The 16-foot transonic tunnel is a single-return atmospheric wind tunnel having a slotted test section. The primary emphasis for research in this facility is the integration of the propulsion system into advanced aircraft concepts. The large test section size, 15.5 feet in diameter lends itself to conducting research in this area, where large models are required in order to provide adequate definition of the model geometry associated with the integration of the propulsion system. The nominal test Mach number range for this facility varies from 0.20 to 1.3. Topics covered include (1) facility description; (2) model installation equipment for aerodynamics; (3) model support system for propulsion simulation testing; (4) propulsion simulation systems; (5) calibrating propulsion simulation systems; (6) instrumentation; (7) data acquisition; (8) model design criteria; and (9) wind tunnel test planning.
A Look inside the Langley 16-Foot Transonic Tunnel: User's Guide
1981
197 pages
Report
No indication
English
Langley annular transonic tunnel
Engineering Index Backfile | 1952
|The Langley Annular Transonic Tunnel
NTRS | 1952
|The Langley annular transonic tunnel
TIBKAT | 1952
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