A REPORT ON RESEARCH DIRECTED TOWARD THE DESIGN, DEVELOPMENT, CONSTRUCTION, AND TESTING OF 'AERODYNAMIC CAVITIES'.
MASSACHUSETTS INST OF TECH CAMBRIDGE NAVAL SUPERSONIC LAB
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The report describes the design and testing of two aerodynamic cavities, capable of holding sensitive instrumentation, built for installation on a KC-135 airplane. Each cavity is housed in a container 24 inches in diameter and 30 inches long. A neck three inches long joins the end of the container to the fuselage skin. Interior dimensions of the cavity are 11-34 inches square by 24 inches deep. A door completes each package making it a self-contained unit. Wind-tunnel tests simulating altitudes between 30,000 and 50,000 feet and at Mach numbers between 0.4 and 0.8 show that low sound pressure levels can be maintained within the cavities. A means of moving the apparatus occupying the cavity close to the airstream is recommended to insure these low sound pressure levels. Preliminary investigations led to water table tests as a means of studying vortex activity and general cavity behavior. Author
- Transport Aircraft