Flutter Test of a 0.50-Scale MOL Meteoroid Shield Panel at Mach Numbers from 1.2 to 2.5
Final rept. 31 Oct-11 Dec 1968
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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A 0.50-scale model of the meteoroid shield portion of the MOL laboratory vehicle was tested in Tunnels 16T and 16S of the Propulsion Wind Tunnel Facility. The model consisted of a sting-supported hollow duct assembly about which the dynamically scaled meteoroid shield skin and various protuberances were mounted. The test objective was to determine if the shield was free of destructive flutter in the flight dynamic pressure environment. Principal shield data included measurements of strain, displacement, temperature, noise level, surface pressure, and boundary-layer profile. Data were recorded at nominal Mach numbers from 1.25 to 1.50 in Tunnel 16T and from 1.70 to 2.25 in Tunnel 16S. Dynamic pressure was varied from tunnel minimums to levels that exceeded the scaled flight value. No indications of flutter were observed.
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