. Range | Reynolds No. | Dynamic Pres. | Stagnation Pres. |
| Mach 0.2 - 2.65 | 540 - 1400oR | 0 to 12 (per ft X 106) | 0 - 6,000 psf | --- psia |
Intermittent blowdown to atmosphere, hot gas ingestion.
Testing Capabilities
This tunnel permits simultaneous aerodynamic and propulsion studies with combustion capability. Thrust levels to 10,000 lb may be accommodated, dependant on pressure altitude required. Testing is not limited to propulsion devices but includes any type of airflow or combustion device that requires a discharge at altitude or ambient pressure. Pressure altitudes from site elevation to 180,000 ft are possible with extension to 300,000 ft for static ignition tests. Time to climb to 150,000 ft in 1 minute is readily obtained, and special provisions can be made to reduce this to about 15 sec.
Data Acquisition
Fifty channels of information can be recorded and reduced on-site with a return time of 2 to 5 min to run (blow).
Current Programs
Planned Improvements
Local Informational Contact
Phone - ( )
Fax - ( )
email -