The operational characteristics and equipment associated with the Langley 16-foot transonic tunnel complex which is located in buildings 1146 and 1234 at the Langley Research Center are described in detail. This complex consists of the 16-foot transonic wind tunnel, the static test facility, and the 16- by 24-inch water tunnel research facilities. The 16-foot transonic tunnel is a single-return atmospheric wind tunnel with a 15.5 foot diameter test section and a Mach number capability from 0.20 to 1.30. The emphasis for research conducted in this research complex is on the integration of the propulsion system into advanced aircraft concepts. In the past, the primary focus has been on the integration of nozzles and empennage into the afterbody of fighter aircraft. During the last several years this experimental research has been expanded to include developing the fundamental data base necessary to verify new theoretical concepts, inlet integration into fighter aircraft, nozzle integration for supersonic and hypersonic transports, nacelle/pylon/wing integration for subsonic transport configurations, and the study of vortical flows (in the 16- by 24-inch water tunnel). The purpose here is to provide a comprehensive description of the operational characteristics of the research facilities of the 16-foot transonic tunnel complex and their associated systems and equipments.
User's Guide to the Langley 16-Foot Transonic Tunnel Complex. Revision 1
1990
240 pages
Report
No indication
English
Test Facilities & Equipment , Laboratory & Test Facility Design & Operation , Research facilities , Static tests , Transonic wind tunnels , Aircraft design , Hydraulic test tunnels , Propulsion system configurations , Afterbodies , Buildings , Data bases , Fighter aircraft , Hypersonics , Mach number , Supersonic transports , Systems integration , Tail assemblies , Vortices
Langley annular transonic tunnel
Engineering Index Backfile | 1952
|The Langley Annular Transonic Tunnel
NTRS | 1952
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