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.


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    Title :

    A Look inside the Langley 16-Foot Transonic Tunnel: User's Guide


    Contributors:

    Publication date :

    1981


    Size :

    197 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






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